Garmin G900X Pilot’s Guide

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Page 1

Integrated Flight Deck

G900X

Pilot’s Guide

Page 2

This manual reﬂects the operation of System Software version 718.00 or later. Some differences in operation may be observed when comparing the information in this manual to earlier or later software versions.

Garmin International, Inc., 1200 East 151st Street, Olathe, Kansas 66062, U.S.A. Tel: 913/397.8200 Fax: 913/397.8282

Garmin AT, Inc., 2345 Turner Road SE, Salem, OR 97302, U.S.A. Tel: 503/391.3411 Fax: 503/364.2138

Garmin (Europe) Ltd., Unit 5, The Quadrangle, Abbey Park Industrial Estate, Romsey, Hampshire S051 9DL, U.K Tel: 44/0870.8501241 Fax: 44/0870.8501251

Garmin Corporation, No. 68, Jangshu 2nd Road, Shijr, Taipei County, Taiwan Tel: 886/02.2642.9199 Fax: 886/02.2642.9099

Website Address: www.garmin.com

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 written permission 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 for personal use, 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® is a registered trademark of Garmin Ltd. or its subsidiaries, and G900X™, FliteCharts™, and SafeTaxi™ are trademarks of Garmin Ltd. or its subsidiaries. These trademarks may not be used without the express permission of Garmin.

NavData® is a registered trademark of Jeppesen, Inc.; Avidyne® and TCAD® are registered trademarks of Avidyne Corporation; S-TEC® is a

registered trademark of S-TEC; CO Guardian is a trademark of CO Guardian, Inc.; and XM

is a registered trademark of XM Satellite Radio,

Inc.

April 2007 Printed in the U.S.A

Garmin G900X Pilot’s Guide

190-00726-00 Rev. A

Page 3

LIMITED WARRANTY

This Garmin product is warranted to be free from defects in materials or workmanship for two years from the date of purchase. Within this period, Garmin will, at its sole option, repair or replace any components that fail in normal use. Such repairs or replacement will be made at no charge to the customer for parts and labor, provided that the customer shall be responsible for any transportation cost. This warranty does not cover failures due to abuse, misuse, accident, or unauthorized alterations or repairs.

THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES EXPRESS OR IMPLIED OR STATUTORY, INCLUDING ANY LIABILITY ARISING UNDER ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE, STATUTORY OR OTHERWISE. THIS WARRANTY GIVES YOU SPECIFIC LEGAL RIGHTS, WHICH MAY VARY FROM STATE TO STATE.

IN NO EVENT SHALL GARMIN BE LIABLE FOR ANY INCIDENTAL, SPECIAL, INDIRECT OR CONSEQUENTIAL DAMAGES, WHETHER RESULTING FROM THE USE, MISUSE, OR INABILITY TO USE THIS PRODUCT OR FROM DEFECTS IN THE PRODUCT. Some states do not allow the exclusion of incidental or consequential damages, so the above limitations may not apply to you.

Garmin retains the exclusive right to repair or replace the unit or software, or to offer a full refund of the purchase price, at its sole discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF WARRANTY.

Products sold through online auctions are not eligible for rebates or other secial offers from Garmin. Online auction conﬁrmations are not accepted for warranty veriﬁcation. To obtain warranty service, an original copy of the sales receipt from the original retailer is required. Garmin will not replace missing components from any package purchased through an online auction.

To obtain warranty service, contact your local Garmin Authorized Service Center. For assistance in locating a Service Center, visit the Garmin website at

Garmin International, Inc., 1200 East 151st Street, Olathe, Kansas 66062, U.S.A. Toll free: 800/800.1020 Tel: 913/397.8200 Fax: 913/397.8282

Garmin AT, Inc., 2345 Turner Road SE, Salem, OR 97302, U.S.A. Toll free: 800/525.6726 Tel: 503/391.3411 Fax: 503/364.2138

Garmin (Europe) Ltd., Unit 5, The Quadrangle, Abbey Park Industrial Estate, Romsey, Hampshire S051 9DL, U.K Toll free (within U.K.): 0808 238 0000 Tel: 44/0870.8501241 Fax: 44/0870.8501251

www.garmin.com

or contact Garmin Customer Service at one of the numbers listed below:

Refer to the G900X Installation Manual for warranty registration instructions.

190-00726-00 Rev. A

Note: Record product serial numbers on reverse side and retain for your records.

Garmin G900X Pilot’s Guide

Page 4

LIMITED WARRANTY

List all Garmin products and serial numbers and retain this document for your records.

Product Serial Number

Garmin G900X Pilot’s Guide

190-00726-00 Rev. Aii

Page 5

WARNINGS, CAUTIONS, AND NOTES

WARNING:

To reduce the risk of unsafe operation, carefully review and understand all aspects of the G900X Pilot’s Guide documentation. Thoroughly practice basic operation prior to actual use. During ﬂight operations, carefully compare indications from the G900X to all available navigation sources, including the information from other NAVAIDs, visual sightings, charts, etc. For safety purposes, always resolve any discrepancies before continuing navigation.

WARNING:

The Garmin G900X has a very high degree of functional integrity. However, the pilot must recognize that providing monitoring and/or self-test capability for all conceivable system failures is not practical. Although unlikely, it may be possible for erroneous operation to occur without a fault indication shown by the G900X. It is thus the responsibility of the pilot to detect such an occurrence by means of cross-checking with all redundant or correlated information available in the cockpit.

WARNING:

For safety reasons, G900X operational procedures must be learned on the ground.

The United States government operates the Global Positioning System and is solely responsible for its accuracy and maintenance. The GPS system is subject to changes which could affect the accuracy and performance of all GPS equipment. Portions of the Garmin G900X utilize GPS as a precision electronic NAVigation AID (NAVAID). Therefore, as with all NAVAIDs, information presented by the G900X can be misused or misinterpreted and, therefore, become unsafe.

WARNING:

The altitude calculated by G900X GPS receivers is geometric height above Mean Sea Level and could vary signiﬁcantly from the altitude displayed by pressure altimeters, such as the GDC 74A Air Data Computer, or other altimeters in aircraft. GPS altitude should never be used for vertical navigation. Always use pressure altitude displayed by the G900X PFD or other pressure altimeters in aircraft.

WARNING:

The displayed minimum safe altitudes (MSAs) are only advisory in nature and should not be relied upon as the sole source of obstacle and terrain avoidance information. Always refer to current aeronautical charts for appropriate minimum clearance altitudes.

WARNING:

Navigation and terrain separation must NOT be predicated upon the use of the terrain function. The G900X Terrain Proximity feature is NOT intended to be used as a primary reference for terrain avoidance and does not relieve the pilot from the responsibility of being aware of surroundings during ﬂight. The Terrain Proximity feature is only to be used as an aid for terrain avoidance and is not certiﬁed for use in applications requiring a certiﬁed terrain awareness system. Terrain data is obtained from third party sources. Garmin is not able to independently verify the accuracy of the terrain data.

WARNING:

Do not use outdated database information. Databases used in the G900X System must be updated regularly in order to ensure that the information remains current. Pilots using any outdated database do so entirely at their own risk.

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Garmin G900X Pilot’s Guide

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Page 6

WARNINGS, CAUTIONS, AND NOTES

WARNING:

Do not use basemap (land and water data) information for primary navigation. Basemap data is intended only to supplement other approved navigation data sources and should be considered as an aid to enhance situational awareness.

WARNING:

Trafﬁc information shown on the G900X Multi Function Display is provided as an aid in visually acquiring trafﬁc. The aircraft should be maneuvered based only upon ATC guidance or positive visual acquisition of conﬂicting trafﬁc.

WARNING:

XM Weather should not be used for hazardous weather penetration. Weather information

provided by the GDL 69/69A is approved only for weather avoidance, not penetration.

WARNING:

NEXRAD weather data is to be used for long-range planning purposes only. Due to inherent delays in data transmission and the relative age of the data, NEXRAD weather data should not be used for short-range weather avoidance.

WARNING

Do not use the G900X to attempt to penetrate a thunderstorm. Both the FAA Advisory Circular, Subject: Thunderstorms, and the Airman’s Information Manual (AIM) recommend avoiding “by at least 20 miles any thunderstorm identiﬁed as severe or giving an intense radar echo.”

CAUTION:

The Garmin G900X does not contain any user-serviceable parts. Repairs should only be made by an authorized Garmin service center. Unauthorized repairs or modiﬁcations could void both the warranty and the pilot’s authority to operate this device under FAA/FCC regulations.

CAUTION:

The GDU 1040 PFD and MFD displays use a lens coated with a special anti-reﬂective coating that is very sensitive to skin oils, waxes, and abrasive cleaners. CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI-REFLECTIVE COATING. It is very important to clean the lens using a clean, lint-free cloth and an eyeglass lens cleaner that is speciﬁed as safe for anti-reﬂective coatings.

NOTE:

All visual depictions contained within this document, including screen images of the G900X panel and displays, are for example only, are subject to change, and may not reﬂect the most current G900X System. Depictions of equipment may differ slightly from the actual equipment.

NOTE: The GDU 1040 PFD/MFD may require a warm-up time of up to 30 minutes when exposed to -40˚C for an

extended period. A warm-up time of up to 15 minutes may be required when exposed to -30˚C for an extended period.

NOTE:

This device complies with part 15 of the FCC Rules. Operation is subject to the following two conditions: (1) this device may not cause harmful interference, and (2) this device must accept any interference received, including interference that may cause undesired operation.

Garmin G900X Pilot’s Guide

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Page 7

WARNINGS, CAUTIONS, AND NOTES

NOTE

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. For additional information, refer to the website at www.garmin.com/prop65.

NOTE:

Interference from GPS repeaters operating inside nearby hangars can cause an intermittent loss of attitude and heading displays while the aircraft is on the ground. Moving the aircraft more than 100 feet away from the source of the interference should alleviate the condition.

