Garmin | G1000 NXi: Cessna Citation Mustang | Garmin G1000 NXi: Cessna Citation Mustang G1000 NXi System Maintenance Manual with Instructions for Continued Airworthiness, Textron Model 510 Mustang

Garmin G1000 NXi: Cessna Citation Mustang G1000 NXi System Maintenance Manual with Instructions for Continued Airworthiness, Textron Model 510 Mustang
G1000 NXi
NXi updates to G1000 on Textron Aviation 510
System Maintenance Manual
Textron Aviation Inc.
Model 510 Citation Mustang
Includes Instructions for Continued Airworthiness
for STC SA01896WI
190-02450-01
2019
Revision 1
© Copyright 2019
Garmin Ltd. or its subsidiaries
All Rights Reserved
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to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of
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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
Revision Revision Date
1
02/04/19
Initial Release
Description
DOCUMENT PAGINATION
Section
Table of Contents
Section 1
Section 2
Section 3
Section 4
Section 5
Section 6
Section 7
Section 8
Section 9
Appendix A
Pagination
3-5
6-9
10-16
17-42
43-48
48-56
57-60
61-74
75-82
83-90
91
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 1
INFORMATION SUBJECT TO EXPORT CONTROL LAWS
This document may contain information which is subject to the Export Administration
Regulations (“EAR”) issued by the United States Department of Commerce (15 CFR, Chapter
VII Subchapter C) and which may not be exported, released or disclosed to foreign nationals
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WARNING
Perchlorate Material – special handling may apply, Refer to www.dtsc.ca.gov./hazardouswaste/
perchlorate.
IMPORTANT
All 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.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 2
TABLE OF CONTENT
1.
INTRODUCTION ......................................................................................................................................... 6
1.1
1.2
1.3
1.4
1.5
1.6
1.7
1.8
2.
SYSTEM DESCRIPTION ...............................................................................................................................10
2.1
2.2
2.3
2.4
3.
AIRWORTHINESS LIMITATIONS ........................................................................................................................... 43
SERVICING INFORMATION .................................................................................................................................43
MAINTENANCE INTERVALS ................................................................................................................................45
VISUAL INSPECTION .........................................................................................................................................46
ELECTRICAL BONDING TEST ............................................................................................................................... 47
TROUBLESHOOTING ..................................................................................................................................49
5.1
5.2
5.3
5.4
5.5
5.6
5.7
5.8
5.9
6.
CONFIGURATION MODE OVERVIEW .................................................................................................................... 17
G1000 SYSTEM SOFTWARE INFORMATION .......................................................................................................... 22
CONFIGURATION MODE ...................................................................................................................................23
G1000 HARDWARE/SOFTWARE COMPATIBILITY CHECK ......................................................................................... 23
EQUIPMENT VERIFICATION (THIRD PARTY/OPTIONAL EQUIPMENT DOCUMENTATION) ................................................. 23
CONFIGURATION CHECKLIST .............................................................................................................................. 27
G1000 SOFTWARE/CONFIGURATION PROCEDURE ................................................................................................ 28
SYSTEM SOFTWARE AND CONFIGURATION LOAD ................................................................................................... 29
AIRFRAME TRIM CALIBRATION CONFIRMATION ..................................................................................................... 36
FEATURE ENABLEMENT ....................................................................................................................................37
CONFIGURATION MANAGER .............................................................................................................................. 39
CLEARING DEFAULT USER SETTINGS .................................................................................................................... 39
DATABASE LOADING ........................................................................................................................................39
CONFIGURATION OF NAVIGATION MAP FOR TRAFFIC SYSTEM .................................................................................. 41
FLIGHT STREAM 510 FIRMWARE REVIEW ............................................................................................................ 41
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ....................................................................................43
4.1
4.2
4.3
4.4
4.5
5.
EQUIPMENT DESCRIPTIONS ............................................................................................................................... 10
SYSTEM INTERFACE SUMMARY ........................................................................................................................... 13
POWER REQUIREMENTS ...................................................................................................................................14
ELECTRICAL BONDING ......................................................................................................................................14
CONTROL AND OPERATION .......................................................................................................................17
3.1
3.2
3.3
3.4
3.5
3.6
3.7
3.8
3.9
3.10
3.11
3.12
3.13
3.14
3.15
4.
CONTENT, SCOPE, PURPOSE ................................................................................................................................6
APPLICABILITY .................................................................................................................................................. 6
ORGANIZATION................................................................................................................................................. 6
DEFINITIONS/ABBREVIATIONS ............................................................................................................................. 7
UNITS OF MEASURE...........................................................................................................................................7
PUBLICATIONS .................................................................................................................................................. 8
REVISION AND DISTRIBUTION .............................................................................................................................. 9
GARMIN TECHNICAL SUPPORT ............................................................................................................................. 9
SYSTEM ANNUNCIATIONS .................................................................................................................................50
AURAL & AUDIO ALERTS ..................................................................................................................................51
GDU 105X TROUBLESHOOTING ........................................................................................................................ 51
GDU 105X ALERTS.........................................................................................................................................52
GMA 1360D TROUBLESHOOTING ..................................................................................................................... 53
GDL 69A SXM TROUBLESHOOTING ................................................................................................................... 54
GCU 475 TROUBLESHOOTING .......................................................................................................................... 55
SOFTWARE/CONFIGURATION TROUBLESHOOTING ................................................................................................. 56
CONNECTOR LAYOUT .......................................................................................................................................56
EQUIPMENT REMOVAL & INSTALLATION ..................................................................................................57
6.1
GDU 1050A/1550 .......................................................................................................................................57
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 3
6.2
6.3
6.4
6.5
6.6
7.
GARMIN G1000 LRU REPLACEMENT/CONFIGURATION & TESTING .............................................................61
7.1
7.2
7.3
7.4
7.5
7.6
8.
GIA BOOT BLOCK LOAD ...................................................................................................................................61
GDU 1050A/1550 PFD & MFD..................................................................................................................... 62
GMA 1360D AUDIO PANEL ............................................................................................................................. 66
GTX 345R TRANSPONDER ............................................................................................................................... 69
GDL 69A OR GDL 69A SXM DATA LINK ............................................................................................................ 71
GCU 475 FMS CONTROLLER............................................................................................................................ 72
SUBSYSTEM FUNCTIONAL CHECKS.............................................................................................................75
8.1
8.2
8.3
8.4
8.5
8.6
8.7
8.8
9.
GMA 1360D AUDIO PANEL ............................................................................................................................. 57
GTX 345R TRANSPONDER ............................................................................................................................... 58
GDL 69A SXM SATELLITE RECEIVER .................................................................................................................. 58
GCU 475 CONTROLLER ...................................................................................................................................59
CONFIGURATION MODULES .............................................................................................................................. 59
TAWS FUNCTIONAL CHECK .............................................................................................................................. 75
CHARTVIEW FUNCTIONAL CHECK ....................................................................................................................... 76
SAFETAXI FUNCTIONAL CHECK ........................................................................................................................... 77
LOW SPEED AWARENESS BAND CHECK ................................................................................................................ 78
DME FUNCTIONAL CHECK ................................................................................................................................79
ADF FUNCTIONAL CHECK .................................................................................................................................79
HF RADIO FUNCTION CHECK ............................................................................................................................. 80
KTA‐870 TAS TRAFFIC SYSTEM FUNCTIONAL CHECK............................................................................................. 81
G1000 SYSTEM RETURN TO SERVICE PROCEDURE ......................................................................................83
9.1
9.2
9.3
9.4
9.5
9.6
9.7
9.8
9.9
DISPLAY TEST .................................................................................................................................................83
DISPLAY FAILURE TEST .....................................................................................................................................86
REVERSION MODE CHECK .................................................................................................................................87
AIRCRAFT BASIC EMPTY WEIGHT INITIALIZATION ................................................................................................... 88
FIELD ELEVATION INITIALIZATION ........................................................................................................................ 88
EICAS VERIFICATION .......................................................................................................................................89
ROTARY TEST .................................................................................................................................................89
G1000 BACKUP PATH TEST .............................................................................................................................. 90
MAINTENANCE RECORDS ..................................................................................................................................90
APPENDIX A ‐ GARMIN UNIT PART AND SERIAL NUMBER CROSS REFERENCE .....................................................91
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 4
TABLE OF FIGURES
FIGURE 2‐1 – GCU 475 ....................................................................................................................................................12
FIGURE 2‐2 – GDL 69A SXM ............................................................................................................................................12
FIGURE 2‐3 – GDU 1050A ...............................................................................................................................................12
FIGURE 2‐4 – GDU 1550 .................................................................................................................................................12
FIGURE 2‐5 – GMA 1360D ..............................................................................................................................................12
FIGURE 2‐6 – GTX 345R ..................................................................................................................................................12
FIGURE 2‐7 – FS 510 .......................................................................................................................................................12
FIGURE 2‐8 – G1000 NXI SYSTEM OVERVIEW ...................................................................................................................... 13
FIGURE 2‐9 – ELECTRICAL BONDING PREPARATION – NUT PLATE .............................................................................................. 15
FIGURE 2‐10 – ELECTRICAL BONDING PREPARATION – BOLT/NUT JOINT .................................................................................... 15
FIGURE 2‐11 – ELECTRICAL BONDING PREPARATION – TERMINAL LUG ....................................................................................... 15
FIGURE 3‐1, SET>ACTV DIAGRAM .....................................................................................................................................18
FIGURE 3‐2, LOSS OF COMMUNICATION ............................................................................................................................... 19
FIGURE 3‐3, CONFIGURATION STATUS ..................................................................................................................................19
FIGURE 3‐4, DATA TRANSMISSION INDICATORS ...................................................................................................................... 19
FIGURE 3‐5, GARMIN UNIT S/N LOCATION ........................................................................................................................... 24
FIGURE 3‐6, SOFTWARE/CONFIGURATION OVERVIEW ............................................................................................................. 28
FIGURE 3‐7, MFD AUX ‐ DATABASE PAGE DB TRANSFER ........................................................................................................ 40
FIGURE 5‐1, AUX – SYSTEM STATUS PAGE – ......................................................................................................................... 49
FIGURE 5‐2, SYSTEM ANNUNCIATIONS .................................................................................................................................50
FIGURE 6‐1, CONFIGURATION MODULE INSTALLATION ............................................................................................................ 59
FIGURE 7‐1, G1000 NORMAL MODE CHECK ........................................................................................................................ 65
FIGURE 7‐2, AIRCRAFT REGISTRATION ..................................................................................................................................70
FIGURE 8‐1, LOW SPEED AWARENESS BAND SYMBOLIZATION ................................................................................................... 78
FIGURE 9‐1, MFD POWER UP PAGE ....................................................................................................................................83
FIGURE 9‐2, PFD POWER‐UP SYSTEM ANNUNCIATIONS .......................................................................................................... 84
FIGURE 9‐3, PFD NORMAL OPERATION ............................................................................................................................... 85
FIGURE 9‐4, GDU REVERSIONARY MODE ............................................................................................................................. 87
FIGURE 9‐5, BASIC EMPTY WEIGHT ENTRY ............................................................................................................................ 88
