Garmin G1000 NXi - Cessna Citation Mustang Owner's manual

190-02450-01 2019 Revision 2

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

Garmin G1000 NXi System Maintenance Manual 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 1

Garmin Ltd. or its subsidiaries

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

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

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

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

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

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

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

Garmin International, Inc.

1200 E. 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

Description

1 02/04/19 Initial Release

2 11/13/14

Revised to incorporate additional feature ‘disable’

options.

DOCUMENT PAGINATION

Section

Pagination

Table of Contents

3-5

Section 1

6-9

Section 2

10-16

Section 3

17-42

Section 4

43-48

Section 5

48-56

Section 6

57-60

Section 7

61-74

Section 8

75-82

Section 9

83-90

Appendix A

91

Garmin G1000 NXi System Maintenance Manual 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 2

INFORMATION SUBJECT TO EXPORT CONTROL LAWS

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

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

VII Subchapter C) and which may not be exported, released or disclosed to foreign nationals

inside or outside the United States without first obtaining an export license. A violation of the

EAR may be subject to a penalty of up to 10 years imprisonment and a fine of up to $1,000,000

under section 2410 of the Export Administration Act of the 1979. The preceding statement is

required to be included on any and all reproductions in whole or in part of this manual.

WARNING

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

California to cause cancer, birth defects, or reproductive harm. This Notice is being provided in

accordance with California's Proposition 65. If you have any questions or would like additional

information, please refer to our web site at www.garmin.com/prop65

.

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 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 3

TABLE OF CONTENT

1. INTRODUCTION ......................................................................................................................................... 6

1.1 CONTENT, SCOPE, PURPOSE ................................................................................................................................ 6

1.2 APPLICABILITY .................................................................................................................................................. 6

1.3 ORGANIZATION ................................................................................................................................................. 6

1.4 DEFINITIONS/ABBREVIATIONS ............................................................................................................................. 7

1.5 UNITS OF MEASURE ........................................................................................................................................... 7

1.6 PUBLICATIONS .................................................................................................................................................. 8

1.7 REVISION AND DISTRIBUTION .............................................................................................................................. 9

1.8 GARMIN TECHNICAL SUPPORT ............................................................................................................................. 9

2. SYSTEM DESCRIPTION ............................................................................................................................... 10

2.1 EQUIPMENT DESCRIPTIONS ............................................................................................................................... 10

2.2 SYSTEM INTERFACE SUMMARY ........................................................................................................................... 13

2.3 POWER REQUIREMENTS ................................................................................................................................... 14

2.4 ELECTRICAL BONDING ...................................................................................................................................... 14

3. CONTROL AND OPERATION ....................................................................................................................... 17

3.1 CONFIGURATION MODE OVERVIEW .................................................................................................................... 17

3.2 G1000 SYSTEM SOFTWARE INFORMATION .......................................................................................................... 22

3.3 CONFIGURATION MODE ................................................................................................................................... 23

3.4 G1000 HARDWARE/SOFTWARE COMPATIBILITY CHECK ......................................................................................... 23

3.5 EQUIPMENT VERIFICATION (THIRD PARTY/OPTIONAL EQUIPMENT DOCUMENTATION) ................................................. 23

3.6 CONFIGURATION CHECKLIST .............................................................................................................................. 27

3.7 G1000 SOFTWARE/CONFIGURATION PROCEDURE ................................................................................................ 28

3.8 SYSTEM SOFTWARE AND CONFIGURATION LOAD ................................................................................................... 29

3.9 AIRFRAME TRIM CALIBRATION CONFIRMATION ..................................................................................................... 39

3.10 FEATURE ENABLEMENT .................................................................................................................................... 40

3.11 CONFIGURATION MANAGER .............................................................................................................................. 43

3.12 CLEARING DEFAULT USER SETTINGS .................................................................................................................... 43

3.13 DATABASE LOADING ........................................................................................................................................ 43

3.14 CONFIGURATION OF NAVIGATION MAP FOR TRAFFIC SYSTEM .................................................................................. 45

3.15 FLIGHT STREAM 510 FIRMWARE REVIEW ............................................................................................................ 46

4. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS .................................................................................... 47

4.1 AIRWORTHINESS LIMITATIONS ........................................................................................................................... 47

4.2 SERVICING INFORMATION ................................................................................................................................. 47

4.3 MAINTENANCE INTERVALS ................................................................................................................................ 49

4.4 VISUAL INSPECTION ......................................................................................................................................... 50

4.5 ELECTRICAL BONDING TEST ............................................................................................................................... 51

5. TROUBLESHOOTING .................................................................................................................................. 53

5.1 SYSTEM ANNUNCIATIONS ................................................................................................................................. 54

5.2 AURAL & AUDIO ALERTS .................................................................................................................................. 55

5.3 GDU 105X TROUBLESHOOTING ........................................................................................................................ 55

5.4 GDU 105X ALERTS ......................................................................................................................................... 56

5.5 GMA 1360D TROUBLESHOOTING ..................................................................................................................... 57

5.6 GDL 69A SXM TROUBLESHOOTING ................................................................................................................... 58

5.7 GCU 475 TROUBLESHOOTING .......................................................................................................................... 59

5.8 SOFTWARE/CONFIGURATION TROUBLESHOOTING ................................................................................................. 60

5.9 CONNECTOR LAYOUT ....................................................................................................................................... 60

6. EQUIPMENT REMOVAL & INSTALLATION .................................................................................................. 61

6.1 GDU 1050A/1550 ....................................................................................................................................... 61

Garmin G1000 NXi System Maintenance Manual 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 4

6.2 GMA 1360D AUDIO PANEL ............................................................................................................................. 61

6.3 GTX 345R TRANSPONDER ............................................................................................................................... 62

6.4 GDL 69A SXM SATELLITE RECEIVER .................................................................................................................. 62

6.5 GCU 475 CONTROLLER ................................................................................................................................... 63

6.6 CONFIGURATION MODULES .............................................................................................................................. 63

7. GARMIN G1000 LRU REPLACEMENT/CONFIGURATION & TESTING ............................................................. 65

7.1 GIA BOOT BLOCK LOAD ................................................................................................................................... 65

7.2 GDU 1050A/1550 PFD & MFD ..................................................................................................................... 66

7.3 GMA 1360D AUDIO PANEL ............................................................................................................................. 70

7.4 GTX 345R TRANSPONDER ............................................................................................................................... 73

7.5 GDL 69A OR GDL 69A SXM DATA LINK ............................................................................................................ 75

7.6 GCU 475 FMS CONTROLLER ............................................................................................................................ 76

8. SUBSYSTEM FUNCTIONAL CHECKS............................................................................................................. 79

8.1 TAWS FUNCTIONAL CHECK .............................................................................................................................. 79

8.2 CHARTVIEW FUNCTIONAL CHECK ....................................................................................................................... 80

8.3 SAFETAXI FUNCTIONAL CHECK ........................................................................................................................... 81

8.4 LOW SPEED AWARENESS BAND CHECK ................................................................................................................ 82

8.5 DME FUNCTIONAL CHECK ................................................................................................................................ 83

8.6 ADF FUNCTIONAL CHECK ................................................................................................................................. 83

8.7 HF RADIO FUNCTION CHECK ............................................................................................................................. 84

8.8 KTA-870 TAS TRAFFIC SYSTEM FUNCTIONAL CHECK ............................................................................................. 85

9. G1000 SYSTEM RETURN TO SERVICE PROCEDURE ...................................................................................... 87

9.1 DISPLAY TEST ................................................................................................................................................. 87

9.2 DISPLAY FAILURE TEST ..................................................................................................................................... 90

9.3 REVERSION MODE CHECK ................................................................................................................................. 91

9.4 AIRCRAFT BASIC EMPTY WEIGHT INITIALIZATION ................................................................................................... 92

9.5 FIELD ELEVATION INITIALIZATION ........................................................................................................................ 93

9.6 EICAS VERIFICATION ....................................................................................................................................... 93

9.7 ROTARY TEST ................................................................................................................................................. 93