190-00726-00 Rev. A

Garmin G900X Pilot’s Guide

Page 8

REVISION INFORMATION

Record of Revisions

Part Number

190-00726-00 A 04/04/07 i – I-6 Initial release

Revision Date Page Range Description

Garmin G900X Pilot’s Guide

190-00726-00 Rev. Avi

Page 9

TABLE OF CONTENTS

SECTION 1 SYSTEM OVERVIEW

1.1 Line Replaceable Units ........................................1-2

1.2 Secure Digital (SD) Cards ....................................1-7

1.3 System Power-up ..................................................1-8

1.4 System Operation .................................................1-9

Display Operation ......................................................1-9

G900X System Annunciations ...................................1-10

System Status ..........................................................1-11

AHRS Operation ......................................................1-13

GPS Receiver Operation ...........................................1-14

1.5 G900X

Controls ..................................................1-18

PFD/MFD Controls ...................................................1-18

MFD/PFD Control Unit (Optional) ..............................1-20

Softkey Function ......................................................1-22

1.6 Accessing G900X Functionality ........................1-28

Menus ....................................................................1-28

Data Entry ..............................................................1-28

Page Groups ...........................................................1-30

System Settings .......................................................1-34

System Utilities ........................................................1-42

Electronic Checklists (Optional) ................................. 1-46

1.7 Display Backlighting .......................................... 1-48

SECTION 2 FLIGHT INSTRUMENTS

2.1 Flight Instruments ................................................2-4

Airspeed Indicator .....................................................2-4

Attitude Indicator ......................................................2-6

Altimeter ..................................................................2-7

Vertical Speed Indicator (VSI) ......................................2-8

Vertical Deviation, Glideslope, and Glidepath Indicators 2-9

Horizontal Situation Indicator (HSI) ...........................2-10

Course Deviation Indicator (CDI) ............................... 2-15

2.2 Supplemental Flight Data .................................2-22

Generic Timer ..........................................................2-22

Outside Air Temperature ...........................................2-23

Wind Data ..............................................................2-23

System Time ............................................................2-24

Vertical Navigation (VNV) Indications ........................ 2-25

2.4 PFD Annunciations and Alerting Functions .....

System Alerting .......................................................2-26

Trafﬁc Annunciation ................................................. 2-27

TAWS Annunciations (Optional) ................................2-27

2-26

Marker Beacon Annunciations ..................................2-28

Altitude Alerting ...................................................... 2-28

Low Altitude Annunciation .......................................2-29

Minimum Descent Altitude/Decision Height Alerting ...2-29

2.5 Abnormal Operations ........................................

Abnormal GPS Conditions ........................................2-31

Unusual Attitudes .................................................... 2-32

2-31

SECTION 3 ENGINE INDICATION SYSTEM

3.1 EIS Display .............................................................3-3

3.2 Engine Page ..........................................................3-8

Electrical .................................................................3-13

Temperatures ..........................................................3-14

CO Alert Reset (Optional) ......................................... 3-14

Fuel Calculations ..................................................... 3-15

3.3 Leaning Assist Mode .......................................... 3-17

Turbocharged .......................................................... 3-17

Normally-aspirated ..................................................3-18

3.4 EIS Display in Reversionary Mode ....................

Lean Display ...........................................................3-21

System Display ........................................................ 3-26

3-19

SECTION 4 AUDIO PANEL AND CNS

4.1 Overview ...............................................................4-1

PFD/MFD Controls and Frequency Display ....................4-2

Audio Panel Controls .................................................4-4

4.2 COM Operation .....................................................4-6

COM Transceiver Selection and Activation ....................4-6

COM Transceiver Manual Tuning .................................4-7

Quick-Tuning and Activating 121.500 MHz ...................4-8

Auto-Tuning the COM Frequency .................................4-9

Frequency Spacing ................................................... 4-13

Automatic Squelch ...................................................4-14

Volume ...................................................................4-14

4.3 NAV Operation ....................................................4-15

NAV Radio Selection and Activation ..........................4-15

NAV Receiver Manual Tuning ....................................4-16

Auto-Tuning the NAV Frequency ................................4-18

Marker Beacon Receiver ...........................................4-23

4.4 GTX 33 Mode S Transponder .............................4-24

Transponder Controls ...............................................4-24

Transponder Mode Selection ..................................... 4-25

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TABLE OF CONTENTS

Entering a Transponder Code ....................................4-27

IDENT Function .......................................................4-29

4.5 Additional Audio Panel Functions ....................4-30

Power-Up ................................................................4-30

Mono/Stereo Headsets .............................................4-30

Speaker ..................................................................4-30

Intercom .................................................................4-31

Passenger Address (PA) System .................................4-32

Clearance Recorder and Player ..................................4-33

Entertainment Inputs ...............................................4-34

4.6 Audio Panel Preﬂight Procedure ......................4-35

4.7 Abnormal Operation ..........................................4-36

Stuck Microphone ....................................................4-36

COM Tuning Failure ..................................................4-36

Audio Panel Fail-Safe Operation ................................ 4-36

Reversionary Mode ..................................................4-36

SECTION 5 GPS NAVIGATION

5.1 Introduction .......................................................... 5-1

5.2 Navigation Map (MFD) ........................................5-2

No-eis Option ............................................................5-4

Navigation Map Setup .............................................5-10

5.3 PFD Inset Map and Windows ............................5-35

Inset Map ...............................................................5-35

PFD Windows ..........................................................5-37

5.4 Direct-to-Navigation (MFD) .............................5-38

Selecting a Direct-to Waypoint ..................................5-39

Clearing Vertical Constraints ....................................5-41

Specifying a Course to a Waypoint ............................5-42

Canceling Direct-to Navigation ................................5-42

Direct-to Navigation Shortcuts .................................5-43

Direct-to Navigation Shortcuts Using the FMS Knob ....5-44

5.6 Direct-to-Navigation (PFD) ..............................5-46

Operations ..............................................................5-46

5.7 Airport Information (MFD) ................................

5-50

5.8 Intersection Information (MFD) ........................5-55

5.9 NDB Information (MFD) ..................................... 5-57

5.10 VOR Information (MFD) ..................................... 5-59

5.11 User Waypoint Information (MFD) ...................5-61

5.12 Nearest Airports (MFD) .....................................5-65

5.13 Nearest Intersections (MFD) .............................5-68

5.14 Nearest NDB (MFD) ............................................5-69

5.15 Nearest VOR (MFD) ............................................5-70

5.16 Nearest User Waypoint (MFD) ..........................5-72

5.17 Nearest Frequencies (MFD) ...............................5-74

5.18 Nearest Airspaces (MFD) ...................................5-77

General Notes on Airspace Alerts ..............................5-78

Airspace Type and Controlling Agency ....................... 5-79

General Notes on Associated Frequencies ..................5-80

5.19 Nearest Airports (PFD) .......................................

Operations ..............................................................5-81

5-81

5.20 Flight Planning (MFD) .......................................5-83

Flight Planning Operations .......................................5-83

Airways/Jetways ......................................................5-93

Display of Airways on the Flight Plan Page ...............5-101

Vertical Navigation (VNV) ....................................... 5-104

Navigating an Example Flight Plan ..........................5-112

Parallel Track (PTK) ................................................5-140

light Planning (PFD) ......................................5-143

5.21 F

Operations ............................................................5-143

5.22 Procedures

Leg Types Supported by the G900X .........................5-148

Departures ............................................................5-149

5.23 Procedures

(MFD) .............................................5-148

(PFD) ..............................................5-161

5.24 Abnormal Operation ........................................ 5-166

Dead Reckoning ....................................................5-166

SECTION 6 HAZARD AVOIDANCE

6.1 XM Satellite Weather (Optional) ........................6-1

Activating Services ..................................................... 6-1

Using XM Satellite Weather Products ...........................6-3

6.2 Terrain Proximity ................................................6-25

Displaying Terrain Proximity Data ..............................6-26

Terrain Proximity Page ..............................................6-28

6.3 Terrain Awareness and Warning System (TAWS

- Optional) .....................................................................6-30

Displaying TAWS Data ..............................................6-31

TAWS Page .............................................................6-33

TAWS Alerts ............................................................6-35

System Status ..........................................................6-41

6.4 Trafﬁc Information Service (TIS) .......................

Displaying TRAFFIC Data ..........................................6-43

6-42

Garmin G900X Pilot’s Guide

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Trafﬁc Map Page ......................................................6-45

TIS Alerts ................................................................6-46

System Status ..........................................................6-47

6.5 Avidyne TAS600-series Trafﬁc Advisory System

(Optional) ......................................................................6-50

Displaying TRAFFIC Data ..........................................6-51

Trafﬁc Map Page ......................................................6-53

TAS Alerts ...............................................................6-55

System Status ..........................................................6-56

SECTION 7 AUTOMATIC FLIGHT CONTROL SYSTEM

SECTION 8 ADDITIONAL FEATURES

8.1 SafeTaxi .................................................................8-1

SafeTaxi Cycle Number and Revision ...........................8-4

8.2 ChartView ..............................................................8-7

ChartView Softkeys ....................................................8-7

Terminal Procedures Charts ........................................8-8

Chart Options ..........................................................8-18

Day/Night View .......................................................8-23

ChartView Cycle Number and Expiration Date ............8-25

8.3 FliteCharts ...........................................................8-29

FliteCharts Softkeys .................................................8-29

Terminal Procedures Charts ......................................8-30

Chart Options ..........................................................8-38

Day/Night View .......................................................8-41

FliteCharts Cycle Number and Expiration Date ............ 8-43

8.4 XM Radio Entertainment (Optional) ................8-47

Activating XM Satellite Radio Services ....................... 8-47

Using XM Radio ......................................................8-49

8.5 Abnormal Operation ..........................................8-53

TABLE OF CONTENTS

Annunciations and Alerts ..............................................A-1

SD Card Use and Databases ..........................................B-1

Glossary ...........................................................................C-1

Frequently Asked Questions .........................................D-1

General TIS Information ................................................ F-1

Map Symbols ................................................................. G-1