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 5
1. Introduction
1.1
Content, Scope, Purpose
This document provides maintenance instructions and Instructions for Continued Airworthiness
(ICA) for the changes to the G1000 Integrated Flight Deck as installed in the Textron Aviation
Inc. Model 510 Citation Mustang. The change under STC SA01896WI upgrades the system to
the NXi configuration of the Garmin G1000 Integrated Flight Deck including the GFC700
Automatic Flight Control System (AFCS). 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 and GFC700.
Throughout this document, the GFC 700 autopilot system is included in the G1000NXi system
description and is identified separately only when needed.
1.2
Applicability
This document applies to Textron Aviation Inc. Model 510 Citation Mustang aircraft equipped
with the G1000 NXi system. All G1000NXi Model 510 aircraft are configured per General
Arrangement drawing 005-01328-01, Rev 1 or subsequent approved revision.
Modification of an aircraft by Supplemental Type Certificate (STC) SA01896WI 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. The scope of maintenance information in this document is limited to aspects
pertaining to the Garmin G1000 NXi upgrade only. For other G1000 and aircraft level
maintenance items, refer to the Textron 510 Maintenance Manual or the G1000 Cessna Citation
Mustang Line Maintenance Manual.
1.3
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 installing G1000 NXi
on Textron Aviation Inc. Model 510. Also provides an interface summary, power requirements,
and instructions on electrical bonding.
Section 3: Control and Operation
Provides brief instructions on controls and operation of the G1000 NXi system.
Section 4: Instructions for Continued Airworthiness
Provides maintenance procedures and instructions for continued airworthiness of the G1000
NXi system.
Section 5: Troubleshooting
Provides troubleshooting information to aid in diagnosing and resolving potential problems with
G1000 NXi system.
Section 6: Equipment Removal & Replacement
Gives instructions for the removal and replacement of G1000 NXi equipment.
Section 7: LRU Configuration & Testing
Gives instructions for loading software, configuring, and testing of the G1000 NXi system.
Section 8: Sub-System Functional Checks
Gives instructions for loading software and configuring the G1000 NXi system.
Section 9: G1000 System Return to Service Procedures
Specifies return-to-service procedures to be performed upon completion of maintenance of the
G1000 NXi system.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 6
1.4
Definitions/Abbreviations
ADI:
AML:
ARP:
ASTM:
CDI:
CFR:
CWS:
DDM:
DTK:
FAA:
GPS:
ICA:
ILS:
LRU:
MFD:
n/a:
NXi:
OBS:
PED:
PFD:
PFT:
SAE:
SD:
SXM:
STC:
VOR:
1.5
Attitude Director Indicator
Approved Model List
Aerospace Recommended Practice
American Society for Testing and Materials
Course Deviation Indicator
Code of Federal Regulations
Control Wheel Steering
Difference in Depth of Modulation
Desired Track
Federal Aviation Administration
Global Positioning System
Instructions for Continued Airworthiness
Instrument Landing System
Line Replaceable Unit
Multifunction Flight Display
Not Applicable
Next Generation Integrated
Omni-Bearing Selector
Personal Electronic Device
Primary Flight Display
Pre-Flight Test
Society of Automotive Engineers
Secure Digital
SiriusXM
Supplemental Type Certificate
VHF Omnidirectional Radio
Units of Measure
Unless otherwise stated, all units of measure are English units.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 7
1.6
Publications
All Garmin documents listed in Table 1-1 and Table 1-2 are available for download through the
Dealer Resource Center section of the Garmin web site. Refer to Section 1.7 for details.
The documents listed in Table 1-1 are required by this maintenance manual to perform
maintenance on the G1000 NXi system on the Textron Aviation Inc. Model 510. It is the
responsibility of the owner/operator to ensure that the latest versions of these documents are
used during operation, servicing or maintenance of the airplane. Refer to the Master Drawing
List 005-01328-00 for applicability.
Table 1-1 – Required Documents
GARMIN PUBLICATIONS
Document Number
Document Title
005-01328-00
Master Drawing List, G1000 NXi Upgrade in Textron Model 510
005-01328-01
General Arrangement, G1000 NXi Upgrade in Textron Model 510
005-01328-02
Equipment Installation, G1000 NXi Upgrade in Textron Model 510
005-01328-03
Wire Harness Routing & Install, G1000 NXi Upgrade, Textron Model 510
005-W0037-00
Wiring Diagram, G1000 NXi Upgrade, Textron Aviation Model 510
TEXTRON PUBLICATIONS
510MM
Cessna Model 510 Airplane Maintenance Manual
The documents listed in Table 1-2 are recommended to be available during the performance of
maintenance activities.
Table 1-2 –Reference Publications
GARMIN PUBLICATIONS
Document Number
Document Title
190-02450-02
Airplane Flight Manual Supplement, G1000 Integrated Avionics System and GFC 700
AFCS in Cessna Citation Mustang Model 510
190-02523-00
Cockpit Reference Guide, G1000 NXi Cessna Citation Mustang
190-02522-00
Pilot's Guide, G1000 NXi Cessna Mustang
190-00355-04
GDL 69 Series SiriusXM Satellite Radio Activation Instructions
190-00903-00
G1000 System Maintenance Manual (LJ/VLJ Aircraft)
190-00303-92
GDU 105X Installation Manual
190-00303-94
GDU 1550 Installation Manual
190-03813-00
GMA 1360 Installation Manual
190-01499-04
GTX 35R/45R Transponder TSO Installation Manual
190-00500-00
G1000 Cessna Citation Mustang Line Maintenance Manual
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 8
Table 1-3 – Other Reference Documents
Document Number
Title
AC 43.13-1B
FAA Advisory Circular, Acceptable Methods, Techniques, and Practices
– Aircraft Inspection and Repair
AC 43.13-2B
FAA Advisory Circular, Acceptable Methods, Techniques, and Practices
– Aircraft Alterations
SAE ARP1870
Aerospace Systems Electrical Bonding and Grounding for Electromagnetic
Compatibility and Safety
SAE AS4461
Assembly and Soldering Criteria for High Quality/High Reliability Soldered Wire and
Cable Termination in Aerospace Vehicles
SAE AS50881
Wiring, Aerospace Vehicle
ASTM F 2490-05
Standard Guide for Aircraft Electrical Load and Power Source Capacity Analysis
1.7
Revision and Distribution
This document is required for maintaining the continued airworthiness of the G1000 NXi system
on Textron Aviation Inc. Model 510. When this document is revised every page will be updated
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 913397-8200, 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.
1.8
Garmin Technical Support
For technical support contact, Garmin Aviation Product Support at 913-397-8200 (toll free 866739-5687) or by using the around-the-world contact information on www.flygarmin.com.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 9
2. System Description
The G1000 NXi system components described in this section are additions or updates to
existing components on the Textron Aviation inc. Model 510. This section briefly describes the
function of these components.
2.1
2.1.1
Equipment Descriptions
GCU 475
The GCU 475 controller is shown in Figure 2-1. This is an updated version of the existing GCU
475 controller. The controller is updated with improved joystick function. This is a drop-in
replacement.
2.1.2
GDL 69A SXM
The GDL 69A SXM satellite receiver is shown in Figure 2-2. The GDL 69A SXM is a data link to
utilize currently available SirusXM satellite data services. This is an update to the existing GDL
69A and is a drop-in replacement.
2.1.3
GDU 1050A
The GDU 1050A display unit is shown in Figure 2-3. The GDU 1050A is a primary flight display
(PFD) mounted in the cockpit. The GDU 1050A is an update to the existing GDU 1040A that
was originally installed. The GDU 1050A improves display quality and brightness, improves
processing time and responsiveness, and improves weight and power consumption.
2.1.4
GDU 1550
The GDU 1550 display unit is shown in Figure 2-4. The GDU 1550 is a multifunction flight
display (MFD) mounted in the cockpit. The GDU 1550 is an update to the existing GDU 1500
that was originally installed. The GDU 1550 improves display quality and brightness, improves
processing time and responsiveness, and improves weight and power consumption.
Electronic Checklist
The Electronic Checklists (ECL) function allows the user to view and interact with aircraft
checklists. The Checklist contents are displayed on the GDUs and the checklist control is
performed using the GCU 475. The Garmin Checkset tool is provided by Garmin at no charge to
the aircraft operator to generate and edit the custom checklist files which are saved in the .gcl
format.
NOTE
For the G1000 NXi update, the name of the checklist has to be saved as
“510R7AJ.gcl” for the checklist function to work.
The Checkset tool can be downloaded from the Fly.Garmin website under the Tools tab
(https://fly.garmin.com/fly-garmin/). The checklist is created or edited by the OEM/End user
without involvement from Garmin. Once the electronic checklist is created by the OEM/end user,
it is then downloaded onto an SD card and inserted into the top or bottom MFD card slot. Upon
power-up, the G1000 system checks the MFD SD cards for any checklist files and then
transfers the electronic checklist to the GDU internal memory. Once the Checklist is transferred
to the GDU, the SD card containing the checklist files can be removed and is no longer
required.
Please note that operational usage of the checklist file may require regulatory approval. The
OEM/Operator is expected to obtain the required approval.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 10
2.1.5
GMA 1360D (optional)
The GMA 1360D audio panel is shown in Figure 2-5. This unit replaces the GMA 1347D audio
panel and there are two per aircraft. The GMA 1360D brings 3D audio and Bluetooth
connectivity.
2.1.6
GTX 345R (optional)
The GTX 345R transponder is shown in Figure 2-6. The GTX 345R replaces the existing GTX
33 #2 transponder. The GTX 345R provides ADS-B Out. The GTX 345R also provides ADS-B
In for TIS-B and air-to-air traffic and FIS-B weather data to the G1000 NXi system for display to
the flight crew.
2.1.7
FS 510
The FS 510 (Flight Stream 510) wireless data card is shown in Figure 2-7. The FS 510 is an
SD card that installs into the MFD in the aircraft cockpit. The FS510 offers the addition of Wi-Fi
and Bluetooth connectivity for activities such as flight plan transfers and data output to carry-on
devices such as tablets and electronic flight bags. This data may be in the form of GPS
information, weather, aircraft traffic, or other items for flight crew use.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 11
Figure 2-1 – GCU 475
Figure 2-2 – GDL 69A SXM
Figure 2-4 – GDU 1550
Figure 2-3 – GDU 1050A
Figure 2-5 – GMA 1360D
Figure 2-6 – GTX 345R
Figure 2-7 – FS 510
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 12
2.2
System Interface Summary
The following figure provides a high-level summary of G1000 NXi on the Textron Aviation Inc.
Model 510 aircraft. Yellow blocks signify new or updated equipment.
GMC 710
(AFCS Mode Controller)
232
From GDC1
429
From GRS1
429
4
HSDB
From GDC2
HSDB
2 3
GTX 345R [2]
(ADS-B
Transponder)
GDU 1050A [1]
(Primary Flight
Display)
From GDC1
TO
GMA1/2
GDL 69A SXM
(XM/Weather 1
Datalink)
4
2
3
HSDB
2
HSDB
3
3
GDU 1550 [3]
(Multifunction
Display)
1
Diagnostics
To
#2 GIA 6W
HSDB
From GRS2
429
429
to GPS / XM
Antenna
Analog
Audio
429
HSDB
4
HSDB
2
GDU 1050A [2]
(Primary Flight
Display)
GCU 475
(FMS Controller)
232
4
1
232
232
HSDB
1
HSDB
GSD 41
(Data
Concentrator)
GWX 68
(Weather Radar)
HSDB
Digital
Bus
232
MKR
BCN
GMA 1360D
[1]
(Audio Panel)
HSDB
Audio
ADF
Audio
KHF 1050
HF Radio
Audio
TAS
Audio
Audio
Audio
Audio
DME1
Audio
Audio
GDL69A
Audio
GMA 1360D
[2]
(Audio Panel)
HSDB
Audio
HSDB
Over 232
GPS / XM COM
COM GPS
To
MFD
To
PFD1
G/S
HSDB
Over 232
Audio
To
GDL 69A SXM
To
PFD2
429
429
coupler
NAV
429
GDC 74B #1
Air Data Computer
429
232
232
429
429
coupler
GDC 74B #2
Air Data Computer
429
GMU 44
Magnetometer
232
485
GRS 77 #1
AHRS
GRS 77 #2
FADEC
LA / RA
GTX 33D [1]
(Transponder)
429
429
232
429
429
ELT
C406-N
232
429
GIA 63W [2]
GIA 63W [1]
232
GSA 81 (Pitch)
485
429
COM,
GPS,
VOR/LOC,
G/S,
Flight
Director
232
485
COM,
GPS,
VOR/LOC,
G/S,
Flight
Director
GSA 81 (Roll)
GSA 80 (Yaw)
GSA 81(Pitch Trim)
485
GEA 71 [1]
(Engine & Airframe)
485
485
GEA 71 [2]
(Engine & Airframe)
485
429
GRS 77 #2
AHRS
KN 63 DME
422
Becker ADF
232
GMU 44
Magnetometer
FADEC
LB / RB
232
232
232
485
GRS 77 #1
Suppression
Analog Audio
Analog Audio
GTX 33D [2]
(Transponder)
Suppression
Suppression
HSDB
HSDB over Ethernet
HSDB Over 232
HSDB over RS-232
HSDB Over 422
HSDB over RS-422
ARINC 429
429
485
232
717
RS-485
RS-232
New Garmin
Equipment
Standard
New Garmin
Equipment
Optional
Legacy Garmin
Equipment
Standard
Legacy Garmin
Equipment
Optional
Non-Garmin Equipment
Standard
Non-Garmin Equipment
Optional
ARINC 717
Figure 2-8 – G1000 NXi System Overview
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 13
Power Requirements
2.3
Table 2-1 below summarizes the power requirements for the LRUs installed by this STC.
Table 2-1 – Power Requirements
LRU
GCU 475
Characteristics
Max Current Draw @ 28 VDC
Specifications
0.05 A
Notes
GDL 69A SXM
Max Current Draw @ 28 VDC
0.35 A
GDU 1050A
Max Current Draw @ 28 VDC
0.9 A
At or below -15° = 1.9A
GDU 1550
Max Current Draw @ 28 VDC
0.9 A
At or below -15° = 1.9A
GMA 1360D
Max Current Draw @ 28 VDC
1.00 A
GTX 345R
Max Current Draw @ 28 VDC
0.36 A
FS 510
Max Current Draw @ 28 VDC
n/a
Powered by GDU 1550
Electrical Bonding
2.4
For the purposes of this STC, aircraft ground reference definitions vary according to airframe
type, as defined in Table 2-2. Refer to the periodic test and reconditioned resistance values
corresponding to these ground reference definitions when performing the equipment bonding
tests in Section 4.5.
The periodic test value is the value allowed during the bonding checks specified in Section 4.5.
The reconditioned value is the value allowed on initial installation or if the bond must be
reworked if the periodic test value is exceeded.
Refer to SAE ARP 1870 Section 5 when surface preparation is required to achieve electrical
bond.
Table 2-2 – Electrical Bonding
Aircraft Type
Ground Reference
Metallic Airframe
Nearby metal structure for
servos
or
Instrument panel for LRU
2.4.1
Maximum Resistance Between LRU
Equipment Chassis and Ground
Reference (mΩ)
Periodic Test
Reconditioned
30.0 for PFD1,
30 for PFD1, MFD,
MFD, PFD2, GMC
PFD2, GMC
2.5 for GMA
5 for GMA 1360D
1360D (if installed)
(if installed) or GTX
or GTX 345R (if
345R (if installed)
installed)
Consideration for Untreated or Bare Dissimilar Metals
The correct material finish is important when mating untreated or bare dissimilar metals.
Materials should be galvanically compatible. When corrosion protection is removed to make an
electrical bond any exposed area after the bond is completed should be protected again.
Additional guidance can be found in SAE ARP 1870 Section 5. Typical electrical bonding
preparation examples are shown in Figure 2-9, Figure 2-10, and Figure 2-11.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 14
Figure 2-9 – Electrical Bonding Preparation – Nut Plate
Figure 2-10 – Electrical Bonding Preparation – Bolt/Nut Joint
Figure 2-11 – Electrical Bonding Preparation – Terminal Lug
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 15
2.4.2
Preparation of Aluminum Surfaces
The following general procedure is recommended to prepare an aluminum surface for proper
electrical bonding.
1. Clean grounding location with solvent.
2. Remove non-conductive films or coatings from the grounding location.
3. Apply a chemical conversion coat such as Alodine 1200 to the bare metal.
4. Once the chemical conversion coat is dry, clean the area.
5. Install bonding equipment at grounding location.
6. After bond is complete, if any films or coatings were removed from the surface, reapply a
suitable film or coating to the surrounding area within 24 hours.
After satisfactory electrical bond is achieved, when it has been necessary to remove any highresistance protective coating, the area from which the coating has been removed should be
refinished with the same finish as is on the rest of the part within 24 hours. In cases where the
parts come in with certain areas spot-faced, or if there is no finish on the part (bare metal), apply
conformal coating over the bond joint and hardware per MIL-I-46058 or clear lacquer per TT-L20A to facilitate future inspection. Refer to the model specific Aircraft Maintenance Manual or
Standard Practices Manual for surface protection requirements applicable to affected areas.
The correct material finish is important when mating untreated or bare dissimilar metals. They
should be galvanically compatible. When corrosion protection is removed to make an electrical
bond, any exposed area after the bond is completed should be protected again. Additional
guidance can be found in SAE ARP 1870 Section 5.
For a more detailed procedure, refer to SAE ARP 1870 Sections 5.1 and 5.5.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 16
3. Control and Operation
3.1
Configuration Mode Overview
Throughout this document, references are made to the PFD1, PFD2, 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 NXi sub-systems.
Troubleshooting and diagnostics information can be viewed in this mode.
To start the G1000 NXi system in configuration mode, follow these steps;
1. Apply power to the G1000 NXi system by applying aircraft EXT power, set the
AVIONICS MASTER PWR and BATT switches to ON.
2. Pull the MFD (PRIM and SEC), PFD1 (PRIM and SEC), and PFD2 (PRIM and SEC)
circuit breakers.
3. Press and hold the ENT key on PFD 2 (co-pilot’s side) while applying power using the
PFD2 PRIM circuit breaker.
4. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of
PFD2.
5. Press and hold the far right softkey on the MFD while applying power using the MFD
PRIM circuit breaker. Note that the ENT key on the GCU 475 controller may be used
after initial software loads.
6. Release the softkey after ‘INITIALIZING SYSTEM’ appears in the upper left corner of the
MFD.
7. Press and hold the ENT key on PFD1 (pilot’s side) while applying power using the PFD1
PRIM circuit breaker.
8. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of
PFD1.
IMPORTANT
The 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. Most protected page content is viewable to allow system
awareness for troubleshooting.
NOTE
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.
3.1.1
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.
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Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
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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).