9.8 G1000 BACKUP PATH TEST .............................................................................................................................. 94

9.9 MAINTENANCE RECORDS .................................................................................................................................. 95

APPENDIX A - GARMIN UNIT PART AND SERIAL NUMBER CROSS REFERENCE ..................................................... 96

Garmin G1000 NXi System Maintenance Manual 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 5

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 ........................................................................................................ 44

FIGURE 5-1, AUX – SYSTEM STATUS PAGE ............................................................................................................................ 53

FIGURE 5-2, SYSTEM ANNUNCIATIONS ................................................................................................................................. 54

FIGURE 6-1, CONFIGURATION MODULE INSTALLATION ............................................................................................................ 63

FIGURE 7-1, G1000 NORMAL MODE CHECK ........................................................................................................................ 69

FIGURE 7-2, AIRCRAFT REGISTRATION .................................................................................................................................. 74

FIGURE 8-1, LOW SPEED AWARENESS BAND SYMBOLIZATION ................................................................................................... 82

FIGURE 9-1, MFD POWER UP PAGE .................................................................................................................................... 87

FIGURE 9-2, PFD POWER-UP SYSTEM ANNUNCIATIONS .......................................................................................................... 88

FIGURE 9-3, PFD NORMAL OPERATION ............................................................................................................................... 89

FIGURE 9-4, GDU REVERSIONARY MODE ............................................................................................................................. 91

FIGURE 9-5, BASIC EMPTY WEIGHT ENTRY ............................................................................................................................ 92

Garmin G1000 NXi System Maintenance Manual 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 6

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 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 7

1.4 Definitions/Abbreviations

ADI: Attitude Director Indicator

AML: Approved Model List

ARP: Aerospace Recommended Practice

ASTM: American Society for Testing and Materials

CDI: Course Deviation Indicator

CFR: Code of Federal Regulations

CWS: Control Wheel Steering

DDM: Difference in Depth of Modulation

DTK: Desired Track

FAA: Federal Aviation Administration

GPS: Global Positioning System

ICA: Instructions for Continued Airworthiness

ILS: Instrument Landing System

LRU: Line Replaceable Unit

MFD: Multifunction Flight Display

n/a: Not Applicable

NXi: Next Generation Integrated

OBS: Omni-Bearing Selector

PED: Personal Electronic Device

PFD: Primary Flight Display

PFT: Pre-Flight Test

SAE: Society of Automotive Engineers

SD: Secure Digital

SXM: SiriusXM

STC: Supplemental Type Certificate

VOR: VHF Omnidirectional Radio

1.5

Units of Measure

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

Garmin G1000 NXi System Maintenance Manual 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 8

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

190-00303-92 GDU 105X Installation Manual

190-00303-94 GDU 1550 Installation Manual

190-03813-00 GMA 1360 Installation Manual

190-01499-02 GTX 3X5 Transponder TSO Installation Manual

190-00500-00 G1000 Cessna Citation Mustang Line Maintenance Manual

Garmin G1000 NXi System Maintenance Manual 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 9

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 913-

397-8200, toll free 866-739-5687, or using around the world contact information on

https://fly.garmin.com/.

A Garmin Service Bulletin describing the revision to this document will be sent to Garmin

dealers if the revision is determined to be significant.

1.8

Garmin Technical Support

For technical support contact, Garmin Aviation Product Support at 913-397-8200 (toll free 866-

739-5687) or by using the around-the-world contact information on www.flygarmin.com.

Garmin G1000 NXi System Maintenance Manual 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 10

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

Equipment Descriptions

2.1.1 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 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 11

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 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 12

Figure 2-1 – GCU 475

Figure 2-2 – GDL 69A SXM

Figure 2-3 – GDU 1050A

Figure 2-4 – GDU 1550

Figure 2-5 – GMA 1360D

Figure 2-6 – GTX 345R

Figure 2-7 – FS 510

Garmin G1000 NXi System Maintenance Manual 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 13

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.