190-00726-00 Rev. A

APPENDICES

INDEX

Garmin G900X Pilot’s Guide

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TABLE OF CONTENTS

BLANK PAGE

Garmin G900X Pilot’s Guide

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Page 13

SYSTEM OVERVIEW

SECTION 1 SYSTEM OVERVIEW

The G900X Integrated Flight Deck System presents ﬂight instrumentation, position, navigation, communication, and identiﬁcation information to the pilot using ﬂat-panel color displays. The system is distributed across the following Line Replaceable Units (LRUs):

•

GDU 1040

•

GDU 1040

•

GMA 1347

Beacon Receiver

•

GIA 63W

•

GDC 74A

Figure 1-1 shows interactions between the LRUs. Additional/optional equipment are shown in Figure 1-2. The G900X is capable of interfacing with the following optional equipment:

•

GCU 476

Primary Flight Display (PFD)

Multi Function Display (MFD)

Audio Panel with Integrated Marker

Integrated Avionics Units (IAU)

Air Data Computer (ADC)

MFD/PFD Control Unit

•

GEA 71

•

GTX 33

•

GRS 77

(AHRS)

•

GMU 44

• TruTrak Digiﬂight I/Sorecerer/DFC Series autopilots

Engine/Airframe Unit

Mode S Transponder

Attitude and Heading Reference System

Magnetometer

•

GDL 69A

• CO Guardian Aero 353R/452R Remote Carbon

Monoxide Detector

• Avidyne TAS600-series Trafﬁc Advisory System

• Artex ELT 406-N Emergency Locator Transmitter

• S-TEC 55X Autopilot

Data Link Receiver

• TruTrak Digiﬂight II-series autopilots

• TruTrak Digitrak/Pictorial Pilot autopilots

• TruTrak Altrak Altitude Hold Autopilot

• TruTrak ADI

• Trio Avionics EZ Pilot Autopilot

• Trio Avionics EZ Altitude Control Autopilot

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Garmin G900X Pilot’s Guide

1-1

Page 14

SYSTEM OVERVIEW

1.1 LINE REPLACEABLE UNITS

• GDU 1040 (2) – The left-hand GDU is conﬁgured as a Primary Flight Display (PFD) and the right-hand GDU as a Multi Function Display (MFD). Both feature 10.4-inch LCD screens with 1024 x 768 resolution. The displays communicate with each other through a High-Speed Data Bus (HSDB) Ethernet connection. Each display is also paired with an Ethernet connection to an IAU.

•

GMA 1347

and marker beacon controls, and is installed between the displays. This unit also provides manual control of display reversionary mode (red with both IAUs using an RS-232 digital interface.

– The Audio Panel integrates navigation/communication radio (NAV/COM) digital audio, intercom,

DISPLAY BACKUP

Button; see Section 1.5, System Operation) and communicates

• GIA 63W (2) – The Integrated Avionics Units (IAU) function as the main communication hubs, linking all LRUs with the on-side display. Each IAU contains a GPS WAAS receiver, VHF COM/NAV/GS receivers, and system integration microprocessors, and is paired with the on-side display via HSDB connection. The IAUs are not paired together and do not communicate with each other directly.

Garmin G900X Pilot’s Guide

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Page 15

SYSTEM OVERVIEW

•

GDC 74A

(OAT) sensor. The ADC provides pressure altitude, airspeed, vertical speed, and OAT information to the G900X System, and it communicates with the primary IAU, displays, and AHRS using an ARINC 429 digital interface.

•

GEA 71

unit communicates with both IAUs using an RS-485 digital interface.

– The Air Data Computer (ADC) processes data from the pitot/static system and outside air temperature

– The Engine Airframe Unit receives and processes signals from the engine and airframe sensors. This

•

GTX 33

through an RS-232 digital interface.

•

GRS 77

via ARINC 429 to both the PFD and the primary IAU. The AHRS contains advanced sensors (including accelerometers and rate sensors) and interfaces with the Magnetometer to obtain magnetic ﬁeld information, with the ADC to obtain air data, and with both IAUs to obtain GPS information. AHRS operation is discussed in Section 1.4, System Operation.

– The solid-state Transponder provides Modes A, C, and S capability and communicates with both IAUs

– The Attitude and Heading Reference System (AHRS) provides aircraft attitude and heading information

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SYSTEM OVERVIEW

•

GMU 44

determine aircraft magnetic heading. This unit receives power directly from the AHRS and communicates with it via an RS-485 digital interface.

•

GCU 476

interface

– The Magnetometer measures local magnetic ﬁeld and sends data to the AHRS for processing to

– The optional Control Unit provides MFD/PFD and radio tuning control through an RS-232 digital

•

GDL 69A

G900X MFD and PFD Inset Map, as well as digital audio entertainment. The Data Link Receiver communicates with the MFD via a HSDB connection. A subscription to XM Satellite Radio Service is required to enable the GDL 69A capability.

– The optional Data Link Satellite Radio Receiver provides real-time weather information to the

Garmin G900X Pilot’s Guide

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Page 17

SYSTEM OVERVIEW

GTX 33

Transponder

Reversionary

Control

GEA 71

Engine/Airframe

Unit

GDC 74A

Air Data

Computer

OAT

Airspeed

Altitude

rtical Speed

GMU 44

Magnetometer

Heading

Reversionary

Control

GMA 1347

Audio Panel

No. 2 GIA 63W

Integrated Avionics Unit

System Integration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS

Glideslope

GPS Output

No. 1 GIA 63W

Integrated Avionics Unit

System Inegration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS

Glideslope

GPS Output

GRS 77

AHRS

Attitude

Rate of Turn

Slip/Skid

GDU 1040

Primary Flight Display

GDU 1040

Multi Function Display

Figure 1-1 Basic G900X System Block Diagram

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SYSTEM OVERVIEW

Avidyne

TAS600-series

Provides Traffic

Information

(optional)

CO Guardian

Carbon Monoxide

Detection (optional)

STEC/

TruTrak/

Trio

Autopilot

(optional)

ELT

Emergency Locator

Transmitter

(optional)

No. 1 GIA 63W

Integrated Avionics Unit

System Integration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS

Glideslope

No. 2 GIA 63W

Integrated Avionics Unit

System Integration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS

Glideslope

GDL 69A

Data Link

Real-time Weather and

Digital Audio Entertainment

(optional,

subscription-based service)

GCU 476

MFD/PFD Control Unit

(optional)

NOTE:

For information on non-Garmin optional/additional equipment shown in Figure 1-2, consult the applicable optional interface user’s guide. This document assumes that the reader is already familiar with the operation of this additional equipment.

Figure 1-2 G900X With Optional/Additional Equipment

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SYSTEM OVERVIEW

1.2 SECURE DIGITAL (SD) CARDS

NOTE:

Ensure the G900X System is powered off before inserting an SD card.

NOTE:

Refer to Appendix B for instructions on updating the aviation database.

The PFD and MFD data card slots use Secure Digital (SD) cards and are located on the upper right side of the

display bezels. Each display bezel is equipped with two SD card slots. SD cards are used for aviation database and system software updates as well as terrain database storage.

Installing an SD card:

1) Insert the SD card in the SD card slot (the front of the card should be ﬂush with the face of the display bezel).

2) To eject the card, gently press on the SD card to release the spring latch.

SD Card Slots

Figure 1-3 Display Bezel SD Card Slots

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SYSTEM OVERVIEW

1.3 SYSTEM POWER-UP

NOTE:

The G900X System is integrated with the aircraft electrical system and receives power directly from electrical busses. The PFD, MFD, and supporting sub-systems include both power-on and continuous built-in test features that exercise the processor, RAM, ROM, external inputs, and outputs to provide safe operation.

During system initialization, test annunciations are displayed, as shown in Figure 1-4. All system annunciations should disappear typically within the ﬁrst minute of power-up. Upon power-up, key annunciator lights also become momentarily illuminated on the Audio Panel, the MFD/PFD Control Unit, and the display bezels.

On the PFD, the AHRS begins to initialize and displays “AHRS ALIGN: Keep Wings Level”. The AHRS should display valid attitude and heading ﬁelds typically within the ﬁrst minute of power-up. The AHRS can align itself both while taxiing and during level ﬂight.

When the MFD powers up, the splash screen (Figure 1-5) displays the following information:

• System version

• Copyright

• Land database name and version

Current database information includes valid operating dates, cycle number, and database type. When this information has been reviewed for currency (to ensure that no databases have expired), the pilot is prompted to continue.

Refer to Appendix A for system-speciﬁc annunciations and alerts.

• Obstacle database name and version

• Terrain database name and version

• Aviation database name, version, and effective dates

Pressing the ENT Key (or right-most softkey) acknowledges this information, and the Navigation Map Page is displayed upon pressing the key a second time. When the system has acquired a sufﬁcient number of satellites to determine a position, the aircraft’s current position is shown on the Navigation Map Page.

Figure 1-4 PFD Initialization Figure 1-5 Example MFD Power-up Splash Screen

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1.4 SYSTEM OPERATION

SYSTEM OVERVIEW

NOTE:

Refer to Appendix A for detailed descriptions of all annunciations and alerts. The G900X System alerts the pilot when backup paths are utilized by the LRUs. The kitplane builder should establish appropriate pilot actions in response to all G900X annunciations in the aircraft-speciﬁc Pilot’s Operating Handbook (POH).

The displays are connected together via a single Ethernet bus for high-speed communication. As shown in Figure 1-1, each IAU is connected to the on-side display. This section discusses normal and reversionary G900X display operation, AHRS modes, GPS receiver operation, and G900X System Annunciations.

DISPLAY OPERATION

NOTE:

In normal operating mode, backlighting can only be adjusted from the PFD (see Section 1.7). In

reversionary mode, it can be adjusted from the remaining display.

In normal operating mode, the PFD presents graphical ﬂight instrumentation (attitude, heading, airspeed, altitude, vertical speed), replacing the traditional ﬂight instrument cluster (see the Flight Instruments Section for more information). The MFD normally displays a full-color moving map with navigation information (see the GPS Navigation Section), while the left portion of the MFD is dedicated to the Engine Indication System (EIS; see the EIS Section). Both displays offer control for COM and NAV frequency selection.