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
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 18
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).
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
3.1.2
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
3.1.3
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
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 19
3.1.4
Configuration Mode Navigation
Using the FMS knob, 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
System Page Group
1. System Status
7. Transaction Log
13. System Data Path
Configuration
2. Time Configuration
8. Aircraft Configuration
14. System Setup
3. Lighting Configuration
9. File Manager
15. Manifest Configuration
4. System Audio
10. Diagnostics Terminal
16. Log Utilities
5. System Upload
11. OEM Diagnostics
17. Configuration Manager
6. LRU Replacement
12. System 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
14. Connext Connections
5. CDU Calibration
10. DAT Configuration
GIA 63W Page Group
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
2. GEA Status Page
3. GEA Configuration
GEA 71 Page Group
1. Engine Configuration
GTX Page Group*
1. Serial Configuration
2. Transponder Configuration
GTX 3X5 Page Group*
1. Transponder Airframe Config
2. Transponder Wiring Config
Transponder Diagnostics
2. GRS / GMU Calibration
3. GRS Flight Data Log**
GRS Page Group
1. Inputs Configuration
ADC Page Group
1. ADC Configuration
2. GDC Configuration***
GFC Page Group
1. GFC Configuration
2. GFC Status
GMA 1347D Page Group
1. GMA Configuration
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 20
GMA X36X Page Group
1. GMA Discrete In
4. GMA Marker
7. GMA Options
2. GMA Discrete Out
5. GMA Misc
8.GMA Squelch
3. GMA Fast Volume
Configuration
6. GMA Noise
9. GMA Status
10. GMA Volume
GDL Page Group
1. GDL 69 Configuration
3. GDL 59 Configuration*
2. GDL 59 Status*
4. GSR 56 Configuration*
RMT Page Group
1. Remote Controller Status
GWX Page Group
1. GWX Configuration
GRA Page Group
1. GRA Configuration
CAL Page Group
1. Fuel Tank Calibration
3. HSCM Calibration
2. Flaps & Trim Calibration
4. DAT Calibration
* Appears only if option is installed.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 21
G1000 System Software Information
3.2
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.
3.2.1
G1000 Software Image
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. Approved software loader cards may be
purchased from Garmin. Refer to the General Arrangement drawing for the part number.
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.
NOTE
Only SanDisk brand SD cards are recommended for use with the G1000
system. Other brand cards have not been tested by Garmin.
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 Sections 5, 6 and 7 before
attempting to use the software loader cards.
3.2.2
Loader Card
Obtain the software loader SD card, Garmin Part Number, 010-00435-41. This SD card contains
the loader image for use in the PFD1 top slot.
3.2.3
Software Files
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 PFD1 System Upload page in configuration mode.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 22
Configuration Mode
3.3
1. Refer to Section 3.1 for the procedure to start the G1000 NXi system in Configuration
mode,
NOTE
If a software loader card is inserted in the top slot of the display before it is
powered on, the display will automatically enter configuration mode and it
is not needed to press and hold a softkey at power-on.
G1000 Hardware/Software Compatibility Check
3.4
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.
Equipment Verification (Third Party/Optional Equipment Documentation)
3.5
Use the configuration/software checklist in Section 3.6 to determine what configuration software
files to load for the aircraft installation. It is extremely important to know exactly what equipment
the aircraft is equipped with and how it is connected before loading any files. Loading the
incorrect files could lead to longer down time and unplanned removal of equipment.

Garmin optional equipment (i.e. GTX 33 or GTX 3X5 transponder, etc.). Section 3.5.1
helps find which units are installed without a physical inspection.

Third party avionics equipment interfaced to G1000 (ADF, DME, non-Garmin traffic
systems, etc.). To determine if the third-party equipment is installed, check the circuit
breaker panel for circuit breakers for the units, and check for G1000 controls for the
third-party devices.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 23
3.5.1
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 PFD1 System
Status page in Config mode. This 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 3-5, Garmin Unit S/N Location
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 24
3.5.2
Aircraft Configuration Survey
IMPORTANT
Verify these items prior to maintenance.
1. Apply ground external power the aircraft. On the pilot’s side main DC electrical panel,
select BATT master switch to ON, then select the AVN PWR switch to ON.
2. Allow G1000 NXi displays to initialize.
3. On the MFD power-up page, record the System Software version shown in the upper
right corner of the display here:
System Software Version: __________________
4. Acknowledge the MFD power-up page by pressing the right-most softkey, then use the
GCU 475 FMS knob and navigate to the Aux - System Status page.
5. Record the G1000 System ID shown in the upper right corner of the display here:
G1000 NXi System ID: __________________
6. On the MFD EICAS, record the left and right fuel quantity indications here:
Left Fuel Tank:______________
Right Fuel Tank:______________
7. On the pilot’s side CB panel, open the PFD1 PRIM circuit breaker. On the copilot’s side
CB panel, open the PFD1 SEC circuit breaker.
8. Press and hold PFD1’s ENT key while closing the PFD1 PRIM circuit breaker. When the
white text ‘Initializing System…’ appears, release the ENT key on PFD1 to start the
display in configuration mode.
9. Use the FMS knob to navigate to the CAL page group then select the AIRFRAME
CALIBRATION page.
10. Record Aileron & Rudder Trim Calibration Offset.
Aileron Trim Offset: __________________
Rudder Trim Offset: __________________
11. Use the FMS knob to navigate back to the SYSTEM page group.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 25
Optional Equipment Survey
Cessna offered several factory equipment options during the span of Citation Mustang
production. Conduct an options equipment survey and record the installed equipment here:
 Bendix/King KTA 870 TAS
 Becker ADF
 Honeywell KN63 DME
 Bendix/King KHF 1050 HF Radio
 L3 FA2100 CVDR
IMPORTANT
At this time the G1000 NXi STC does not support the factory L3 FA2100
CVDR option. The G1000 NXi upgrade may have been performed with the
understanding that the CVDR will be inoperative.
GIA 63W Hardware P/N Survey
Review and record each GIA 63W’s hardware part number and mod status here:
GIA63W #1 P/N:_____________________ MOD: ____
GIA63W #2 P/N:_____________________ MOD: ____
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 26
3.6
Configuration Checklist
This sheet should be completed and
maintained with the aircraft permanent
records.
Date:
Aircraft
Registration:
Aircraft Serial
#:
Unlock Card Options
(Multiple selections possible)




TAWS-B, P/N 010-00330-51
ChartView, P/N 010-00330-50
Synthetic Vision, P/N 010-00330-55.
XM For Cockpit Enablement,
P/N 010-00435-E1.
NOTE: 010-00435-E1 is not required if
installing optional GMA 1360D, otherwise
RETAIN and re-use for GMA 1347D.
Loader Card
Version:
Mustang Baseline
(Multiple Selections Possible)
Cessna Mustang Base Configuration
Baseline GMA 1347
Baseline GMA 1360
Mustang Baseline - Dual GTX33D
Transponders
 Mustang Baseline - GTX33D with
GTX345Rs