GDU 1050A [1]

(Primary Flight

Display)

GIA 63W [2]

COM,

GPS,

VOR/LOC,

G/S,

Flight

Director

GIA 63W [1]

COM,

GPS,

VOR/LOC,

G/S,

Flight

Director

GDU 1050A [2]

(Primary Flight

Display)

GDL 69A SXM

(XM/Weather

Datalink)

GMA 1360D

[1]

(Audio Panel)

GMC 710

(AFCS Mode Controller)

HSDB

Legacy Garmin

Equipment

Standard

GMA 1360D

[2]

(Audio Panel)

GDU 1550 [3]

(Multifunction

Display)

HSDB

232

HSDB

Digital

Bus

GSD 41

(Data

Concentrator)

GWX 68

(Weather Radar)

Non-Garmin Equipment

Standard

Audio

NAV

COM

GPS / XM

to GPS / XM

Antenna

To

GDL 69A SXM

HSDB

Over 232

Legacy Garmin

Equipment

Optional

HSDB

MKR

BCN

COM

coupler

2

3

1

2

3

4

1

HSDB

232

GTX 33D [1]

(Transponder)

GTX 33D [2]

(Transponder)

Analog

Audio

TO

GMA1/2

Audio

232

ARINC 429

1

GSA 81 (Roll)

3

4

HSDB over RS-232

HSDB

HSDB over Ethernet

HSDB Over 23 2

429

RS-485

485

RS-232

232

HSDB over RS-422

HSDB Over 42 2

Non-Garmin Equipment

Optional

GSA 80 (Yaw)

GSA 81(Pitch Trim)

GSA 81 (Pitch)

GPS

GCU 475

(FMS Controller)

232

HSDB

ADF

DME1

TAS

KHF 1050

HF Radio

Audio

Audio Audio

GDL69A

Audio Audio

G/S

coupler

HSDB

Over 232

GEA 71 [1]

(Engine & Airframe)

485

GEA 71 [2]

(Engine & Airframe)

485 485

485

ELT

C406-N

429

Becker ADF

KN 63 DME

FADEC

LB / RB

GRS 77 #1

GRS 77 #2

AHRS

232

429

GDC 74B #2

Air Data Compu ter

232

429

232

GRS 77 #2

GRS 77 #1

AHRS

232

429

GDC 74B #1

Air Data Compu ter

232

429

232

429

GMU 44

Magnetometer

232

485

GMU 44

Magnetometer

232

485

429

FADEC

LA / RA

429

GTX 345R [2]

(ADS-B

Transponder)

HSDB

232

To

#2 GIA 6W

232

422

Analog Audio

Suppression

HSDB

New Garmin

Equipment

Standard

New Garmin

Equipment

Optional

Audio

717

ARINC 717

1

2

4

3

HSDB

Diagnostics

To

PFD1

To

MFD

To

PFD2

429

From GDC1

429

From GDC1

From GRS1

429

From GRS2

From GDC2

Figure 2-8 – G1000 NXi System Overview

Garmin G1000 NXi System Maintenance Manual 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 14

2.3 Power Requirements

Table 2-1 below summarizes the power requirements for the LRUs installed by this STC.

Table 2-1 – Power Requirements

LRU

Characteristics

Specifications

Notes

GCU 475 Max Current Draw @ 28 VDC 0.05 A

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

2.4 Electrical Bonding

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

Maximum Resistance Between LRU

Equipment Chassis and Ground

Reference (mΩ)

Periodic Test

Reconditioned

Metallic Airframe

Nearby metal structure for

servos

or

Instrument panel for LRU

30.0 for PFD1,

MFD, PFD2, GMC

30 for PFD1, MFD,

PFD2, GMC

5 for GMA 1360D

(if installed) or GTX

345R (if installed)

2.5 for GMA

1360D (if installed)

or GTX 345R (if

installed)

2.4.1 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 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 15

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 190-02450-01

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Page 16

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 high-

resistance 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-L-

20A 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 190-02450-01

Textron Aviation Inc. Model 510 Citation Mustang Revision 2

Page 17

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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Page 18

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 190-02450-01

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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

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Garmin G1000 NXi - Cessna Citation Mustang Owner's manual

Garmin G1000 NXi - Cessna Citation Mustang Owner's manual

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