In the event of a display failure, the G900X System automatically switches to reversionary (backup) mode. In reversionary mode, all important ﬂight information is presented on the remaining display in the same format as in normal operating mode.

If a display fails, the appropriate IAU-display Ethernet interface is cut off. Thus, the IAU can no longer communicate with the remaining display (refer to Figure 1-1), and the NAV and COM functions provided to the failed display by the IAU are ﬂagged as invalid on the remaining display. The system reverts to backup paths for the AHRS, ADC, Engine/Airframe Unit, and Transponder, as required. The change to backup paths is completely automated for all LRUs and no pilot action is required.

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Figure 1-6 G900X Normal Operation

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SYSTEM OVERVIEW

If the system fails to detect a display problem, reversionary mode may be manually activated by pressing the Audio Panel’s red Pressing this button again deactivates reversionary mode.

DISPLAY BACKUP

Button (refer to the Audio Panel and CNS Section for further details).

NAV1 and COM1 (provided by the

failed PFD) Flagged Invalid

DISPLAY BACKUP

Deactivates Reversionary Mode on Both Displays

Button Manually Activates/

Figure 1-7 G900X Reversionary Mode (Failed PFD)

G900X SYSTEM ANNUNCIATIONS

When an LRU or an LRU function fails, a large red ‘X’ is typically displayed over the instrument experiencing failed data (Figure 1-8 displays all possible ﬂags and responsible LRUs). Upon G900X power-up, certain instruments remain invalid as equipment begins to initialize. All instruments should be operational within one minute of power-up. If any instrument remains ﬂagged, the G900X should be serviced by a Garmin-authorized repair facility.

GIA 63W Integrated

Avionics Units

GEA 71 Engine

Airframe Unit

GIA 63W Integrated

Avionics Unit

GIA 63W Integrated Avionics Units

GDC 74A Air Data Computer

GRS 77 AHRS OR GMU 44 Magnetometer

GDC 74A Air

Data Computer

Figure 1-8 G900X System Failure Annunciations

Garmin G900X Pilot’s Guide

GIA 63W Integrated Avionics Units

GTX 33 Transponder OR GIA 63W Integrated Avionics Units

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SYSTEM OVERVIEW

SYSTEM STATUS

The System Status Page displays the statuses, serial numbers, and software version numbers for all detected system LRUs. Active LRUs are indicated by green check marks; failed, by red ‘X’s. Failed LRUs should be noted and a service center or Garmin-authorized dealer informed.

Viewing LRU information:

1) Use the FMS Knob to select the AUX - System Status Page.

2) To place the cursor in the ‘LRU Info’ Box,

a) Select the LRU Softkey.

OR:

a) Press the MENU Key.

b) With ‘Select LRU Window’ highlighted, press the ENT Key.

3) Use the FMS Knob to scroll through the box to view LRU status information.

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Figure 1-9 Example System Status Page

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SYSTEM OVERVIEW

Pertinent information on all system databases is also displayed on this page. Refer to the Appendices and

Additional Features sections for more information about databases.

Viewing database information:

1) Use the FMS Knob to select the AUX - System Status Page.

2) To place the cursor in the ‘Database’ Box,

a) Select the DBASE Softkey.

OR:

a) Press the MENU Key.

b) Highlight ‘Select Dbase Window’ and press the ENT Key.

3) Use the FMS Knob to scroll through the box to view database status information.

The G900X uses aural tones to convey the priority of airframe-speciﬁc alerts. The alerting system’s annunciation

tone may be tested from the System Status Page. Refer to the Appendices for airframe-speciﬁc alerts.

Testing the system annunciation tone:

1) Use the FMS Knob to select the AUX - System Status Page.

2) Select the ANN TEST Softkey.

OR:

a) Press the MENU Key.

b) Highlight ‘Enable Annunciator Test Mode’ and press the ENT Key.

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AHRS OPERATION

Attitude/Heading Invalid

AHRS

no-GP

Mode

AHRS Normal

Operation

AHRS no-

Mag Mode

AHRS no-Mag/

no-Air Mode

Heading Invalid

available

unavailable

una

vailable

available

unavailable

available

Airspeed Data

Magnetometer

unavailable

available

GPS

SYSTEM OVERVIEW

NOTE:

Aggressive maneuvering while AHRS is not operating normally may degrade AHRS accuracy.

The Attitude and Heading Reference System (AHRS) performs attitude, heading, and vertical acceleration calculations for the G900X System, utilizing GPS, magnetometer, and air data in addition to information from its internal sensors. Attitude and heading information are updated on the PFD while the AHRS receives appropriate combinations of information from the external sensor inputs.

Loss of GPS, magnetometer, or air data inputs is communicated to the pilot by message advisory alerts. Any failure of the internal AHRS inertial sensors results in loss of attitude and heading information (indicated by red ‘X’ ﬂags over the corresponding ﬂight instruments).

Two GPS inputs are provided to the AHRS. If GPS information from one of the inputs fails, the AHRS uses the remaining GPS input and an alert message is issued to inform the pilot. If both GPS inputs fail, the AHRS can continue to provide attitude and heading information to the PFD as long as magnetometer and airspeed data are available and valid.

If the magnetometer input fails, the AHRS continues to output valid attitude information; however, the heading output on the PFD is ﬂagged as invalid with a red ‘X’.

Failure of the air data input has no effect on the AHRS output while AHRS is receiving valid GPS information. Invalid/unavailable airspeed data in addition to GPS failure results in loss of all attitude and heading information.

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Figure 1-10 AHRS Operation

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SYSTEM OVERVIEW

GPS RECEIVER OPERATION

Each Integrated Avionics Unit (IAU) contains a GPS receiver. Internal system checking is performed to ensure both GPS receivers are providing accurate data to the PFD. When both GPS receivers are providing accurate data, the GPS receiver producing the better solution is used by the system. Information collected by the speciﬁed receiver (GPS1 for the #1 IAU or GPS2 for the #2 IAU) may be viewed on the AUX - GPS Status Page.

Viewing GPS receiver status information:

1) Use the large FMS Knob on the MFD to select the Auxiliary Page Group (see Section 1.6 for information on

navigating MFD page groups).

2) Use the small FMS Knob to select GPS Status Page (third page in the AUX Page Group).

3) To change the selected GPS receiver:

Select the desired

OR:

a) Press the MENU Key.

b) Use the FMS Knob to highlight the receiver which is not selected and press the ENT Key.

GPS

Softkey.

Satellite Constellation

Diagram

Satellite Signal

Information

GPS Receiver Status

RAIM Availability Prediction

Figure 1-11 GPS Status Page

Garmin G900X Pilot’s Guide

Satellite Signal Strength Bars

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SYSTEM OVERVIEW

GPS sensor annunciations are most often seen after system power-up when one GPS receiver has acquired satellites before the other or one of the GPS receivers has not yet acquired a WAAS signal. While the aircraft is on the ground, the WAAS signal may be blocked by obstructions causing one GPS receiver to have difﬁculty acquiring a good signal. Also, while airborne, turning the aircraft may result in one of the GPS receivers temporarily losing the WAAS signal. If no failure message exists, check the GPS Status Page and compare the information for GPS1 and GPS2. Discrepancies may indicate a problem.

GPS RECEIVER STATUS

The GPS solution type (ACQUIRING, 2D NAV, 2D DIFF NAV, 3D NAV, 3D DIFF NAV) for the active GPS receiver (GPS1 or GPS2) is shown in the upper right of the GPS Status Page. When the receiver is in the process of acquiring enough satellite signals for navigation, the receiver uses satellite orbital data (collected continuously from the satellites) and last known position to determine the satellites that should be in view. ACQUIRING is indicated as the solution until a sufﬁcient number of satellites have been acquired for computing a solution.

When the receiver is in the process of acquiring a 3D navigational GPS solution, 3D NAV is indicated as the solution until the 3D differential ﬁx has ﬁnished acquisition. Satellite-Based Augmentation System (SBAS) status should be indicated as INACTIVE at this point. When acquisition is complete, the solution status changes to 3D DIFF NAV and SBAS becomes active.

In certain situations, such as when the aircraft is outside or on the fringe of the WAAS coverage area, it may be desirable to disable WAAS (although it is not recommended). When disabled, the SBAS ﬁeld in the GPS Status box indicates DISABLED.

Disabling WAAS:

1) Select the GPS Status Page.

2) Select the SBAS Softkey. The RAIM PREDICTION box is replaced by SBAS SELECTION.

3) Press the

4) Press the ENT Key to uncheck the box.

5) Press the FMS Knob to remove the cursor.

FMS

Knob

. ‘WAAS’ is highlighted.

Figure 1-12 Enable/Disable WAAS

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SYSTEM OVERVIEW

RAIM PREDICTION

Receiver Autonomous Integrity Monitoring (RAIM) is a GPS receiver function that performs a consistency check on all tracked satellites. RAIM ensures that the available satellite geometry allows the receiver to calculate a position within a speciﬁed RAIM protection limit (2.0 nautical miles for oceanic and enroute, 1.0 nm for terminal, and 0.3 nm for non-precision approaches). During oceanic, enroute, and terminal phases of ﬂight, RAIM is available nearly 100% of the time.

The RAIM prediction function also indicates whether RAIM is available at a speciﬁed date and time. RAIM computations predict satellite coverage within ±15 min of the speciﬁed arrival date and time. In most cases performing RAIM prediction is not necessary. However, in some cases, the selected approach may be outside the WAAS coverage area and it may be necessary to perform a RAIM prediction for the intended approach.

Because of the tighter protection limit on approaches, there may be times when RAIM is not available. The G900X automatically monitors RAIM and warns with an alert message when it is not available. If RAIM is not predicted to be available for the ﬁnal approach course, the approach does not become active, as indicated by the messages “Approach is not active”. If RAIM is not available when crossing the FAF, the missed approach procedure must be ﬂown.

Predicting RAIM availability:

1) Select the GPS Status Page.

2) Select the RAIM Softkey.