Mustang Options
(Multiple selections possible)
 Cessna Mustang KTA870 TAS Legacy
Option
 Cessna Mustang KTA870 TAS
GTX345R Option
 Cessna Mustang Becker ADF Option
 Enable Flightstream 510
 Cessna Mustang KN63 DME Option
 Cessna Mustang KHF1050 HF Option
 Cessna Mustang GA57 Antenna
 Cessna Mustang Chart Disable
 Cessna Mustang Pathways Disable
 Cessna Mustang Pre-S/N -0380 Wiring
(No TCAS II)
 Mustang - GDL69A Legacy
 Mustang - GDL69A SXM
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Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 27
3.7
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. Sections of this manual where software is required to be reloaded
will 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.
GDU 1050A PFDs / GDU 1550 MFD Software Load
Software is first loaded to the MFD and PFDs. From the factory, G1000 units do
not contain useable software or configuration settings. Load software to PFD2
first then MFD and finally to PFD1.
G1000 System Upload Selection
After software is loaded to the MFD and PFDs, the displays should be placed in
configuration mode. Using PFD1, the technician goes to the System Upload
page. From the System Upload page, software files are selected to create an
automated profile to load. Once all desired files are checked, the G1000
automatically loads the selected files in the correct sequence to the LRUs.
G1000 System Software Verification
After software is loaded to the system, the technician verifies that each LRU
reports the correct version and software part number.
G1000 System Configuration Upload Selection
Following G1000 system software upload and verification, the aircraft specific
configuration files, as defined in the general arrangement drawing are loaded.
The aircraft general arrangement drawing will define the configuration files
appropriate to the specific aircraft serial number, STC modifications and
applicable AFMS.
G1000 Configuration Verification
After system configuration files are loaded, the technician verifies that the
correct configuration on the Airframe Configuration page.
Figure 3-6, Software/Configuration Overview
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 28
System Software and Configuration Load
3.8
3.8.1
System Power Up
Apply power to the G1000 NXi system by connecting external power to the aircraft to energize
the aircraft and avionics electrical busses.
IMPORTANT
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
NXi SYSTEM.
Power loss during a software update may cause an LRU to become corrupted and
unresponsive requiring replacement. Remove power only when told to do so in the procedure.
3.8.2
PFD1 Software Load
1. Open the MFD PRIM, MFD SEC, PFD 1 PRIM, PFD 1 SEC, PFD 2 PRIM, and PFD2
SEC circuit breakers.
2. Remove Garmin database cards from bottom slots of PFD 1, MFD, and PFD 2 if
present.
3. Insert the software loader card into PFD 1 top card slot.
4. Start the MFD and PFD 2 in configuration mode by pressing and holding the ENT key or
softkey #12 when closing the ‘PRIM’ circuit breakers. Release the key when the words
“INITIALIZING SYSTEM” appear on the screen.
5. Close the PFD 1 PRIM circuit breaker (the software loader card will force the PFD into
configuration mode, so there is no need to hold any key).
6. When the “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt appears on PFD 1,
press the YES softkey.
7. After the new GDU software is loaded to PFD 1, a “DO YOU WANT TO UPDATE THE
SPLASH SCREEN?” prompt will appear.
8. Press the YES softkey.
9. When complete, PFD 1 restarts in configuration mode displaying the “System Upload”
page. When complete, leave PFD 1 on with the loader card remaining in the top card
slot.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 29
3.8.3
Mustang Baseline Software and Configuration Load
IMPORTANT
If the aircraft being maintained 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.
As a general rule, all displays should be in the same mode
(configuration or normal) unless instructed otherwise.
When loading software, follow the order of software and
configuration loading Sections. Do not skip or rearrange
steps in the Sections.
Do not operate or turn off MFD and/or PFDs 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 at Step 2 in this Section.
1. Ensure all avionics circuit breakers except for PFD 1 SEC are closed and the G1000 NXi
system is fully powered. The PFD 1 PRIM circuit breaker should be used throughout the
software load procedure to cycle power on PFD 1 when required.
2. On PFD 1, go to the SYSTEM UPLOAD page using the small FMS knob.
3. Push in the PFD 1 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
“Mustang Baseline” in the drop-down menu and press the ENT key to select it.
4. Once “Mustang Baseline” is selected, the cursor moves to the ITEM window. Rotate
the small FMS knob to activate the drop-down menu. Highlight ‘Cessna Mustang Base
Configuration’, then press the ENT key to select it. The PRODUCT field will then
populate.
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Revision 1
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NOTES
The PRODUCT window displays information regarding each G1000 NXi
LRU. The LRU column depicts the reported software version of the LRU
(may be blank if PFD 1 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. 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.
5. Press the Load softkey.
6. 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.
7. Press the ENT key to acknowledge the “Upload Complete” box.
3.8.4
Audio Panel Selection
Follow this procedure to configure the audio panel type.
1. Move the cursor to the Group field and rotate FMS inner knob to display drop down
menu and select the ‘Mustang Baseline’ item and press ENT to select it.
2. The cursor should automatically move to the ITEM window. Rotate the small FMS knob
to display drop down menu:
a. If legacy GMA 1347D audio panels remain installed, highlight
“Baseline GMA1347” and press the ENT key to select it.
b. If new GMA 1360D audio panels are installed, highlight ‘Baseline GMA1360’ and
press the ENT key to select it.
3. Press the Load softkey.
4. 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.
5. Press the ENT key to acknowledge the “Upload Complete” box.
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3.8.5
Transponder Selection
Follow this procedure to configure the transponder combination installed in the aircraft.
1. Move the cursor to the Group field and rotate FMS inner knob to display drop down
menu and select the ‘Mustang Baseline’ item and press ENT to select it.
2. The cursor should automatically move to the ITEM window. Rotate the small FMS knob
to display drop down menu:
a. If legacy dual GTX 33D transponders remain installed, highlight “Mustang –
Dual GTX33D Transponders” and press the ENT key to select it.
b. If the optional #2 GTX 345R transponder unit is installed, highlight ‘Mustang GTX33D with GTX345R’ and press the ENT key to select it.
3. Press the Load softkey.
4. 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.
5. Press the ENT key to acknowledge the “Upload Complete” box.
3.8.6
GDL 69 Selection
Follow this procedure to configure GDL 69 type installed in the aircraft.
1. Move the cursor to the Group field and rotate FMS inner knob to display drop down
menu and select the ‘Options’ item and press ENT to select it.
2. The cursor should automatically move to the ITEM window. Rotate the small FMS knob
to display drop down menu:
a. If legacy GDL 69A XM unit remains installed, highlight “Mustang - GDL69A
Legacy” and press the ENT key to select it.
b. If new GDL 69A SXM unit is installed, highlight ‘Mustang - GDL69A SXM’ and
press the ENT key to select it.
3. Press the Load softkey.
4. 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.
5. Press the ENT key to acknowledge the “Upload Complete” box.
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3.8.7
Cessna Mustang Pre-S/N 510-0380 Wiring
IMPORTANT
If the aircraft under maintenance is within the serial number range
510-0001 through 510-0379, this option must be loaded.
Follow this procedure to configure pre-S/N 510-0380 wiring option in the aircraft.
1. Move the cursor to the Group field and rotate FMS inner knob to display drop down
menu and select the ‘Options’ item and press ENT to select it.
2. The cursor should automatically move to the ITEM window. Rotate the small FMS knob
to display drop down menu and highlight ‘Cessna Mustang Pre-S/N 510-0380 Wiring
(No TCAS II)’ and press the ENT key to select it.
3. Press the Load softkey.
4. 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.
5. Press the ENT key to acknowledge the “Upload Complete” box.
3.8.8
Cessna Mustang GA57 Antenna
IMPORTANT
If the aircraft under maintenance is within the Serial Number range 5100003 through 510-0040 and is equipped with the Garmin GA57 GPS/XM
antenna, this option must be loaded.
Follow this procedure to configure the appropriate gain for aircraft equipped with the GA57
GPS/XM combo antenna:
1. Move the cursor to the Group field and rotate FMS inner knob to display drop down
menu and select the ‘Options’ item and press ENT to select it.
2. The cursor should automatically move to the ITEM window. Rotate the small FMS knob
to display drop down menu and highlight ‘Cessna Mustang GA57 Antenna’ and press
the ENT key to select it.
3. Press the Load softkey.
4. 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.
5. Press the ENT key to acknowledge the “Upload Complete” box.
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3.8.9
Cessna Mustang KTA870 TAS Option
If the aircraft under maintenance has a Bendix/King KTA870 TAS system installed, follow these
steps to enable this interface.
1. Move the cursor to the Group field and rotate FMS inner knob to display drop down
menu and select the ‘Options’ item and press ENT to select it.
2. The cursor should automatically move to the ITEM window. Rotate the small FMS knob
to display drop down menu:
a. If dual GTX 33D transponders are installed, highlight ‘Cessna Mustang KTA870
TAS Legacy Option’ and press the ENT key to select it.
b. If the optional GTX 345R transponder has been installed, highlight ‘Cessna
Mustang KTA870 TAS GTX345R Option’ and press the ENT key to select it.
3. Press the Load softkey.
4. 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.
5. Press the ENT key to acknowledge the “Upload Complete” box.
3.8.10
Cessna Mustang Becker ADF Option
If the aircraft under maintenance has a Becker ADF system installed, follow these steps to
enable this interface.
1. Move the cursor to the Group field and rotate FMS inner knob to display drop down
menu and select the ‘Options’ item and press ENT to select it.
2. The cursor should automatically move to the ITEM window. Rotate the small FMS knob
to display drop down menu and highlight ‘Cessna Mustang Becker ADF Option’ and
press the ENT key to select it.
3. Press the Load softkey.
4. 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.
5. Press the ENT key to acknowledge the “Upload Complete” box.
3.8.11
Cessna Mustang KN63 DME Option
If the aircraft under maintenance has a Honeywell KN63 DME system installed, follow these
steps to enable this interface.
1. Move the cursor to the Group field and rotate FMS inner knob to display drop down
menu and select the ‘Options’ item and press ENT to select it.
2. The cursor should automatically move to the ITEM window. Rotate the small FMS knob
to display drop down menu and highlight ‘Cessna Mustang KN63 DME Option’ and
press the ENT key to select it.
3. Press the Load softkey.
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4. 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.
5. Press the ENT key to acknowledge the “Upload Complete” box.
3.8.12
Reserved
3.8.13
Cessna Mustang KHF1050 HF Option
If the aircraft under maintenance has a Honeywell KHF-1050 radio option installed, follow these
steps to enable this interface.
1. Move the cursor to the Group field and rotate FMS inner knob to display drop down
menu and select the ‘Options’ item and press ENT to select it.
2. The cursor should automatically move to the ITEM window. Rotate the small FMS knob
to display drop down menu and highlight ‘Cessna Mustang KHF1050 HF Option’ and
press the ENT key to select it.
3. Press the Load softkey.
4. 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.
5. Press the ENT key to acknowledge the “Upload Complete” box.
3.8.14
Garmin Flight Stream 510 Option
If the Flight Stream 510 was installed with the G1000 NXi upgrade, follow these steps to enable
this interface.
1. Move the cursor to the Group field and rotate FMS inner knob to display drop down
menu and select the ‘Options’ item and press ENT to select it.
2. The cursor should automatically move to the ITEM window. Rotate the small FMS knob
to display drop down menu and highlight ‘Enable Flightstream 510’ and press the ENT
key to select it.
3. Press the Load softkey.
4. 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.
5. Press the ENT key to acknowledge the “Upload Complete” box.
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3.8.15
Aircraft Registration Number Entry
1. On PFD 1, select the AIRCRAFT CONFIGURATION page.
2. Activate the cursor to select the ”AIRCRAFT REGISTRATION” field and enter the
aircraft’s tail number. Press the ENT key to save.
3. For non-US “N” number aircraft registrations, rotate the large FMS knob to select the
“ICAO ADDRESS” and enter the aircraft’s 24 bit ICAO address. Press the ENT key to
save. US “N” number aircraft registrations are automatically decoded and entered in this
field, do not change the number.
4. If applicable, rotate the large FMS knob to select the ”ICAO REGION” field and select
the appropriate ICAO region. Press the ENT key to save.
5. If applicable, rotate the large FMS knob to select the ”DOMAIN IDENTIFIER” field and
enter the number. Press the ENT key to save. Otherwise, leave blank.
6. 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 ENT key to
save.
7. Press the SET GTX1 softkey and acknowledge the prompt by pressing the ENT key.
8. Press the SET GTX2 softkey and acknowledge the prompt by pressing the ENT key.
9. Deactivate the cursor.
IF the optional GTX 345R transponder has been installed, continue to next step. Otherwise
continue to next section.
10. Rotate large FMS knob to select “GTX 3X5” configuration page group.
11. On the Transponder Airframe Configuration page, verify the GTX 2 box at the top of
the page is green and the tail number, ICAO address, and VFR code that were entered
previously are correct.
3.9
Airframe Trim Calibration Confirmation
1. On PFD 1, use the FMS knob to select the AIRCRAFT CALIBRATION page, located in
the CAL page group.
2. Review and compare the AILERON TRIM and RUDDER TRIM correction values to what
was recorded prior to the G1000 NXi modification (see Section 3.5.2).
3. If the values do not match, re-enter the previously recorded trim correction values using
the FMS knob, pressing the ENT key after each entry is made.
NOTE
If the trim offset values from the legacy G1000 system were not recorded
and not retained by the system, technician must re-establish the correct
offset per the Model 510 AMM, Chapter 34-60-00 Procedure 6 “GDU 1500
MFD Aileron and Rudder Trim Tab Pointer Adjustment”
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.
3.10 Feature Enablement
This section describes how to unlock or enable optional features. The installer will only load the
Sections for the required features. For installing all feature enable cards, PFD 1, PFD 2, and
the MFD must be in configuration mode.
The G1000 NXi 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’.
NOTE
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.
3.10.1
ChartView Feature Enablement
Follow this procedure to activate the ChartView display feature.
NOTE
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
1. Insert the ChartView Enablement card into the top slot of PFD 1 and power on PFD 1 in
configuration mode.
2. On PFD 1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “Configuration Files” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “Enable ChartView” and
press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:

Green “PASS” in the Configuration column for each item loaded.

“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD 1 circuit breaker and remove the ChartView enablement card.
3.10.2
Reserved
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3.10.3
TAWS-B Feature Enablement
Follow this procedure to enable the TAWS Class B feature.
1. Insert the TAWS-B Enablement card in the top slot of PFD 1 and power on PFD 1 in
configuration mode.
2. On PFD 1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “Configuration Files” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “Enable TAWS-B” and
press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:

Green “PASS” in the Configuration column for each item loaded.

“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD 1 circuit breaker and remove the TAWS-B enablement card.
3.10.4
Synthetic Vision System Enablement
Follow this procedure to enable the Synthetic Vision feature.
1. Insert the SVS Enablement card in the top slot of PFD 1, power on PFD 1 in
configuration mode.
2. On PFD 1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “Configuration Files” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “Enable SVS Dual PFD”
and press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:

Green “PASS” in the Configuration column for each item loaded.

“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD 1 circuit breaker and remove SVS enablement card.
3.10.5
Reserved
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3.11 Configuration Manager
1. On PFD 1, rotate the large FMS knob to select “SYSTEM” configuration page group.
2. Rotate the small FMS knob to select Configuration Manager page.
3. Press the softkey labelled CNFM CFG.
4. Highlight OK in the popup window and press the ENT key to select.
5. Open the MFD PRIM, MFD SEC, PFD 1 PRIM, PFD 1 SEC, PFD 2 PRIM, and PFD 2
SEC circuit breakers.
3.12 Clearing Default User Settings
1. While holding the CLR button on PFD 1, close PFD 1 PRIM circuit breaker.
2. When prompted to clear user settings, select the YES softkey.
3. When user settings have been cleared appears on the screen, open PFD 1 PRIM circuit
breaker.
4. Wait ten seconds, then while holding the second key from the right side (#11 softkey) of
the MFD, close the MFD PRIM circuit breaker.
5. When prompted to clear user settings, select the YES softkey.
6. When user settings have been cleared appears on the screen, open MFD PRIM circuit
breaker.
7. Wait ten seconds, then while holding the CLR button on PFD 2, close the PFD 2 PRIM
circuit breaker.
8. When prompted to clear user settings, select the YES softkey.
9. When user settings have been cleared appears on the screen, open PFD 2 PRIM circuit
breaker.
10. Remove power from the aircraft.
11. Close all open circuit breakers.
3.13 Database Loading
NOTE
It is not recommended to alternate between methods when updating
avionics databases. For example, if Flight Stream 510 is used for reoccurring database updates, reverting to the SD card method may introduce
conflicting database versions when the Flight Stream 510 card is installed.
If a technician desires to use the SD card method, any databases on the
Flight Stream 510 should first be deleted by formatting the card. A USB card
reader may be used to communicate with the FS 510. Garmin P/N 01300203-03 is a recommended USB card reader for this purpose
3.13.1
Follow this procedure to load the databases using the SD card method.
1. The following databases are available for purchase and download from fly.garmin.com
or by obtaining Garmin SD Card P/N 010-00474-50 which contains a selection of the
databases below. Databases with an (*) asterisk are included on the P/N 010-00474-50
SD card. If obtaining the databases from fly.garmin.com and using SD cards smaller
than 16GB to transfer the databases to the G1000 NXi system, you may need to use
multiple cards (or reuse one) to load all the databases.
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a. Terrain* (Worldwide, 4.9 Arc Second, TDBs2 format) (required)
b. Obstacle* (US/Canada/Europe, OBD2 format) (required)
c. AOPA Airport Directory* (US) (optional)
d. AC-U-KWIK Airport Directory (optional)
e. SafeTaxi* (US*, North America, Canada, Europe, Full Coverage) (optional)
f.
Basemap* (Worldwide) (optional)
g. Garmin FliteCharts* (US*, Canada, Europe) (optional)
h. Jeppesen ChartView (optional)
i.
IFR/VFR Charts* (US) (optional)
j.
Navigation (required)
2. With the displays off, insert the SD card into the MFD top slot.
3. Apply power to the PFD 1, MFD, and PFD 2.
4. On the MFD, database verification messages may appear. If so, follow the on-screen
instructions to continue.
5. 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.
Figure 3-7, MFD Aux - Database Page DB Transfer
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6. 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 engines
are not running and the aircraft is determined to be on-ground, 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 1, MFD, and PFD 2.
7. Remove the database update card from the top slot of the MFD.
8. Turn ON the displays.
9. The displays may state they are verifying databases at power-up. If so, follow the onscreen instructions to continue.
10. 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 GCU 475 controller to turn on the cursor.
b. Turn the FMS knob to highlight the database to transfer to the Active column.
c. Press the ENT key on the GCU 475 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.
3.14 Configuration of Navigation Map for Traffic System
1. With the MFD in normal mode, use the GCU 475 FMS knob to select the Navigation
Map page then press the MENU key to display the PAGE MENU.
2. Turn the small right knob to select or verify selected ‘Map Settings’ and press the ENT
key.
3. Verify the flashing cursor highlights the GROUP field.
4. Turn the GCU 475 small FMS knob to select Traffic and press ENT.
5. If not already selected, use the GCU 475 FMS knob to make the following selections:

Traffic – On

Traffic Mode – All Traffic

Traffic Symbols – 150NM

Traffic Labels – On 150NM
6. Return to the Map Page by pressing the GCU 475 FMS knob or pressing and holding
the CLR key. Deactivate cursor.
3.15 Flight Stream 510 Firmware Review
If the optional Flight Stream 510 is installed, technician must review the reported Flight Stream
firmware version and compare it to the version approved by the STC.
Reference the STC General Arrangement drawing to find the approved firmware release (see
Table 1-1).
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NOTE
This STC approves a major release of Flight Stream 510 and allows for
periodic minor software updates to account for low-level driver and
Bluetooth interface updates. Example – If the STC data specifies version
2.3( ) as the approved version, all minor releases within the 2.3X series are
approved.
At the time of installation, minor firmware updates may be available. The
technician may check for updates to the firmware by following this
procedure.
CAUTION
The technician must review the Flight Stream 510 version approved by this
STC and ensure a newer major release is not utilized. Otherwise,
incompatibility with the GDU display software may result.
NOTE
Note that Flight Stream firmware update requires a device running iOS
8.1 or later 
iPhone 5 and newer

iPad 3 and newer

iPad Air and newer

iPad Mini with Retina and newer
It also requires that the above device to run Garmin Pilot App v7.1 or
higher.
Firmware update is not supported via Android devices at the time of
writing this document.
1. Download Garmin Pilot on the iOS device
2. Create an account in the Garmin Pilot App. If an account exists already, log in to the
account.
3. Contact Garmin Aviation Product Support - https://fly.garmin.com/fly-garmin/support/
- identify yourself as a Garmin Dealer, and request access to update Flight Stream
Firmware.
4. After Support grants access, refresh Subscription page in Garmin Pilot (swipe down
across page to refresh)
5. Garmin Pilot will show a "Dealer Mode" subscription.
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
Section 7 gives configuration and testing instructions to be accomplished if G1000 NXi
equipment or parts are reinstalled 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.
4.2.2
Required Tools
The following tools are needed to perform maintenance tasks on G1000 NXi equipment:

3/32” Hex tool

Calibrated VHF NAV/COM/ILS 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

Standard sockets & wrenches
4.2.3
Special Tools
The following tools may be needed to perform maintenance tasks on G1000 NXi equipment
and/or installation:

No special tools are required.
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4.3
Maintenance Intervals
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 to be in flight time as well as calendar months, the
first interval reached should be used as the limit.
NOTE
The information in this section only pertains to equipment and systems installed via this STC.
Overall information regarding avionics maintenance intervals on Textron 510 is still furnished by
Textron Aviation in the support of this aircraft.
Those inspections that are based on flight time or calendar elapsed time or cycles shall have
specific intervals stated in Table 4-1.
Table 4-1 – Maintenance Intervals
Item
GDU 1050A PFD
(Qty 2)
Manual
Section No.
Interval
Removal & Replacement
6.1
On Condition
Removal & Replacement
6.2
On Condition
Removal & Replacement
6.3
On Condition
7.4.4
24 Calendar Months
Description/Procedure
GDU 1550 MFD
GMA 1360D Audio
Panel (Qty 2)
GTX 345R
Transponder
Special Inspection - Perform GTX 345R test.
GDL 69A SXM
Satellite Receiver
Removal & Replacement
6.4
On Condition
GCU 475 Controller
Removal & Replacement
6.5
On Condition
G1000 Alerts
Check for and troubleshoot any alerts
provided in the alert window per the
referenced manual section.
5
On Condition
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4.4
Visual Inspection
Perform a visual inspection in accordance with requirements in
Table 4-2. Check for corrosion, damage, or other defects of the LRUs on the Left and Right
sides. Replace any damaged parts as required. Inspection may require the temporary removal
of a unit or units to gain access to connectors. Follow guidance in Section 6 for equipment
removal and replacement. Refer to the aircraft manufacturer service or maintenance manual
for instructions on access panel locations.
Table 4-2 – Nose and Cabin Visual Inspection Procedure
Item
Description/Procedure
Initials
Gain access to behind the instrument panel by removing the PFDs and MFD (see below). Gain access to the nose
compartment by following instructions in the Textron 510 Maintenance Manual.
GCU 475
Controller
Inspect the GCU in the cockpit pedestal for any visual damage to the bezels
including buttons and control knobs.
Remove the GCU as described in Section 6.
Inspect the mounting surface and connector for corrosion, heavy oxidation, or
other damage. Check the integrity of the SHIELD BLOCK ground attachments
to the harness connector assembly as well as the integrity of the individual
shields and their attachment.
Reinstall the GCU as described in Section 6.
GDL 69A SXM
Satellite Receiver
Access the GDL 69A unit in the nose of the aircraft as described in the Model
510 Maintenance Manual. Inspect the GDL 69A unit, rack, and connectors for
corrosion or other defects. Check the integrity of the SHIELD BLOCK ground
attachments to the harness connector assembly as well as the integrity of the
individual shields and their attachment.
GDU 1050A PFD
(Qty 2) & GDU
1550 MFD
Inspect the PFDs and MFD for any visual damage to the display screens or
bezels including buttons and control knobs.
Remove the MFD and PFDs from the instrument panel as described in Section
6.
Inspect the mounting surface and connector for corrosion, heavy oxidation, or
other damage. Check the integrity of the SHIELD BLOCK ground attachments
to the harness connector assembly as well as the integrity of the individual
shields and their attachment.
Do not reinstall GDUs at this time. GDU cutouts provide access for visual
inspections below.
GMA 1360D
Audio Panel
(Qty 2)
Inspect the GMA 1360D unit (including face of unit), rack and connectors for
corrosion or other defects. Check the integrity of the SHIELD BLOCK ground
attachments to the harness connector assembly as well as the integrity of the
individual shields and their attachment.
GTX 345R
Inspect the GTX unit, rack, and connectors for corrosion or other defects. Check
the integrity of the shield block ground attachments to the harness connector
assembly as well as the integrity of the individual shields and their attachment.
Reinstall the MFD and PFDs as described in Section 6 and close access to the nose compartment following
instructions in the Textron 510 Maintenance Manual.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 46
Electrical Bonding Test
4.5
The following bonding tests are provided for aircraft that have a G1000 NXi system installed.
These bonding tests are a requirement beyond any that may be given in the aircraft
maintenance manual section above. These tests are specific to hardware added per STC
SA01896WI.
4.5.1
Requirements
All G1000 avionics equipment must be installed. Gain access for the procedure listed below in
Section 4.5.3 as required and in accordance with the Textron 510 Maintenance Manual. It is
recommended that these tests are conducted after visual inspection of the zone to minimize
access requirements.
4.5.2
Test Equipment
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.)
NOTE
When a 1A current is used all the millivolt readings are the same as mΩ,
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. .
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 47
4.5.3
Electrical Bonding Procedure
Using the measurement method in Section 4.5.2, record the bonding measurement for the
following equipment. Some equipment in the list is optional and may not be installed.
Ensure that the measurements do not exceed the values shown in Table 2-2. If the values
exceed those listed, perform the reconditioning procedure in Section 2.4
Pilot Compartment







Metal case of PFD 1: __________ mΩ
Metal case of PFD 2: __________ mΩ
Metal case of MFD: __________ mΩ
Metal case of GMA 1360D #1: __________ mΩ
Metal case of GMA 1360D #2: __________ mΩ
Metal case of GCU 475: __________ mΩ
Metal case of GTX 345R #2: __________ mΩ
Nose Compartment

GDL 69A SXM top: __________ mΩ
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 48
5. Troubleshooting
This section provides information to assist with troubleshooting of the G1000 NXi system as
installed per STC SA01896WI.
The scope of maintenance information in this document is limited to aspects pertaining to the
Garmin G1000 NXi upgrade only. For other G1000 and aircraft level maintenance items, refer to
the Textron 510 Maintenance Manual or the G1000 Cessna Citation Mustang Line Maintenance
Manual.
See the G1000 NXi system Configuration Log retained in the aircraft permanent records for a
list of the system configuration data. When troubleshooting the G1000 NXi system refer to the
interconnect diagrams retained with the aircraft permanent records.
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 –
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 49
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 system cannot
communicate with the LRU.

Serial Number: Each LRU serial number is displayed (functions such as GPS 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
5.1.1
Data Path Failure Messages
Refer to the G1000 Cessna Citation Mustang Line Maintenance Manual.to troubleshoot data
path failure messages.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 50
5.2
Aural & Audio Alerts
The G1000 system is capable of issuing audio and aural (voice) alerts for various situations.
The following alerts are utilized by the G1000:
Alert Name
Purpose
Traffic (voice)
Traffic Advisory
No Traffic (voice)
Traffic Unavailable
“Minimums, Minimums” (voice)
Minimums Aural Alert
Alt Alert (aural)
Altitude Alerting Function
“Caution Terrain, Caution Terrain” (voice) and
TAWS Caution alert: Reduced required terrain clearance
“Terrain Ahead, Terrain Ahead” (voice)
Or Imminent impact with terrain.
“Terrain Terrain, Pull Up Pull Up” (voice) and
TAWS Warning alert: Reduced required terrain clearance
“Terrain Ahead Pull Up, Terrain Ahead Pull Up” (voice)
Or Imminent impact with terrain.
“Caution Obstacle, Caution Obstacle” (voice) or
TAWS Caution alert: Reduced required obstacle clearance
“Obstacle Ahead, Obstacle Ahead ” (voice)
Or Imminent impact with obstacle.
“Obstacle Obstacle Pull Up Pull Up” (voice) or
“Obstacle Ahead Pull Up, Obstacle Ahead Pull Up” (voice)
TAWS Warning alert: Imminent impact with obstacle.
“TAWS System Failure” (voice)
TAWS status alert: Terrain failure
“TAWS Not Available” (voice)
TAWS status alert: Terrain not available
“TAWS System Test, OK” (voice)(If passed) or
TAWS status alert: Terrain self-test
“TAWS System Failure” (voice) (If test failed)
“TAWS Available” (voice)
TAWS status alert: Terrain available
“Vertical Track” (voice)
Vertical navigation alerting function
.
5.3
5.3.1
GDU 105X Troubleshooting
GDU 105X Symptoms
Symptom
Recommended Action


Display is blank

Display resets

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 power.
 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.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
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Symptom
Recommended Action


Display flickers





SD card is stuck in GDU




Display will not track dimmer bus
Keyboard will not track dimmer bus
5.4
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 for service.

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.
A button/knob/joystick does not appear
to function
Terrain/Obstacle/SafeTaxi does not
display
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 PFD1 and PFD2.
 If problem follows unit, replace the display. Please note the
position it failed in (PFD1/2).
 If problem does not follow unit, troubleshoot aircraft wiring for
fault.




Reload GDU configuration files.
If display is a PFD, swap PFD1 and PFD2 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.
If display is the MFD, check dimmer input to verify voltage is present.
 Replace MFD if dimmer voltage is present.
GDU 105X Alerts
Refer to the G1000 Cessna Citation Line Maintenance Manual referenced in Table 1-2 to
troubleshoot GDU Alerts.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 52
5.5
5.5.1
GMA 1360D Troubleshooting
GMA Symptoms
Symptom/Failure
Message
Recommended Action
Noise in Audio
Most often the cause of the noise is external to the GMA. Try the following to locate
the source of the noise before replacing the GMA:

Try a different pair of headsets. Noise cancelling headsets may pick up and/or
generate more noise than standard headsets from their own circuitry.

Check for noise with the engine turned off.
 If the noise is present only when the engine is running, check the generator
and/or ignition system as possible sources of noise (see applicable airframe
specific maintenance manual).

Check for noise as all electrical equipment is turned on and off (strobes, other
radios, etc.).
 If the noise is identified from one electrical system or component refer to the
applicable airframe specific maintenance manual.

Ensure the NAV/COM squelch is not open.

Ensure the ADF and DME audio is not active.

Ensure the marker beacon audio is not active.

Ensure the ICS squelch is not open.
 Master squelch level can be adjusted on the GMA CONFIGURATION page for
higher noise environments.

Replace unit only after all possible external sources of noise are eliminated.
Buttons Do Not Work.

Some buttons are disabled in the GMA CONFIGURATION page by default. This is
to remove potential sources of audio noise for inputs that are not used. If in doubt
as to which buttons should be disabled, reload GMA config files and other config
files for optional equipment installed in the aircraft (i.e. ADF, HF, etc.) from the
loader card.
COM Bleedover

Verify on the GMA CONFIGURATION page that “Disable Split COM” has a green
box. Due to the closeness of the COM antennas and high power of the COM
transceivers, Split COM operation is not approved. If the box is black (indicating
COM ½ button is active), highlight “Disable Split COM” with the cursor and press
the ENT key to turn the box green which will deactivate Split COM mode.
Speaker Cuts Out

Reduce volume level of the item that caused the speaker to cut out when turned
up. A speaker protection circuit disables the speaker output if the volume is too
high. If the volume is not sufficient, replace aircraft cockpit speaker, reference the
Airframe Maintenance Manual.
Mic Audio Heard in
Speaker

Reduce ICS Volume.
GMA XTALK – GMA
crosstalk error has
occurred.
5.5.2





Ensure both GMA units are receiving power.
Ensure both units are properly configured by verifying there are no GMA alert
messages.
Check interconnect wiring between the GMA’s for faults.
Replace GMA1.
If problem persists, reinstall GMA1 and replace GMA2.
GMA Alerts
Refer to the G1000 Cessna Citation Line Maintenance Manual referenced in Table 1-2 to
troubleshoot GMA Alerts. Only GMA alerts new to this STC or that have additional
troubleshooting steps are listed.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 53
Failure Message
GMA1 AUX MANIFEST – GMA 1
AUX software mismatch,
communication halted.
GMA1 AUX MANIFEST – GMA 1
AUX software mismatch,
communication halted.
5.6
5.6.1
Cause
Solution
The system has detected an
incorrect software version loaded
in the specified GMA 1360D AUX
board.
Load the correct unit software. See
Section 3.8 for the Software Loading
procedure.
GDL 69A SXM Troubleshooting
GDL 69A SXM Symptoms
Symptom
Recommended Action
No SiriusXM audio is heard

No SiriusXM weather information is
displayed
Ensure the following items are not preventing the audio panel from
distributing SiriusXM audio (reference applicable G1000 Pilot’s
Guide):
Verify the SiriusXM volume is not muted on the Aux – XM Radio page on
the MFD.
 Verify the COM squelch is not open.
 Verify the ICS squelch is not open.
 Verify the marker beacon tones are not being received.
 Verify the headphone (if equipped) volume is turned up.
Go to the Aux – System Status page on the MFD and ensure unit is
online.
 If a red X is present, verify the unit is receiving power at the rack
connector.

Ensure there are no GDL alerts in the alert window. If there is an
Alert for software or configuration error or mismatch, reload the file
noted in the Alert.

Restart the PFD’s and MFD in configuration mode and go to the GDL
page.
 Verify unit is active.
 Verify the Signal number is “2” or “3”. If it is “0” or “1” check the
GDL 69A/69A SXM antenna and cabling for faults.
 Reseat the 69A SXM to verify the coax connector is fully seated.
 If unit is not active, contact SiriusXM Customer service to have a
refresh signal sent to your unit. You will need to provide them the
Audio Radio ID (and Data Radio ID number for SiriusXM weather)
numbers. Also verify with SiriusXM that the correct Weather
package (Aviator Lite or Aviator) is on the account, and that no
traffic service has been activated against that Radio ID. The unit
must be on for approximately one hour after the request for the
refresh has been sent to receive the signal.
 Alternatively, go to SiriusXM’s website and enter the radio
ID’s to have a refresh signal sent.
 If there are still problems receiving weather products after
performing the above step, call SiriusXM and have the account
deactivated, and a new account activated to clear out any corrupt
account information.
 Verify there is a good ground connection through the aircraft
between the MFD and the GDL 69A SXM unit. Reference the
Aircraft Maintenance Manual for instructions on how to check
bonding and ground points.
If problem persists, replace the GDL 69A SXM. Return unit to an
Authorized Repair Facility for service.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 54
5.6.2
GDL 69A SXM Alerts
Refer to the G1000 Cessna Citation Line Maintenance Manual referenced in Table 1-2 to
troubleshoot GDL 69 Alerts
5.7
5.7.1
GCU 475 Troubleshooting
GCU 475 Alerts and Problems
Failure Message
GCU CNFG – GCU Config error.
Config service req’d.
Cause
Solutions



Load GCU configuration files.
Replace GCU.
If problem persists, replace master
configuration module, check config
module wiring for faults and
replace if necessary.
NOTE
New Terrain/Obstacle cards,
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.

Check wiring for faults (ref Failed
Path troubleshooting section).
Replace the GCU 475.
Return unit to an Authorized
Repair Facility for service
The G1000 has detected a
GCU 475 configuration
mismatch.
GCU FAIL – GCU is inoperative.
The G1000 has detected a
failure in the GCU 475.
MANIFEST – GCU software
mismatch. Communication halted.
The system has detected an
incorrect software version
loaded in GCU 475.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang


Load the correct software version.
190-02450-01
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5.8
Software/Configuration Troubleshooting
Problem
Solutions
MFD or PFD displays do not power up:
Ensure that the criteria listed in Section 5.8.1 are
fulfilled for the applicable situation.

Ensure power is present at display backshell
connector.

Troubleshoot per the “Blank Display” GDU section.
5.8.1
System Communication Hierarchy
The following criteria must be satisfied to be able to perform the desired operation:
Desired Operation
Criteria for Success
Load Software to MFD or PFD Displays



Load AIRFRAME, SYSTEM, MFD1, PFD 1, PFD 2 and
MANIFEST configuration files to MFD and PFDs



Load Software/Configuration files to:
- GMA 1360D
- GRS 77
- GDC 74
- GTX 33
- GTX 345R
5.9



SW Loader Card must be inserted in top slot for
each display to be loaded.
CLR & 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 1.
PFD 1 and MFD must be powered on.
PFD 1 and MFD must have correct software.
SW Loader Card must be inserted into PFD 1 top
slot.
G1000 must be powered on.
PFD 1 and MFD must have correct software and
configuration settings.
Connector Layout
Refer to the current revision of the Installation manuals listed in Table 1-2 for connector layout
and pin assignments. These manuals are available in the Garmin Dealer Resource Center.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 56
6. Equipment Removal & Installation
This section describes how to remove and replace equipment associated with this STC. After
removal and replacement, the system must be configured and tested as described in Section 7.
Refer to Table 1-1 for specific installation drawings for unit locations and details.
CAUTION
When removing and/or replacing any G1000 NXi component, always ensure
that aircraft power is off. Unplug any auxiliary power supplies.
6.1
GDU 1050A/1550
Removal:
1. Using a 3/32” hex tool, rotate all four (GDU 1050A) or six (GDU 1550) 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 (GDU 1050A) or six (GDU 1550) ¼-turn fasteners clockwise
to lock the display to the panel.
6. Configure and test the MFD and/or PFD according to Section 7.2.
6.2
GMA 1360D Audio Panel
Removal:
1. Using a 3/32” hex tool, turn the hex nut counter-clockwise until the GMA 1360D is
unlocked from its location.
2. Carefully remove the GMA 1360D 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 1360D 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 1360D according to Section 7.3.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 57
6.3
GTX 345R Transponder
GTX 345R Removal:
1. Gain access to the unit located behind PFD2.
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 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. 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. Slide the unit in the rack until it stops. The unit will appear to stick out of the rack
approximately 3/8”.
5. Insert a 3/32” hex drive tool into the access hole in the front of the unit.
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.
6.4
GDL 69A SXM Satellite Receiver
Removal:
1. Gain access by removing the nose access panels. Refer to the Textron 510
Maintenance Manual for removal instructions.
2. Unlock the GDL 69A/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/69A SXM into its rack. The handle should
engage the dogleg track.
3. Press down on the GDL 69A/69A SXM handle to lock the unit into the rack.
4. Lock the handle to the GDL 69A/69A SXM body using the Philips screw. Torque the
handle screw to 10-14 in-lbs.
5. Configure and test the GDL 69A/69A SXM according to Section 7.5.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 58
GCU 475 Controller
6.5
Removal:
1. Use a 3/32” hex drive tool to turn each of the four locking sockets ¼ turn
counterclockwise until they reach their stops.
2. Disconnect backshell assembly from unit.
Reinstallation:
1. Inspect connector(s) for damaged pins.
2. Connect backshell assembly to unit.
3. Hold unit flush with the pedestal, ensuring locking stud alignment marks are in the
vertical position.
4. Use a 3/32” hex drive tool to turn each of the four locking sockets ¼ turn clockwise. This
may require applying a small amount of forward pressure to engage the ¼ turn sockets.
5. Configure and test the GCU 475 according to Section 7.6.
6.6
6.6.1
Configuration Modules
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 1050A PFD1. Refer to Table 1-1 for
specific installation drawings and wiring diagrams.
NOTE
Garmin Configuration Modules are not ESD sensitive. Configuration modules do not require
special ESD protection for handling during installation or maintenance.
Figure 6-1, Configuration Module Installation
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 59
Table 6-1, Configuration Module Kit – 011-00979-00
Garmin Part
Number
Item
Description
Qty Needed
1
Configuration Module PCB Board Assembly w/EEPROM & Temp
Sensor
1
2
Spacer, Config Module
1
213-00043-00
3
Cable, 4-Conductor Harness
1
325-00122-00
Pins, #22 AWG (HD)
5
336-00021-00
4
012-00605-00 or -02
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 6.6.26.6.2.
6.6.2
Configuration Module Checkout
If both PFD 1 and Master Configuration Module are replaced:
NOTE
New Terrain/Obstacle cards, 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 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 PFD 1.
2. Start the G1000 in configuration mode. Go to the System Upload Page on PFD 1.
3. See Section 3.8 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 3.8. Load optional files as
necessary.
5. Continue to Section 9 and conduct the return to service checkout.
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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. This section only applies to the hardware that was
changed or added as part of the G1000 NXi update per STCSA01896WI.
WARNING
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 3.8.
7.1
GIA Boot Block Load
Refer to the G1000 Cessna Citation Mustang Line Maintenance Manual for GIA 63W
replacement procedures.
If the GIA Boot Block version is 6.10 or later. No action is required to update the GIA Boot
Block.
If the GIA Boot Block version is less than version 6.10, the boot block must be updated. Follow
the steps to update the GIA boot block.
1. On PFD 1, go to the SYSTEM UPLOAD page using the small FMS knob.
2. Push in the PFD 1 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
“Options” in the drop-down menu and press the ENT key to select it.
Once “Options” is selected, the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Highlight ‘Cessna Mustang GIA BB Update’, then
press the ENT key to select it. The PRODUCT field will then populate.
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GDU 1050A/1550 PFD & MFD
7.2
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 7.2.7.
Original PFD Displays Installed in Opposite Locations for Troubleshooting
If the PFD 1 and PFD 2 are installed in opposite positions, no software or configuration loading
is required. Continue to the PFD/MFD Test procedure, Section 7.2.7.
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.
7.2.1
LRU Replacement Procedure PFD1
1. Open the PRIM and SEC circuit breakers for the MFD, PFD 1 and PFD 2.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the MFD, scroll to the LRU replacement page.
6. Activate the curser and select PFD1 in the LRU dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. 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.
16. If there are no red-Xs or system alerts, continue to Section 7.2.7.
7.2.2
Legacy Replacement Procedure PFD1 (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 3.8.
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7.2.3
LRU Replacement Procedure PFD2
1. Open the PRIM an SEC circuit breakers for the MFD, PFD 1 and PFD 2.
2. Remove SD cards from top and bottom slots of PFD2, MFD, and PFD1 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 PFD2, MFD, and PFD1 in configuration mode.
6. Using the MFD, scroll to the LRU replacement page.
7. Activate the curser and select PFD2 in the LRU dropdown box.
8. Press the CHK All softkey.
9. Press the Load softkey.
10. Press ENT to acknowledge the process was complete.
11. Deactivate the curser.
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 3.8.
17. If there are no red-Xs or system alerts, continue to Section 7.2.7.
7.2.4
Legacy Replacement Procedure PFD2 (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 3.8.
7.2.5
LRU Replacement Procedure MFD
NOTE
Anytime the MFD is replaced, all databases will have to be reloaded.
1. Open the PRIM and SEC circuit breakers for MFD, PFD 1 and PFD 2.
2. Remove SD cards from top and bottom slots of PFD2, MFD, and PFD1 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 PFD2, MFD, and PFD1 in configuration mode.
6. Using the PFD1, scroll to the LRU replacement page.
7. Activate the curser and select MFD in the LRU dropdown box.
8. Press the CHK All softkey.
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9. Press the Load softkey.
10. Press ENT to acknowledge the process was complete.
11. Deactivate the curser.
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 3.8.
17. Install databases. Refer to Section 3.13 to re-load databases.
18. After databases are re-loaded, continue to Section 7.2.7.
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7.2.6
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 3.8.
7.2.7
PFD/MFD Test
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 RAT fields are valid
within 2 minutes of power up on both PFDs.
4. Press the Sensor softkey on each PFD and switch between ADC1 and ADC2. Verify
that data from both air data computers is valid on both displays.
5. Press the Sensor softkey on each PFD and switch between AHRS1 and AHRS2. Verify
that data from both AHRS is valid on both displays.
6. Check that the engine instrument fields are valid on the MFD.
Figure 7-1, G1000 Normal Mode Check
7. Push the red DISPLAY BACKUP button on the pilot-side GMA. Verify that the pilot-side
PFD and MFD displays enter reversion mode. MFD should have valid altitude, airspeed,
vertical speed, COM1, COM2, NAV1, NAV2 and engine instruments.
8. De-activate pilot-side reversion mode by pushing the DISPLAY BACKUP button. Verify
PFD 1 and MFD return to normal display modes.
9. Repeat Step 1 using GMA2. Ensure that PFD 2 and MFD enter reversion mode and
MFD displays valid altitude, airspeed, vertical speed, COM1, COM2, NAV1, NAV2 and
engine instruments.
10. De-activate co-pilot’s side reversion mode by pushing the DISPLAY BACKUP button.
Verify PFD 2 and MFD return to normal display modes.
11. Select the Map – TAWS Map page on the MFD.
12. 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”.
13. Press the MENU button and select “Test TAWS” from the pop-up menu.
14. After the TAWS test has completed, verify that “TAWS System Test Okay” is heard over
the cockpit speaker.
15. If no other service is to be performed, perform final return-to-service test as specified in
Section 9.
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GMA 1360D Audio Panel
7.3
Original GMA 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.
Original GMA Installed in Opposite Locations for Troubleshooting
If the original GMA #1 and GMA #2 are installed in opposite locations, configuration loading is
required. See Section 7.3.1.
New, Repaired or Exchange GMA Installed
If a new, repaired or exchanged GMA is installed, the correct software and configuration files
must be loaded to the unit. See Section 7.3.1.
7.3.1
LRU Replacement Procedure GMA 1 or GMA 2
1. Open the PRIM and SEC circuit breakers for the MFD, PFD 1 and PFD 2..
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GMA1 or GMA2, whichever was replaced in the LRU
dropdown box
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.3.2.
16. If there are no red-Xs or system alerts, continue to Section 7.3.3.
7.3.2
Legacy Replacement Procedure GMA 1 or GMA 2 (Alternate Method)
Perform the steps in Section 3.8.4 to load the applicable audio panel software and configuration.
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Configuration Manager Update
1. With the system still in configuration mode, scroll to the Configuration Manager page on
PFD 1.
2. Press the CNFM CFG softkey.
3. Select ok when prompted to “Confirm configuration as expected configuration”
4. Power cycle the system. Verify there are no red-Xs or system alerts.
5. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
6. If there are no red-Xs or system alerts, continue to Section 7.3.3.
7.3.3
GMA Test
Except for marker beacon operation, an in-aircraft checkout may be performed in the aircraft
with known good microphone, headset, and speaker.
7.3.4
Intercom System (ICS) Check
1. Ensure that the MAN SQ key is off (no light).
2. Adjust GMA1 and GMA2 ICS volume to a comfortable level.
3. Plug in a headset at each COCKPIT ICS position simultaneously.
4. Verify the following:

Two-way communication between each COCKPIT ICS jack position.
5. On GMA1 select COM1 MIC and AUDIO.
6. Ensure PA is deselected on GMA1 or GMA2. Verify an active (green) COM1 frequency
is displayed on both PFDs.
7. On GMA1 or 2 select PA and verify the PA select annunciator is illuminated on GMA1
and GMA2. Verify COM1 active frequency is displayed white.
8. Initiate passenger address using pilot’s headset boom mic by selecting PA on the audio
panel and keying the pilot’s PTT. Verify the following: Ensure that the passenger
locations have headsets installed with 3.5mm jack connectors

Clear PA audio can be heard over the passenger headsets

PA selected annunciator on GMA1 flashes ~ once per second during PA
address.
9. Initiate passenger address using copilot’s headset boom mic by selecting PA on the
audio panel and keying the copilot’s PTT. Verify the following:

Clear PA audio can be heard over the passenger headsets

PA selected annunciator on GMA2 flashes ~ once per second during PA
address.
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7.3.5
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.
3. On the copilot’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 copilot’s headset.
4. Press the SPKR key on copilot’s audio panel and verify that the selected audio is heard
over the copilot’s speaker.
7.3.6
Failsafe Operation Check – GMA #1
1. Turn the GMA #1 off by pulling the AUDIO NO 1 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 NO 1 circuit breaker to continue testing.
7.3.7
Failsafe Operation Check – GMA #2
1. Turn the GMA #2 off by pulling the AUDIO NO 2 circuit breaker. This directs all COM 2
phone audio, MIC audio and MIC key to the co-pilot’s position.
2. Check the failsafe operation by exercising the COM 2 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 2 using the failsafe
operation.
3. Close the AUDIO NO 2 circuit breaker to continue testing.
7.3.8
Marker Beacon Test
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 1 and PFD 2 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 #1 and #2 GMA 1360D 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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GTX 345R Transponder
7.4
Original GTX is Reinstalled
No software or configuration loading is required if the removed GTX 345R 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 345R Test Section 7.4.4.
New, Repaired or Exchange GTX is Installed
If a new, repaired or exchange GTX 345R is installed, the correct software and configuration
files must be loaded to the unit. See Section 7.4.1.
7.4.1
LRU Replacement Procedure GTX2
1. Open the PRIM and SEC circuit breakers for MFD, PFD 1 and PFD 2.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GTX2, whichever was replaced in the LRU dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. 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.
16. If there are no red-Xs or system alerts, continue to Section 7.4.3.
7.4.2
Legacy Replacement Procedure GTX2 (Alternate Method)
Perform the steps in Section 3.8.5 to load the applicable transponder software and
configuration.
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7.4.3
Transponder Configuration
1. If not applied, apply power to the G1000 system and put all displays into config mode.
2. On PFD1, select the AIRCRAFT CONFIGURATION page.
3. Press the Set GTX # softkey for the unit replaced and acknowledge the PFD1 prompt by
pressing the ENT key.
4. After completing transponder configuration, deactivate the cursor.
Figure 7-2, Aircraft Registration
7.4.4
GTX 345R Test
Operation of the GTX transponder is accomplished using PFD 1, PFD 2 or the MFD. Refer to
Cockpit Reference Guide, listed in Table 1-2 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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GDL 69A or GDL 69A SXM Data Link
7.5
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
7.5.3.
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.
7.5.1
LRU Replacement Procedure
1. Open the PRIM and SEC circuit breakers for MFD, PFD 1 and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GDL69 in the LRU dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.5.2.
16. If there are no red-Xs or system alerts, continue to Section 7.5.3.
7.5.2
Legacy Replacement Procedure GDL69 (Alternate Method)
Perform the steps in Section 3.8.6 to load the applicable GDL69 software and configuration..
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7.5.3
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.
If no other service is to be performed, continue to the return-to-service checks in Section 9.
GCU 475 FMS Controller
7.6
Original GCU 475 Reinstalled
No software or configuration loading is required if the removed GCU 475 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 GCU 475 Test Section 7.6.3.
New, Repaired or Exchange GCU 475 Installed
If a new, repaired or exchange GCU 475 is installed, the correct software and configuration files
must be loaded to the unit. See Section 7.6.1 and then continue to the GCU 475 Test Section
7.6.3.
7.6.1
LRU Replacement Procedure GCU 475
1. Open the PRIM and SEC circuit breakers for MFD, PFD 1 and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select the installed servo CTL in the LRU dropdown box.
7. Press the Load softkey.
8. Press ENT to acknowledge the process was complete.
9. Select the installed servo MON in the LRU dropdown box.
10. Press the Load softkey.
11. Press ENT to acknowledge the process was complete.
12. Deactivate the curser.
13. Scroll to the Configuration Manager page.
14. Press the CNFM CFG softkey.
15. Select ok when prompted to “Confirm configuration as expected configuration”
16. Power cycle the system. Verify there are no red-Xs or system alerts.
17. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.6.2.
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18. If there are no red-Xs or system alerts, continue to Section 7.6.3.
7.6.2
Legacy Replacement Procedure GCU 475 (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “Mustang Baseline” and press ENT key on PFD1.
6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight Cessna Mustang Baseline Configuration. Press ENT key on PFD1.
7. Press the CLR ALL key.
8. Scroll to highlight GMC.
9. Highlight the software box and press the ENT key to check the box.
10. Highlight the Configuration box and press the ENT key to check the box.
11. Press the Load softkey.
12. Monitor load progress. Verify software load completes without errors as indicated by the
following:

Green “PASS” in the Configuration and Software columns for each item loaded.

“Upload Complete………….COMPLETE” in the summary box.
13. Press ENT key on PFD1 to acknowledge upload complete.
14. Deactivate cursor.
15. Scroll to the Configuration Manager page.
16. Press the CNFM CFG softkey.
17. Select ok when prompted to “Confirm configuration as expected configuration”
18. Power cycle the system. Verify there are no red-Xs or system alerts.
19. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
20. If there are no red-Xs or system alerts, continue to Section 7.6.3.
7.6.3
GCU 475 Test
Perform the following key and knob presses and knob rotations on the GCU 475, and verify the
actions on the MFD.
1. Rotate the large FMS knob and verify that the page groups change. On the MFD
2. Rotate the small FMS knob and verify that the pages change within the page groups.
3. Use the large FMS knob to display the Map page group and the small FMS knob to
display the Map - Navigation Map page.
4. Rotate the RANGE knob to the right and verify the map display zooms out.
5. Rotate the RANGE knob to the left and verify the map display zooms in.
6. Press the RANGE knob to get the pointer on the map display.
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7. Move the RANGE knob to the left and verify the pointer moves to the left.
8. Move the pointer up, right and down and verify that the pointer moves accordingly.
9. Press the RANGE knob to stop displaying the pointer.
10. Press the left and right arrowheads of the SOFTKEY SELECT keys. Verify softkeys
highlighting on the MFD changes.
11. Press the
key to display the FPL – Direct To page.
12. Use the keypad to type KIXD and verify KIXD is displayed on the MFD.
13. Press the SPC key to add a space and then the BACK key to delete the space.
14. Press the CLR key to clear the field.
15. Type K34 and then press the ENTER key twice. Verify that the flight path to K34 is
displayed on the map.
16. Press the FPL key to open the FPL – Active Flight Plan page. Press the FPL key
again to close it.
17. Press the PROC key to open the Procedures page. Press the PROC key again to close
it.
18. Press the MENU key to open the Menu page. Press the MENU key again to close it.
19. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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8. SUBSYSTEM FUNCTIONAL CHECKS
TAWS Functional Check
8.1
8.1.1
Functional Check for TAWS-B
1. With the G1000 in Normal Mode, use the GCU FMS knob to select the Map group and
TAWS page on the MFD.
2. Verify that the title at the top of the page reads “Map – TAWS-B Map”.
NOTE
If TAWS has not been enabled, the title will read “Map – Terrain Proximity”
or “Map – Terrain”. Refer to Section 3.10.3 for TAWS B Configuration for
enabling this feature
3. Press the GCU MENU button and select “Test TAWS System” from the pop-up menu.
Verify TAWS test annunciation is displayed on the MFD and both PFDs.
4. After the TAWS test has completed, verify that “TAWS System Test Okay” is heard over
the cockpit speaker (if selected) and the headsets.
5. Press the GCU MENU button again and select “Inhibit TAWS” from the pop-up menu
and press ENT on the GCU. Verify “TAWS INH” is displayed on PFD 1 and PFD 2.
6. Press the GCU MENU button again and select “Enable TAWS” from the pop-up menu
and press ENT on the GCU. Verify the “TAWS INH” annunciation on the PFDs has
extinguished.
7. Ensure cockpit speaker is selected ON.
8. Pull the PFD1 PRI and PFD1 SEC circuit breakers, and power PFD1 on in configuration
mode. Use the PFD1 FMS knob to go to the System Audio (Audio Alert Configuration)
page.
9. Use the PFD1 FMS knob to highlight each of the following messages then select PLAY.
Verify each of the following audio messages are played:

Too Low Terrain

Sink Rate

Pull Up

Don’t Sink

Five Hundred

Caution, Terrain (2X)

Terrain (2X), Pull Up (2X)

Caution, Obstacle (2X)

Obstacle (2X), Pull Up (2X)

Terrain Ahead (2X)

Terrain Ahead, Pull Up (2X)

Obstacle Ahead (2X)

Obstacle Ahead, Pull Up (2X)
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10. Pull the PFD1 PRI and PFD1 SEC circuit breakers, and re-power PFD1 in normal
operating mode.
11. If no other service is to be performed, continue to the return-to-service checks in Section
9.
8.2
ChartView Functional Check
ChartView must be enabled using a ChartView Enable Card. Reference Section 3.10.1 for
enabling procedures.
NOTE
The required ChartView databases are subscription-based and are to be
procured by the aircraft owner directly from Jeppesen.
1. With the G1000 in Normal Mode, use the GCU FMS knob to select ‘Aux – System
Status’ page, then select MFD1 DB softkey.
2. Use the small FMS knob to scroll to CHART.
3. Verify “ChartView” is displayed in blue text adjacent to CHART.
4. Verify the ChartView database cycle number is displayed in blue text and the ChartView
database is current.
5. Deactivate the cursor and use the large GCU FMS knob to select the Navigation Map
Page then press the Charts softkey.
6. Verify the airport chart is displayed and the following softkeys are displayed(some
softkeys may be grayed out):

CHRT OPT
 APR

Show Map
 WX

INFO-1
 NOTAM

DP
 Go Back

STAR
7. Press CHRT OPT softkey and verify the following softkeys are displayed (some softkeys
may be grayed out):

All

Header

Plan

Profile

Minimums

Fit WDTH

Full SCN

Back
8. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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8.3
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 map