2) Press the

3) Turn the small FMS Knob to display the Waypoint Information Window.

4) Enter the desired waypoint and press the ENT Key (refer to Section 1.6 for instructions on data entry).

OR:

a) To use the present position, press the MENU Key.

b) With ‘Set WPT to Present Position’ highlighted, press the ENT Key.

c) Press the ENT Key to accept the waypoint entry.

5) Enter an arrival time and press the ENT Key.

6) Enter an arrival date and press the ENT Key.

7) With the cursor highlighting ‘COMPUTE RAIM?’, press the ENT Key. Once RAIM availability is computed, one

FMS

Knob

. The ‘WAYPOINT’ ﬁeld is highlighted.

of the following is displayed:

• ‘COMPUTE RAIM?’—RAIM has not been computed for the current waypoint, time, and date combination

• ‘COMPUTING AVAILABILITY’—RAIM calculation in progress

• ‘RAIM AVAILABLE’—RAIM is predicted to be available for the speciﬁed waypoint, time, and date

• ‘RAIM NOT AVAILABLE’—RAIM is predicted to be unavailable for the speciﬁed waypoint, time, and date

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SYSTEM OVERVIEW

SATELLITE INFORMATION

Satellites currently in view are shown at their respective positions on a satellite constellation diagram. This sky view is always oriented north-up, with the outer circle representing the horizon, the inner circle representing 45° above the horizon, and the center point showing the position directly overhead. Each satellite is represented by an oval containing the Pseudo-random noise (PRN) number (i.e., satellite identiﬁcation number). Satellites whose signals are currently being used are represented by solid ovals.

The GPS Status Page can be helpful in troubleshooting weak (or missing) signal levels due to poor satellite coverage or installation problems. As the GPS receiver locks onto satellites, a signal strength bar is displayed for each satellite in view, with the appropriate satellite PRN number (01-32 or 120-138 for WAAS) below each bar. The progress of satellite acquisition is indicated by signal bar appearance:

• No signal strength bar—Receiver is looking for the indicated satellite.

• Hollow signal strength bar—Receiver has found the satellite and is collecting data. Each satellite has a 30-

second data transmission that must be collected (signal strength bar is hollow) before the satellite may be

used for navigation (signal strength bar becomes solid).

• Solid signal strength bar—Receiver has collected the necessary data and the satellite signal can be used.

• Checkered signal strength bar—Receiver has excluded the satellite (Fault Detection and Exclusion; FDE).

• “D” indication on signal strength bar—Satellite is being used for differential computations.

Using the current satellite signal information, they system calculates the aircraft’s GPS position, time, altitude, ground speed, and track for the aircraft (displayed below the satellite signal accuracy measurements for reference). The following quantities denote the accuracy of the aircraft’s GPS ﬁx:

• Estimated Position Uncertainty (EPU)—A statistical error indication; the radius of a circle centered on an

estimated horizontal position in which actual position has 95% probability of lying

• Horizontal Dilution of Precision (HDOP)—Measures satellite geometry quality (i.e., number of satellites

received and where they are relative to each other) on a range from 0.0 to 9.9, with lower numbers denoting

better accuracy

• Horizontal and Vertical Figures of Merit (HFOM and VFOM)—Measures of horizontal and vertical position

uncertainty; the current 95% conﬁdence horizontal and vertical accuracy values reported by the GPS

receiver

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SYSTEM OVERVIEW

1.5 G900X CONTROLS

The G900X controls have been designed to simplify operation of the system and minimize workload and the time required to access sophisticated functionality. Controls are located on the PFD and MFD bezels, MFD/PFD Control Unit, and Audio Panel. PFD and MFD controls and softkeys are discussed in this section. Audio Panel controls are described in the Audio Panel and CNS section; see the Audio Panel and CNS Section for more information about NAV/COM controls.

PFD/MFD CONTROLS

NAV VOL/ID Knob

NAV Frequency Transfer Key

NAV Knob

Heading Knob

Figure 1-13 PFD/MFD Controls

Turn to control NAV audio volume (shown in the NAV Frequency Box as a

percentage)

Press to toggle Morse code identiﬁer audio ON/OFF

Transfers the standby and active NAV frequencies

Turn to tune NAV receiver standby frequencies (large knob for MHz; small for kHz) Press to toggle light blue tuning box between NAV1 and NAV2

Turn to manually select a heading Press to display a digital heading momentarily to the left of the HSI and synchronize

the Selected Heading to the and current heading

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SYSTEM OVERVIEW

Joystick

CRS/BARO Knob

COM Knob

COM Frequency Transfer Key (EMERG)

COM VOL/SQ Knob

Direct-to Key ( )

FPL Key

Turn to change map range Press to activate Map Pointer for map panning

Turn large knob for altimeter barometric pressure setting Turn small knob to adjust course (only when HSI is in VOR or OBS Mode) Press to re-center the CDI and return course pointer directly TO bearing of active

waypoint/station

Turn to tune COM transceiver standby frequencies (large knob for MHz; small for

kHz) Press to toggle light blue tuning box between COM1 and COM2 The selected COM (green) is controlled with the COM MIC Key (Audio Panel).

Transfers the standby and active COM frequencies Press and hold 2 seconds to tune the emergency frequency (121.5 MHz) automatically

into the active frequency ﬁeld

Turn to control COM audio volume level (shown as a percentage in the COM

Frequency Box) Press to turn the COM automatic squelch ON/OFF

Activates the direct-to function and allows the user to enter a destination waypoint

and establish a direct course to the selected destination (speciﬁed by identiﬁer,

chosen from the active route)

Displays ﬂight plan information

CLR Key (DFLT MAP)

MENU Key

PROC Key

ENT Key

FMS Knob

(Flight Management System Knob)

Softkey Selection Keys

ALT Knob

Erases information, cancels entries, or removes menus Press and hold to display the MFD Navigation Map Page (MFD only).

Displays a context-sensitive list of options for accessing additional features or making

setting changes

Gives access to IFR departure procedures (DPs), arrival procedures (STARs), and

approach procedures (IAPs) for a ﬂight plan or selected airport

Validates/conﬁrms menu selection or data entry

Press to turn the selection cursor ON/OFF. Data Entry: With cursor ON, turn to enter data in the highlighted ﬁeld (large

knob moves cursor location; small knob selects character for highlighted cursor

location) Scrolling: When a list of information is too long for the window/box, a scroll bar

appears, indicating more items to view. With cursor ON, turn large knob to scroll

through the list. Page Selection: Turn knob on MFD to select the page to view (large knob selects a

page group; small knob selects a speciﬁc page from the group)

Press to select softkey shown above the bezel key on the PFD/MFD display

Sets the Selected Altitude, shown above the Altimeter (the large knob selects the

thousands, the small knob selects the hundreds)

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SYSTEM OVERVIEW

The NAV, CRS/BARO, COM, FMS, and ALT knobs are concentric dual knobs, each having small (inner)

and large (outer) control portion. When a portion of the knob is not speciﬁed in the text, either may be used.

Large (Outer) Knob

Small (Inner) Knob

Figure 1-14 Dual Concentric Knob

MFD/PFD CONTROL UNIT (OPTIONAL)

The optional MFD/PFD Control Unit is a pedestal-mounted user interface allowing for ease of data entry, PFD/MFD operation, and NAV/COM tuning. Many procedures in this Pilot’s Guide can be performed using the MFD/PFD Control Unit rather than the display bezel controls. Indicators above the PFD, MFD, NAV, and COM keys are illuminated when their respective control mode(s) are selected. The unit is in MFD control mode by default on system power-up.

NAV/COM radio tuning can be accomplished in either PFD or MFD control mode. The appropriate frequency box on the selected display is outlined by a light blue selection box, which ﬂashes for a few seconds to indicate Control Unit activity (refer to the Audio Panel and CNS Section for more information about NAV/COM tuning). Selection of a different display control or radio tuning mode results in cancelation of the previous radio tuning mode.

Figure 1-15 GCU 476 MFD/PFD Control Unit (Optional)

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SYSTEM OVERVIEW

FPL Key

Direct-to Key ( )

Displays ﬂight plan information

Activates the direct-to function and allows the user to enter a destination waypoint

and establish a direct course to the selected destination (speciﬁed by identiﬁer, chosen from the active route)

MENU Key

Displays a context-sensitive list of options for accessing additional features or making

setting changes

PROC Key

Gives access to IFR departure procedures (DPs), arrival procedures (STARs), and

approach procedures (IAPs) for a ﬂight plan or selected airport

Joystick

Turn to change map range Press to activate Map Pointer for map panning

Alphanumeric Keys Allow data entry (rather than using the FMS Knob to select characters/numbers)

BKSP Key

SPC Key

ENT Key

CLR Key

Moves cursor back one character space and removes last character entered

Adds a space character

Validates or conﬁrms a menu selection or data entry

Erases information, cancels entries, or removes menus Press and hold to display the MFD Navigation Map Page (MFD only).

SEL Key

Arrows move light blue Softkey Selection Box (Figure 1-14) on selected display Press the center to activate the selected softkey

Decimal Key

Plus-Minus (±) Key

NAV Key

COM Key

Frequency Transfer Key (EMERG)

PFD Key

MFD Key

FMS/NAV-COM Knob

Enters a decimal point character

Toggles entry between the + and - characters

Selects/deselects NAV radio tuning mode on the MFD/PFD Control Unit

Selects/deselects COM radio tuning mode on the MFD/PFD Control Unit

Transfers between active and standby selected COM or NAV tuning frequencies Press and hold 2 seconds to tune the emergency frequency (121.5 MHz) automatically

into the active frequency ﬁeld

When selected, the MFD/PFD Control Unit can be used to access PFD functions

When selected, the MFD/PFD Control Unit can be used to access MFD functions

(default display control mode)

NAV/COM Tuning Modes PFD/MFD Control Modes

: Acts as the NAV or COM Knob

: Acts as the FMS Knob

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SYSTEM OVERVIEW

INSET

XPDR

IDENT

TMR/REF

NRST

ALERTS

OBS

PFD

CDI

Press the CDI Softkey to cycle through navigation sources

- GPS

- NAV1 (VOR/LOC)

- NAV2 (VOR/LOC)

SOFTKEY FUNCTION

The softkeys are located along the bottoms of the displays. The softkeys shown depend on the softkey level or page being displayed. The bezel keys below the softkeys can be used to select the appropriate softkey. When a softkey is selected, its color changes to black text on gray background and remains this way until it is turned off, at which time it reverts to white text on black background. When a softkey function is disabled, the softkey label is subdued (dimmed).

Softkeys revert to the previous level after 45 seconds of inactivity.

Softkey OnSoftkey Selection Box

(using Control Unit)

Bezel-Mounted Softkeys (Press)

Figure 1-16 Softkeys (Second-Level PFD Conﬁguration)

The MFD/PFD Control Unit can also be used to select softkeys.

Softkey Names (Displayed)

Selecting a softkey using the MFD/PFD Control Unit:

1) Choose the desired display control mode by pressing the PFD or MFD Key on the MFD/PFD Control Unit.

2) Move the Softkey Selection Box (the light blue outline around the softkey label) to the desired softkey using the

arrows of the SEL Key.

3) Press the center of the SEL Key to select the desired softkey.

In the following descriptions, top level softkeys are denoted by bullets.

PFD SOFTKEYS

The

CDI, IDENT, TMR/REF, NRST,

gray background and automatically switch back to white text on black background when selected.

The PFD softkeys provide control over ﬂight management functions, including GPS, NAV, terrain, trafﬁc, and lightning (optional). Each softkey sublevel has a BACK Softkey which can be selected to return to the previous level. The ALERTS Softkey is visible at all softkey levels (label changes if messages are issued).

and

ALERTS

softkeys undergo a momentary change to black text on

Figure 1-17 Top Level PFD Softkeys

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SYSTEM OVERVIEW

INSET

XPDR

IDENT

TMR/REF

NRST

ALERTS

OBS

PFD

CDI

Press the CDI Softkey to cycle through navigation sources

- GPS

- NAV1 (VOR/LOC)

- NAV2 (VOR/LOC)

BACK

Press the OFF or BACK Softkey to return to the top-level softkeys.

DCLTR

DCLTR-2

DCLTR-3

DCLTR-1

TOPO

ALERTS

NEXRAD

(optional)

TERRAIN

XM LTNG

(optional)

OFF

TRAFFIC

INSET

• INSET OFF DCLTR (3)

TRAFFIC TOPO TERRAIN NEXRAD XM LTNG

Displays Inset Map in PFD lower left corner Removes Inset Map Selects desired amount of map detail; cycles through declutter levels: DCLTR (No Declutter): All map features visible DCLTR-1: Removes land data DCLTR-2: Removes land and SUA data DCLTR-3: Removes everything except active ﬂight plan Displays/removes trafﬁc information on Inset Map Displays/removes topographical data (e.g., coastlines, terrain, rivers, lakes) on Inset Map Displays/removes terrain information on Inset Map Displays/removes NEXRAD weather and coverage information on Inset Map ( Displays/removes XM lightning information on Inset Map (

optional)

• PFD DFLTS WIND

OPTN1 OPTN2 OPTN3 OFF

BRG1

HSI FMT

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360 HSI

Figure 1-18 INSET Softkeys

Displays second-level softkeys for additional PFD conﬁguration Resets PFD to default settings, including changing units to standard Displays softkeys to select and conﬁgure wind data Displays wind data in longitudinal and lateral components Displays wind data total direction and speed Displays wind data total direction with head and cross-wind speed components Removes wind information from display Cycles the Bearing 1 Information Window through: NAV1: Waypoint frequency/identiﬁer and distance information GPS: Waypoint identiﬁer and GPS distance information OFF: Removes window Displays softkeys to select the HSI format Displays HSI as a 360° compass rose

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SYSTEM OVERVIEW

INSET

XPDR

IDENT

TMR/REF

NRST

ALERTS

OBS

PFD

CDI

Press the CDI Softkey to cycle through navigation sources

- GPS

- NAV1 (VOR/LOC)

- NAV2 (VOR/LOC)

BACK

Press the OFF or BACK Softkey to return to the top-level softkeys.

DCLTR

DCLTR-2

DCLTR-3

DCLTR-1

TOPO

ALERTS

NEXRAD

(optional)

TERRAIN

XM LTNG

(optional)

OFF

TRAFFIC

INSET

STD BARO

BACK

ALERTS

WIND

HSI FMT

PFD

BRG

Select the STD BARO or BACK Softkey to return to the top-leve

softkeys.

ALT UNIT

DFLTS

Select the BRG1/BRG2 softkeys to display/remove the Bearing Information windows and cycle throug

bearing sources:

- NAV1/NAV2

- GPS

HPA

BACK

ALERTS

METERS

BACK

ALERTS

OPTN1 OPTN2 OPTN3 OFF

BACK

ALERTS

360 HSI

ARC HSI

BRG2

ALT UNIT

METERS IN HPA

STD BARO

Displays HSI as a 140° viewable arc (Bearing Information windows unavailable) Cycles the Bearing 2 Information Window through: NAV2: Waypoint frequency/identiﬁer and distance information GPS: Waypoint identiﬁer and GPS distance information OFF: Removes window Displays softkeys for changing the Altimeter barometric setting and altitude displays to

metric units Displays the current and Selected altitudes in meters in addition to feet, when selected Displays the Altimeter barometric setting in inches of mercury (in Hg) Displays the Altimeter barometric setting in hectopascals (hPa) Sets barometric pressure to 29.92 in Hg (1013 hPa if metric display is selected)

Figure 1-19 PFD Conﬁguration Softkeys

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INSET

XPDR

IDENT

TMR/REF

NRST

ALERTS

OBS

PFD

CDI

Press the CDI Softkey to cycle through navigation sources

- GPS

- NAV1 (VOR/LOC)

- NAV2 (VOR/LOC)

Select the BACK Softkey to return to the top-level softkeys

Select the IDENT

or BACK

Softkey to return to the toplevel softkeys.

XPDR

STBY

ALT

VFR

IDENT

BACK

ALERTS

CODE

IDENT

BACK

ALERTS

BKSP

BACK

Press the OFF or BACK Softkey to return to the top-level softkeys.

DCLTR

DCLTR-2

DCLTR-3

DCLTR-1

TOPO

ALERTS

NEXRAD

(optional)

TERRAIN

XM LTNG

(optional)

OFF

TRAFFIC

INSET

STD BARO

BACK

ALERTS

WIND

HSI FMT

PFD

BRG

Select the STD BARO or BACK Softkey to return to the top-leve

softkeys.

ALT UNIT

DFLTS

Select the BRG1/BRG2 softkeys to display/remove the Bearing Information windows and cycle throug

bearing sources:

- NAV1/NAV2

- GPS

GND

HPA

BACK

ALERTS

METERS

BACK

ALERTS

OPTN1 OPTN2 OPTN3 OFF

BACK

ALERTS

360 HSI

ARC HSI

• OBS

• CDI

• XPDR

• IDENT

• TMR/REF

• NRST

• ALERTS

STBY ON ALT

GND

VFR CODE

0 — 7 BKSP

Selects OBS Mode on the CDI when navigating by GPS (only available with active leg) Cycles through GPS, VOR1, and VOR2 navigation sources on the HSI Displays transponder mode selection softkeys: Selects standby mode (Transponder does not reply to any interrogations) Selects Mode A (Transponder replies to interrogations) Selects Mode C – altitude reporting mode (Transponder replies to identiﬁcation and altitude

interrogations)

Manually selects Ground Mode (Transponder does not allow Mode A and Mode C

replies, but does permit acquisition squitter and replies to discretely addressed Mode S

interrogations) Automatically enters the VFR code (1200 in U.S.A. only) Displays transponder code selection softkeys 0-7 Use numbers to enter code Removes numbers entered, one at a time Activates the Special Position Identiﬁcation (SPI) pulse for 18 seconds, identifying the

transponder return on the ATC screen Displays/removes Timer/References Window Displays/removes Nearest Airports Window Displays/removes Alerts Window

SYSTEM OVERVIEW

Figure 1-20 XPDR Softkeys

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CHKLIST

DCLTR

ENGINE

DCLTR-2

DCLTR-3

DCLTR-1

Select the ENGINE Softkey to return to the top-level softkeys.

INC FUEL

RST FUEL

DCLTR

ASSIST

DEC FUEL

ENGINE

MAP

The DONE Softkey label changes to UNDO when the checklist item is already checked.

EXIT

DONE

ENGINE

EMERGCY

BACK

TOPO

(optional)

NEXRAD

TRAFFIC

TERRAIN

(optional)

XM LTNG

Select the BACK softkey to return to the top-le

vel softkeys.

AIRWY LO

AIRWY HI

AIRWY ON

AIRWAYS

CO RST

(optional)

MFD SOFTKEYS

MFD softkeys vary depending on the page selected. EIS, Navigation Map Page (default MFD page), and

Checklist Page softkeys are described here.