Weather Datalink Page

Airport Information Page

Intersection Information Page

NDB Information Page

VOR Information Page

User Waypoint Information Page

Trip Planning Page

Nearest Pages
1. Use the FMS knob on the GCU to select the Aux – System Status page and select
MFD1 DB softkey. Use the small FMS knob to scroll to CHART category and verify
“FliteCharts” is displayed in blue text adjacent to “CHART”.
2. Verify the FliteCharts database ‘Region’, ‘Cycle’ number, ‘Effective’, ‘Expires’, and
‘Disables’ dates of the subscription appear in cyan text.
3. Use the FMS knob on the GCU to select Map - Navigation Map page.
4. On the GCU, press MENU. With Map Setup highlighted, press ENT on the GCU. Rotate
the small GCU FMS knob to select the Aviation group and press the ENT key on GCU.
5. Turn the GCU large FMS Knob to scroll through the Aviation Group options to ‘SafeTaxi’.
6. Turn the GCU small FMS Knob to display the range of distances.
7. Turn the GCU FMS Knob to select 5000ft as the distance for maximum SafeTaxi display
range, and then press the GCU ENT key to complete the selection.
8. Using the GCU range knob, select a range of 5000ft or less. Verify SafeTaxi display
represents the current aircraft location and the airport layout.
9. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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8.4
Low Speed Awareness Band Check
This procedure will verify that the GDU air/ground status is functioning correctly with valid
Weight on Wheels (WOW) inputs.
1. Ensure aircraft is positioned with weight on wheels.
7. Apply external power to the aircraft. Set BATT and AVN PWR switches to ON and wait
for all aircraft and avionics systems to complete their initialization and begin operating
normally.
8. Use a pitot/static ramp tester to simulate an airspeed value of 110 knots indicated.
9. Verify there is no WOW MISCOMPARE CAS message.
10. Verify the Low Speed Awareness band (red band) is NOT displayed on the PFD 1 and
PFD 2 airspeed tapes (see Figure 8-1)
11. Place the airplane on jacks with the wheels clear of the ground (reference Textron
Aviation 510MM Chapter 7-00-00), or configure the WOW switches to the In-Air position.
12. Verify there is no WOW MISCOMPARE CAS message.
13. Verify the Low Speed Awareness band (red band) appears at the low end of the Air
Speed Tape on the PFD 1 and PFD 2 (see Figure 8-1). This may require the AOA vane
to be moved to a high-alpha position.
14. Remove airplane from jacks, or return the WOW switches to the On-Ground position.
Figure 8-1, Low Speed Awareness Band Symbolization
15. Verify the Low Speed Awareness band (red band) is removed from PFD 1 and PFD 2
airspeed tapes
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8.5
DME Functional Check
This check verifies that the DME-to-G1000 interface operates correctly.
1. If DME is not displayed, press the PFD Opt softkeys on PFD 1 and PFD 2, then press
the DME softkey. Verify the DME window is displayed next to the PFD 1 and PFD 2
HSI.
2. On PFD 1 and PFD 2, press the BACK softkey then select DME softkeys. Verify the
DME TUNING screen is displayed.
3. On PFD 1 and PFD 2, use the large FMS knob to select the NAV1, NAV2 and HOLD
modes in the DME field. Verify that the NAV1, NAV2 and HOLD modes can be selected
by turning the small FMS knob.
4. Set NAV1 and NAV2 frequencies to 108.00 and 117.00 respectively.
5. On PFD 1 and PFD 2, set the DME Tuning mode to NAV1. Verify that the DME window
display is set to the NAV1 frequency of 108.00.
6. On PFD 1 and PFD 2, set the DME Tuning mode to NAV2. Verify that the DME window
display is set to the NAV2 frequency of 117.00.
7. On PFD 1 and PFD 2, set the DME Tuning mode to HOLD. Verify that the last selected
NAV frequency of 117.00 remains the same when the NAV2 frequency is changed.
8. Set the DME Tuning mode to NAV1
9. On the NAV Test Set, set up a DME test and note the Nav frequency. Tune NAV 1 to
the test set frequency and ensure the DME Tuning MODE is set to NAV1 on PFD 1 and
PFD 2. Set NAV 2 to a frequency other than the test set frequency.
10. Verify that the DME distance on PFD 1 and PFD 2 match the test set.
11. Enable the DME and SPKR buttons on GMA1 and GMA2 audio panels. Verify DME
audio can be heard over the cockpit speakers.
12. Disable the DME button on both GMAs.
13. On PFD 1 and PFD 2, set the DME Tuning mode to NAV2 and verify that the DME
distance is dashed out.
14. Tune NAV 2 to the test set frequency. Set NAV 1 to a frequency other than the test set
frequency.
15. Verify that the DME distance on PFD 1 and PFD 2 match the test set.
8.6
ADF Functional Check
This check verifies that the ADF / G1000 interface operates correctly.
1. Press the PFD softkey on PFD1 and PFD2. Toggle the BRG1 and BRG2 softkey until
the ADF bearing is shown on PFD1 and PFD2.
2. Verify that the ADF window is not invalid (no red ‘X’).
3. Using the ADF control head select a known valid local ADF. Verify that the ADF bearing
pointer moves towards a bearing and stabilizes.
4. Select ADF and SPKR on GMA1 and GMA2. Using the ADF control head, select, ANT
mode. Verify that the audio from the station tuned can be heard on the pilots and
copilots headset and cockpit speaker.
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5. Increment the ADF volume control from full low to full high. Verify the volume increases
and decreases appropriately over pilots and copilots headset and cockpit speaker.
6. If no other service is to be performed, continue to the return-to-service checks in Section
9.
8.7
HF Radio Function Check
NOTE
This functional check applies to only to aircraft equipped with the
Bendix/King KHF-1050 radio, that have also installed the optional
GMA 1360D audio panels
1. Make sure that the HF and the HF PA RESET circuit breakers on the copilot's circuit
breaker panel are engaged.
2. Push and release the VOL/PUSH PWR inner knob on the HF control unit to start the
KHF-1050 HF communication system and do a BIT.
NOTE
Let the BIT operate for at least 30 seconds to complete.
3. After the BIT is completed, set the function selector knob (left outer knob) on the HF
control unit to the FREQ position.
4. Push the AUX MIC and the SPKR buttons on both GMA 1360D audio panels.
5. Push and release the TEST button on the HF control unit.
6. Verify that a short “tune” tone is heard in the HF receiver audio through the cockpit
speakers.
7. Push and release the TEST button again to exit the test mode.
8. Tune the HF radio to radio station WWV (Ft. Collins, CO) or WWVH (Kehaha, HI) on the
frequencies that follow (select the frequency with the best signal):
NOTE
This test can be performed in a hangar if the airplane is near the open
hangar doors. If the signal strength is not sufficient, a signal generator can
be used (IFR 4000 or equivalent). Set the signal generator to radiate a 10
MHz, AM signal, modulated with a 1000 Hz (approximate) continuous tone.
Do not directly couple the signal generator to the KPA-1052 HF power
amplifier, KAC-1052 HF antenna coupler, or HF antenna wire. Tune the HF
for 10000.0 kHz, instead of the below frequencies.
a. 2500.0 kHz
b. 5000.0 kHz
c. 10000.0 kHz
d. 15000.0 kHz
e. 20000.0 kHz
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9. Turn the function selector knob to the SQL position.
10. Push the FUNC button again and again as necessary to select SBH.
11. Turn the TUNE ENT inner knob to change the squelch mode to OPN.
NOTE
Use the VOL/PUSH PWR inner knob to adjust the HF volume
12. Make sure that the HF audio is heard on the two cockpit speakers and the two flight
crew headsets.
13. Push the SPKR button on the two audio panels as necessary to isolate each cockpit
speaker while you test the other speaker.
8.8
KTA-870 TAS Traffic System Functional Check
NOTE
This functional check applies to only to aircraft equipped with the optional
Bendix/King KTA 870 TAS.
The G1000 interface to the TAS system differs slightly depending on whether the GTX 345R
ADS-B In Transponder is installed or not. Follow these procedures and take note of which
transponder configuration is presently installed when performing them.
1. Select the TRAFFIC MAP page on the MFD.
2. On PFD1, press the Map/HSI softkey, then press the Layout softkey. Press the HSI
Trfc softkey.
3. On PFD2, press the Map/HSI softkey, then press the Layout softkey. Press the Inset
Trfc softkey.
4. For aircraft without GTX 345R, perform the following steps:
a. Verify Standby, Normal, Test, and ALT Mode softkeys are available on the
bottom of the display.
b. Press the Test softkey and verify that TEST is displayed in the upper left corner
of the traffic map and a traffic test pattern is displayed. Upon completion of the
test, verify that a “TAS SYSTEM TEST OK” aural is heard over the cockpit
speaker.
5. For aircraft with GTX 345R, perform the following steps:
a. Verify ADS-B, TAS STBY, TAS OPR, Test, FLT ID, Motion, and ALT Mode
softkeys are available on the bottom of the display.
NOTE
If the ADS-B In softkey is selected, or if the aircraft is “In Air”, the Test mode
softkey will be greyed out.
If the ALT Mode softkey is not displayed, the G1000 NXi has not been
properly configured for the traffic system. Load the configuration file for the
non-Garmin traffic system installed.
b. Press the ADS-B softkey to deselect it.
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c. Press the Test softkey and verify that TEST is displayed in the upper left corner
of the traffic map and a traffic test pattern is displayed. Upon completion of the
test, verify that a “TRAFFIC SYSTEM TEST PASSED” aural is heard over the
cockpit speaker.
6. Open the TRAFFIC circuit breaker on the copilot circuit breaker panel.
7. For aircraft without GTX 345R:
a. Verify an amber TRFC FAIL banner is displayed on the Traffic Map and the PFD
inset and HSI traffic maps.
b. On either PFD, press the Messages softkey.
c. Verify a white system message ‘TRAFFIC FAIL – Traffic device has fail.’ Is
shown.
8. For aircraft with GTX 345R:
a. Verify an white TAS: FAIL is shown in the upper right corner of the Traffic Map
and the PFD2 inset map.
b. Verify an amber FAILED banner is shown in the center of the Traffic Map page
on the MFD and PFD inset and HSI traffic maps.
c. On either PFD, press the Messages softkey.
d. Verify a white system message ‘TCAS FAIL – Traffic: TAS/TCAS inop or
connection lost’ is shown.
e. Press the ADS-B softkey on the MFD to enable it.
f.
Verify the amber FAILED banner is removed from the center of the Traffic Map
and PFD inset and HSI maps.
9. Close the TRAFFIC circuit breaker on the copilot circuit breaker panel and verify that the
TAS: FAIL failure indications and system message are removed after several seconds.
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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 using
the General Arrangement drawing listed in Table 1-1.
Perform the following subsection tests to confirm the G1000 system is operating correctly.
9.1
Display Test
Apply aircraft power. On the MFD power-up screen in the upper right corner, find the
Cessna Mustang System XXXX.XX’ number. This number is the G1000 System
Software Loader Image version number that was used to install the software to the
system.
Figure 9-1, MFD Power Up Page
Verify that the System Software Version is the same as listed in Table 1 of the 00501328-01 General Arrangement Drawing.
Press the GCU ENT key to acknowledge the splash screen. on the MFD (NOTE: The
rightmost softkey on the MFD 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 RAT 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 both PFDs 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 PFDs with
no Red-X failure indications are shown in Figure 9-3.
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(Without SVS enabled, reversionary mode)
(With SVS enabled)
Figure 9-3, PFD Normal Operation
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NOTE
Outputs from the GRS 77 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 PFD1 and PFD2.
Check that altitude, airspeed, vertical speed, GS, TAS, and RAT fields are valid on
PFD1 and PFD2.
Press the PFD Opt softkey on each PFD.
Press the SENSOR softkey on each PFD and switch between ADC1 and ADC2. Verify
that data from both air data computers are valid on both displays.
Press the SENSOR softkey on each PFD and switch between AHRS1 and AHRS2.
Verify that data from both AHRS are valid on both displays.
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
Step
Desired Result
MFD Failure Condition:
1. Open MFD CB.
2. Verify desired results.
3. Close MFD CB.
For an MFD failure condition, the following shall occur:
PFD2 Display Failure Condition:
1. Open PFD 2 CB.
2. Verify desired results.
3. Close PFD 2 CB.


MFD goes blank.

The COM 1/2 and NAV 1/2 tuning fields remain valid
and can be tuned by rotating the tuning knobs on
PFD1 and PFD2.

XPDR 1/2 fields remain valid and XPDRs can adjusted
via PFD softkeys.
All PFD1 and PFD2 primary flight information is
retained.
For a PFD2 failure condition, the following shall occur:


PFD2 goes blank.
PFD1 and MFD remain in normal display formats. The
following illuminate on PFD1:
o
o
o
o
o


A white HDG box adjacent to the heading window
A white ROL box adjacent to the roll scale
A white PIT box adjacent to the pitch ladder
A white IAS box in the airspeed tape
A white ALT box in the altitude tape
GMA2 Fail – GMA2 is inoperative.
XPDR2 Fail – XPDR2 is Inoperative.
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Step
Desired Result
PFD1 Display Failure Condition:
1. Open PFD 1 PRI and PFD1 SEC circuit
breakers.
2. Verify desired results.
3. Close PFD 1 PRI and PFD1 SEC circuit
breakers.
For a PFD1 failure condition, the following shall occur:


PFD2 and MFD remain in normal display formats. The
following illuminate on PFD2:
o
o
o
o
o


9.3
PFD1 goes blank.
A white HDG box adjacent to the heading window
A white ROL box adjacent to the roll scale.
A white PIT box adjacent to the pitch ladder
A white IAS box in the airspeed tape
A white ALT box in the altitude tape
GMA1 Fail – GMA1 is inoperative.
XPDR1 Fail – XPDR1 is Inoperative.
Reversion Mode Check
Push the red DISPLAY BACKUP button on GMA1. Verify that the pilot-side 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
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De-activate pilot-side reversion mode by pushing the DISPLAY BACKUP button. Verify
PFD1 and MFD return to normal display modes.
Repeat Step 1 using GMA2. Ensure that PFD2 and MFD enter reversion mode and
MFD displays valid altitude, airspeed, vertical speed, COMM1, COMM2, NAV1, NAV2
and engine instruments.
De-activate co-pilot’s side reversion mode by pushing the DISPLAY BACKUP button.
Verify PFD2 and MFD return to normal display modes.
9.4
Aircraft Basic Empty Weight Initialization
Figure 9-5, Basic Empty Weight Entry
10. At the MFD Aux – Weight Planning page, press the Empty WT softkey.
11. Determine the aircraft’s basic empty weight from the appropriate Weight & Balance
records.
12. Use the GCU 475 FMS knob to input the aircraft’s basic empty weight to the nearest 10
LB, then press the ENT key.
9.5
Field Elevation Initialization
1. On PFD1, press the TMR/REF softkey.
2. Use the FMS knob to highlight the DEST ELV field, then enter the local field elevation at
the present position. Press the ENT key.
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3. Verify the red X on the MFD EICAS ‘DEST ELV’ field is replaced by the field elevation
entered on PFD1.
4. Press the TMR/REF softkey on PFD1.
9.6
EICAS Verification
1. Review the engine indicating and Crew Alerting window on the MFD.
2. Confirm all data fields are valid with no red X’s present.
3. Actuate the rudder trim in both L and R directions and verify the cyan rudder trim pointer
tracks in the appropriate direction of movement.
4. Actuate the aileron trim in both L and R directions and verify the cyan aileron trim pointer
tracks in the appropriate direction of movement.
5. Lower the flaps through each selection detent while observing the flap indication window
and verify the flap indication tracks through the range of movement.
6. Raise the flaps to the fully retracted position.
9.7
Rotary Test
NOTE
Technician should acknowledge any flashing CAS message(s) by
pressing the Master Warning reset or Master Caution reset switches as
appropriate, before continuing to the next rotary test position.
1. Rotate the rotary test switch to the FIRE WARN test position.
2. Verify the red L ENGINE FIRE, R ENGINE FIRE, and pilot/copilot MASTER WARNING
lights illuminate.
3. Rotate the rotary test switch to the LANDING GEAR test position.
4. Verify the gear warning horn sounds, alternating between pilot and copilot cockpit
speakers.
5. Rotate the rotary test switch to the CABIN ALT test position.
6. Verify the red CABIN ALT and the amber CABIN ALT CAS messages posts on the MFD
and that both MASTER CAUTION lights illuminate.
7. Rotate the rotary test switch to the STALL test position.
8. Verify both MASTER CAUTION lights illuminate. Verify the following CAS messages
posts to the MFD
a. STALL WARN FAIL (Amber)
b. STALL WARN HTR (Amber)
c. STALL WARN HI (White)
9. Rotate the rotary test switch to the FLAPS test position.
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10. Verify the flap position indication on the MFD turns invalid (red X) and that both
MASTER CAUTION lights illuminate for 3 seconds. Verify the following CAS messages
posts to the MFD
a. FLAPS FAIL (Amber)
b. STALL WARN FAIL (Amber, posts only for 3 seconds)
11. Rotate the rotary test switch to the OVERSPEED test position.
12. Verify the overspeed warning horn sounds, alternating between pilot and copilot
speakers.
13. Rotate the rotary test switch to the ANTI SKID test position.
14. Verify both MASTER CAUTION lights illuminate, and the following CAS messages post
to the MFD:
a. ANTISKID FAIL (Amber, posts only for 6 seconds)
b. NO TIRE SPINDOWN (White, posts only for 6 seconds)
15. Rotate the rotary test switch to the ANNU test position.
16. Verify both MASTER CAUTION lights illuminate and cannot be acknowledged or
cancelled.
17. Verify both MASTER WARNING lights illuminate and cannot be acknowledged or
cancelled.
18. Verify the GMC autopilot mode control panel lights are illuminated.
19. Verify both GMA audio panel lights are illuminated.
20. Verify a test audio tone sounds.
21. Rotate the rotary test switch to the OFF position.
G1000 Backup Path Test
9.8
With all three displays in normal mode and the entire avionics system turned on, verify on PFD1
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.
Maintenance Records
9.9
The Configuration Checklist in Section 3.6 should be completed when a software update has
been performed and maintained with the aircraft permanent 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.
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 90
APPENDIX A - GARMIN UNIT PART AND SERIAL NUMBER CROSS REFERENCE
This table below shows the unit part number and serial number prefix combinations.
LRU
GIA 63W
GDU 1050A (PFD1 & PFD2)
GDU 1550 (MFD)
GMA 1347D
GMA 1360D
GTX 33 (LEGACY)
GTX 33D (OPTIONAL)
GTX 345R (OPTIONAL)
GCU 475
GDL 69A (LEGACY)
GDL 69 SXM
FLIGHT STREAM 510 (OPTIONAL)
PART NUMBER
SERIAL NUMBER FIRST
THREE DIGITS
011-01105-00
011-01105-01
011-01105-20
011-03470-10
011-03472-00
011-01257-20
011-03568-20
011-00779-30
011-00779-21
011-03303-00
011-04475-00
011-00987-00
011-03177-10
011-03595-00
685
15W
1HQ
494
496
171
4QF
891
848
3EH
48V
477
3NV
402
Garmin G1000 NXi System Maintenance Manual
Textron Aviation Inc. Model 510 Citation Mustang
190-02450-01
Revision 1
Page 91
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