Figure 1-21 MFD Softkeys (EIS, Navigation Map Page, and Checklist)

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SYSTEM OVERVIEW

• ENGINE

DCLTR ASSIST CO RST DEC FUEL INC FUEL RST FUEL

• MAP TRAFFIC TOPO

TERRAIN AIRWAYS

NEXRAD XM LTNG BACK

• DCLTR (3)

• CHKLIST DONE EXIT EMERGCY

Displays EIS - Engine Page and second-level engine softkeys; select again to exit page (see the

EIS Section for more information) Turns off CHT and EGT cylinder readouts Accesses engine leaning assist mode Resets CO Guardian; softkey enabled when carbon monoxide alert generated ( Decreases displayed fuel remaining in 1-gal increments Increases displayed fuel remaining in 1-gal increments Resets displayed fuel remaining to maximum fuel capacity for aircraft and fuel used to zero Enables second-level Navigation Map Page softkeys Displays/removes trafﬁc information on Navigation Map Page Displays/removes topographical data (e.g., coastlines, terrain, rivers, lakes) on Navigation

Map Page Displays/removes terrain information on Navigation Map Page Selects the desired display of Airways; cycles through: AIRWY ON: All Airways displayed AIRWY LO: Low Altitude (Victor) Airways displayed AIRWY HI: High Altitude Airways (Jetways) displayed AIRWAYS: Airways are not displayed Displays/removes NEXRAD weather/coverage on Navigation Map Page ( Displays/removes XM lightning information on Navigation Map Page ( Returns to top-level softkeys Selects desired amount of map detail; cycles through declutter levels: DCLTR (No Declutter): All map features visible DCLTR-1: Removes land data DCLTR-2: Removes land and SUA data DCLTR-3: Removes everything except the active ﬂight plan Displays the Checklist Page Selects the highlighted checklist item Returns to the top-level softkeys Immediately accesses the emergency procedures

optional)

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SYSTEM OVERVIEW

1.6 ACCESSING G900X FUNCTIONALITY

MENUS

The G900X has a dedicated MENU Key that when pressed displays a context-sensitive list of options. This options list allows the user to access additional features or make settings changes which speciﬁcally relate to the currently displayed window/page. There is no all-encompassing menu. Some menus provide access to additional submenus that are used to view, edit, select, and review options. Menus display ‘NO OPTIONS’ when there are no options for the window/page selected. The main controls used in association with all window/page group operations are described in Section 1.5, G900X Controls.

Navigating a menu:

1) Press the MENU Key to display the menu.

2) Turn the FMS Knob to scroll through a list of available options (a scroll bar always appears to the right of the

window/box when the option list is longer than the window/box).

3) Press the ENT Key to select the desired option.

4) Press the CLR Key or FMS Knob to remove the menu and cancel the operation.

No Options for

NRST Window

Figure 1-22 Page Menu Examples

Options for FPL Window

DATA ENTRY

Two methods exist for directly entering alphanumeric data (e.g., Flight ID, waypoint identiﬁers, barometric minimum descent altitude) into the G900X: using the using the alphanumeric keypad (on the MFD/PFD Control Unit) or the FMS Knob corresponding to the display (PFD, MFD, or MFD/PFD Control Unit).

In some instances, such as when entering an identiﬁer, the G900X tries to predict the desired identiﬁer based on the characters being entered. In this case, if the desired identiﬁer appears, use the ENT Key to conﬁrm the entry without entering the rest of the identiﬁer manually. This can save the pilot from entering all the characters of the identiﬁer.

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SYSTEM OVERVIEW

Besides character-by-character data entry, the system also provides a shortcut for entering waypoint identiﬁers. When the cursor is on a ﬁeld awaiting entry of a waypoint identiﬁer, turning the small FMS Knob counterclockwise accesses three different lists of waypoint identiﬁers for quick selection: ﬂight plan (FPL), nearest (NRST), and recently-entered (RECENT). The G900X automatically ﬁlls in the identiﬁer, facility, and city ﬁelds with the information for the selected waypoint.

Using the MFD/PFD Control Unit keypad to enter data:

1) Choose the desired display control mode by pressing the PFD or MFD Key on the MFD/PFD Control Unit.

2) If needed, press the FMS Knob to activate the cursor.

3) Use the large FMS Knob to highlight the desired ﬁeld.

4) Use the alphanumeric keys to enter the desired information.

5) Press the ENT Key to conﬁrm the entry

6) Press the CLR Key to cancel data entry (the ﬁeld revers back to its previous information).

Using the FMS Knob to enter data:

1) If needed, press the FMS Knob to activate the cursor.

2) Use the large FMS Knob to highlight the desired ﬁeld.

3) Begin entering data.

a) To quickly enter a waypoint identiﬁer, turn the small FMS Knob counter-clockwise to display a list of waypoints

in the active ﬂight plan (list is titled FPL). If desired, turn the small FMS Knob clockwise to scroll through lists of nearest waypoints (NRST) and recently-entered waypoints (RECENT).

b) Turn the large FMS Knob to highlight the desired waypoint from the list and press the ENT Key.

OR:

a) Turn the small FMS Knob to select a character for the ﬁrst placeholder.

Turning the knob clockwise scrolls through the alphabet (where appropriate) toward the letter Z, starting at

K, and the digits zero through nine. Afterwards, turning the knob counter-clockwise scrolls in the opposite direction.

b) Use the large FMS Knob to move the cursor to the next placeholder in the ﬁeld.

c) Repeat, using the small FMS Knob to select a character and the large FMS Knob to move the cursor, until the

ﬁeld is complete.

d) Press the ENT Key to conﬁrm entry.

7) Press the FMS Knob or CLR Key to cancel data entry (the ﬁeld reverts back to its previous information).

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SYSTEM OVERVIEW

PAGE GROUPS

NOTE:

Refer to other supporting sections in this Pilot’s Guide for details on speciﬁc pages.

Information on the MFD is presented on pages which are grouped according to function. The page group and active page title are displayed in the upper center of the screen, below the Navigation Status Box. In the bottom right corner of the screen, the current page group, number of pages available in the group, and placement of the current page within the group are indicated by icons. For some of these pages (Airport/Procedure/Weather Information, XM, Procedure Loading), the title of the page may change while the page icon remains the same.

Page Group Active Page Title

Page Groups

MFD

Figure 1-23 Page Title and Page Group Icons

Pages in Current Group

Selected Page

There are four main page groups, navigated using the FMS Knob; speciﬁc pages within each group can vary depending on the conﬁguration of optional equipment.

Selecting a page using the FMS Knob:

1) Turn the

Turn

the

large FMS

small FMS

Knob until the desired page group is selected (MAP, WPT, AUX, NRST).

Knob until the desired page is selected.

There are also several pages (Airport/Procedures/Weather Information and XM pages) which are selected ﬁrst from within a main page group with the FMS Knob, then with the appropriate softkey at the bottom of the page. In this case, the page remains set to the selected page until a different page softkey is selected, even if a different page group is selected.

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• Map Page Group (MAP)

Navigation Map

Trafﬁc Map (TAS optional)

Weather Data Link (optional)

Terrain/TAWS (TAWS optional)

SYSTEM OVERVIEW

Figure 1-24 Map Pages

• Waypoint Page Group (WPT)

Airport/Procedures/Weather Information Pages

- Airport Information (INFO Softkey)

- Departure Information (DP Softkey)

- Arrival Information (STAR Softkey)

- Approach Information (APR Softkey)

- Weather Information (optional) (WX Softkey)

Intersection Information

NDB Information

VOR Information

User Waypoint Information

Airport/Procedures/

Weather Information

Pages

Figure 1-25 Waypoint Pages

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SYSTEM OVERVIEW

• Auxiliary Page Group (AUX)

Trip Planning

Utility

GPS Status

System Setup

XM Satellite pages (optional)

- XM Information (INFO Softkey)

- XM Radio (RADIO Softkey)

System Status

Pages

• Nearest Page Group (NRST)

Nearest Airports

Nearest Intersections

Nearest NDB

Nearest VOR

Nearest User Waypoints

Nearest Frequencies

Nearest Airspaces

Figure 1-26 Auxiliary Pages

Figure 1-27 Nearest Pages

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SYSTEM OVERVIEW

In addition to the main page groups accessed exclusively using the FMS Knob, there are pages for ﬂight planning (FPL) and loading procedures (PROC) which are accessed by key. In some instances, softkeys may be used to access the Procedure Loading pages.

The Flight Plan pages are accessed using the FPL Key on the MFD. Main pages within this group are selected by turning the small FMS Knob.

• Flight Plan Page Group (FPL)

Active Flight Plan

Flight Plan Catalog

- Stored Flight Plan (NEW Softkey)

Figure 1-28 Flight Plan Pages

The Procedure Loading pages may be accessed at any time on the MFD by pressing the

PROC Key. A menu is initialized, and when a departure, approach, or arrival is selected, the appropriate Procedure Loading page is opened. These pages can also be accessed from the Active and Stored Flight Plan pages using the LD softkeys. Turning the FMS Knob does not scroll through the Procedure Loading pages (note the single page icon in the lower right corner).

• Procedure Loading Page Group (PROC)

Departure Loading

Arrival Loading

Approach Loading

Information on optional electronic checklist pages is offered later in this section. Checklist pages may be

accessed from any page on the MFD using the

190-00726-00 Rev. A

Figure 1-29 Procedure Loading Pages

CHKLIST Softkey.

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SYSTEM OVERVIEW

SYSTEM SETTINGS

The System Setup Page allows management of the following system parameters:

• Time format (local 12- or 24-hr, or UTC)

• Displayed measurement units

• Airspace alerts

• Arrival alerts

• Audio alert voice

• MFD Data Bar (Navigation Status Box) ﬁelds

• GPS Course Deviation Indicator (CDI) range

• COM transceiver channel spacing

• Displayed nearest airports

Figure 1-30 System Setup Page

Restoring system setup defaults:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Select the DFLTS Softkey.

OR:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the MENU Key.

3) Highlight ‘Restore Defaults’ and press the ENT Key.

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SYSTEM OVERVIEW

PILOT PROFILES

System settings may be saved under a pilot proﬁle. When the system is powered on, the last selected pilot proﬁle is shown on the MFD Power-up Splash Screen (Figure 1-5). The G900X can store up to 25 proﬁles; the currently active proﬁle, the amount of memory used, and the amount of memory available are shown at the top of the System Setup Page in the box labeled ‘Pilot Proﬁle’. From here, pilot proﬁles may be created, selected, renamed, or deleted.

Creating a proﬁle:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight ‘CREATE’ in the Pilot Proﬁle Box.

4) Press the ENT Key. A ‘Create Proﬁle’ window is displayed.

5) Use the FMS Knob to enter a proﬁle name up to 16 characters long and press the ENT Key. Pilot proﬁle names

cannot begin with a blank as the ﬁrst letter.

6) In the next ﬁeld, use the small FMS Knob to select the desired settings upon which to base the new proﬁle.

Proﬁles can be created based on Garmin factory defaults, default proﬁle settings (initially based on Garmin factory defaults unless edited by the pilot), or current system settings.

7) Press the ENT Key.

8) With ‘CREATE’ highlighted, press the ENT Key to create the proﬁle

OR:

Use the large FMS Knob to select ‘CREATE and ACTIVATE’ and press the ENT Key to activate the new proﬁle.

9) To cancel the process, select ‘CANCEL’ with the large FMS Knob and press the ENT Key.

Selecting an active proﬁle:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight the active proﬁle ﬁeld in the Pilot Proﬁle Box.

4) Turn the small FMS Knob to display the pilot proﬁle list and highlight the desired proﬁle.

5) Press the ENT Key. The G900X loads and displays the system settings for the selected proﬁle.

Renaming a proﬁle:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight ‘RENAME’ in the Pilot Proﬁle Box.

4) Press the ENT Key.

5) In the ‘Rename Proﬁle’ window, turn the FMS Knob to select the proﬁle to rename.

6) Press the ENT Key.

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SYSTEM OVERVIEW

7) Use the FMS Knob to enter a new proﬁle name up to 16 characters long and press the ENT Key.

8) With ‘RENAME’ highlighted, press the ENT Key.

9) To cancel the process, use the large FMS Knob to select ‘CANCEL’ and press the ENT Key.

Deleting a proﬁle:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight ‘DELETE’ in the Pilot Proﬁle Box.

4) Press the ENT Key.

5) In the ‘Delete Proﬁle’ window, turn the FMS Knob to select the proﬁle to delete.

6) Press the ENT Key.

7) With ‘DELETE’ highlighted, press the ENT Key.

8) To cancel the process, use the large FMS Knob to select ‘CANCEL’ and press the ENT Key.

DATE/TIME

The system time is displayed in the lower right corner of the PFD. Time and date format (local 12-hr, local 24-hr, or UTC) are modiﬁed on the System Setup Page. Universal Coordinated Time (UTC; also called Greenwich Mean Time (GMT) or Zulu) date and time are calculated directly from the GPS satellites signals and cannot be changed. An offset is provided to add or subtract the desired amount of time (hours:minutes) from UTC to deﬁne current local time.

Conﬁguring the system time:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob to activate the cursor.

3) Turn the large FMS Knob to highlight the ‘Time Format’ ﬁeld.

4) Turn the small FMS Knob to select the desired format and press the ENT Key to conﬁrm selection. The ‘Time

Offset’ ﬁeld is highlighted (for local time formats).

5) Use the FMS Knob to enter the desired time offset (±HH:MM) and press the ENT Key to conﬁrm selection.

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SYSTEM OVERVIEW

DISPLAY UNITS

Units in which various quantities are displayed on the G900X screens can be changed on the System Setup

Page.

Changing a display units setting:

1) Use the FMS Knob to select the AUX - System Setup Page on the MFD.

2) Press the FMS Knob to activate the cursor.

3) Turn the

large FMS

Knob to highlight the desired ﬁeld in the ‘Display Units’ box.

4) Turn the small FMS Knob to select from a list of measurement units and press the ENT Key when the desired unit is highlighted.

Category Settings Affected Quantities Exceptions

Navigation Angle

Distance and Speed

Altitude and Vertical Speed

Temperature

Fuel and Fuel Flow*

Weight Pounds

Position

Magnetic True

Metric Nautical

Feet Meters

Celsius Fahrenheit

Gallons Fuel parameters (Trip Planning Page) Engine Indication System (EIS)

Kilograms HDDD°MM.MM’

HDDD°MM’SS.S”

Heading Course Bearing Track Desired Track Wind direction (Trip Planning Page)

Crosstrack error (HSI) Bearing distances (information windows) DME distance (information window) Flight plan distances Map ranges DIS, GS, TAS, XTK ﬁelds (Navigation Status Box) All distances on MFD Altitude buffer distance (System Setup) Arrival Alert trigger distance (System Setup) All speeds on MFD

All altitudes on MFD All elevations on MFD

All temperatures on PFD Total Air Temperature (Trip Planning Page)

N/A N/A

All positions N/A

Airspeed Indicator True Airspeed (PFD) Wind speed vector Map range (Trafﬁc Page, Terrain

CDI scaling (System Setup) Fuel range calculation (EIS)

Altimeter Vertical Speed Indicator VNV altitudes (Active Flight Plan)

Engine Indication System (EIS)

Proximity/TAWS Page)

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Table 1-1 Display Units Settings (System Status Page)

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SYSTEM OVERVIEW

AIRSPACE ALERTS

The Airspace Alert feature provides a message alert when the aircraft is approaching or near a controlled or special-use airspace. The altitude buffer setting increases the range above or below an airspace for which an alert is generated; the default value is 200 feet. Alerts for the following airspaces can be turned on/off from the System Setup Page:

• Class B/TMA

• Class C/TCA

Turning Airspace Alerts off does not affect the alerts listed on the Nearest Airspaces Page or the airspace boundaries depicted on the Navigation Map Page.

Turning an airspace alert on or off:

1) Use the FMS Knob to select the System Setup Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight the desired ﬁeld in the ‘Airspace Alerts’ Box.

4) Turn the small FMS Knob clockwise to turn the airspace alert ON or counterclockwise to turn the alert OFF.

Changing the altitude buffer distance setting:

1) Use the FMS Knob to select the System Setup Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight the altitude buffer ﬁeld in the ‘Airspace Alerts’ Box.

4) Enter an altitude buffer value and press the ENT Key.

• Class D

• Restricted

• MOA (Military)

• Other airspaces

ARRIVAL ALERTS

Arrival alerts provide notiﬁcation upon reaching a speciﬁed distance from the ﬁnal destination (the direct-to waypoint or the last waypoint in a ﬂight plan). Once this trigger distance (up to 99.9 units) has been reached, the Navigation Status Box on the PFD displays an “Arrival at [waypoint]” message.

Enabling/disabling arrival alerting and changing the trigger distance:

1) Use the FMS Knob to select the System Setup Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to select the ON/OFF ﬁeld in the ‘Arrival Alert’ Box.

4) Turn the small FMS Knob clockwise to turn the airspace alert ON or counterclockwise to turn the alert OFF.

5) Turn the large FMS Knob to highlight the distance ﬁeld in the ‘Arrival Alert’ Box.

6) Enter a trigger distance and press the ENT Key.

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SYSTEM OVERVIEW

AUDIO ALERTS

The gender of the voice used to announce audio alerts may be set to male or female on the System Setup

Page. See the Appendices for voice alerts.

Changing the audio alert voice:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight the voice in the Audio Alert Box.

4) Turn the small FMS Knob to display and highlight the desired voice and press the ENT Key.

MFD DATA BAR FIELDS

By default, the Navigation Status Box on the MFD is set to display ground speed (GS), distance to next waypoint (DIS), estimated time enroute (ETE), and enroute safe altitude (ESA). These four data ﬁelds can be changed to display the following information:

• Bearing (BRG)

• Distance (DIS)

• Desired Track (DTK)

• Enroute Safe Altitude (ESA)

•

Estimated Time of Arrival (ETA)

The Navigation Status Box on the PFD is not affected by these changes; ﬂight plan, distance, and bearing information are displayed at all times.

Changing the information shown in the MFD Navigation Status Box:

1) Use the FMS Knob to select the System Setup Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight the desired ﬁeld number in the MFD Data Bar Fields Box.

4) Turn the small FMS Knob to highlight the desired selection from the data options list and press the ENT Key.

• Estimated Time Enroute (ETE)

• Ground Speed (GS)

• Minimum Safe Altitude (MSA)

• True Airspeed (TAS)

• Track Angle Error (TKE)

• Track (TRK)

• Vertical Speed Required (VSR)

• Crosstrack Error (XTK)

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Figure 1-31 Navigation Status Box (MFD)

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SYSTEM OVERVIEW

GPS CDI

The GPS CDI Box on the System Setup Page allows the pilot to deﬁne the scale for the Course Deviation Indicator (CDI) when GPS is the selected navigation source and also displays the current system value for the CDI scale. The range values represent full scale deﬂection for the CDI to either side. The default setting is ‘Auto’ (refer to the CDI description in the Flight Instruments Section for information on CDI scaling).

If a lower CDI scale setting is selected (i.e., 1.0 or 0.3 nm), the higher scale settings are not selected during any phase of ﬂight. Note that the Receiver Autonomous Integrity Monitoring (RAIM) protection limits follow the selected CDI scale and corresponding ﬂight phase.

Changing the selected GPS CDI setting:

1) Use the FMS Knob to select the AUX - System Setup Page on the MFD.

2) Press the FMS Knob to activate the cursor.

3) Turn the

4) Turn the small FMS Knob to highlight the desired setting (2 nm, 1 nm, 0.3 nm, Auto) and press the ENT Key.

large FMS

Knob to highlight ‘Selected’ in the ‘GPS CDI’ box.

COM CONFIGURATION

The COM Conﬁguration Box on the System Setup Page allows the pilot to select 8.33 kHz or 25.0 kHz COM frequency channel spacing.

Changing COM channel spacing:

1) Use the FMS Knob to select the System Setup Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight the channel spacing ﬁeld in the COM Conﬁguration Box.

4) Turn the small FMS Knob to select the desired spacing and press the ENT Key.

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SYSTEM OVERVIEW

NEAREST AIRPORTS

The Nearest Airports Box on the System Setup Page deﬁnes the minimum runway length and surface type used when determining the nine nearest airports to display on the MFD Nearest Airports Page. A minimum runway length and/or surface type can be entered to prevent airports with small runways or runways that are not of appropriate surface from being displayed. Default settings are 0 feet (or meters) for runway length and “any” for runway surface type.

Selecting nearest airport surface matching criteria (any, hard only, hard/soft, water):

1) Use the FMS Knob to select the System Setup Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight the runway surface ﬁeld in the Nearest Airports Box.

4) Turn the small FMS Knob to select the desired runway option (any, hard only, hard/soft, water) and press the ENT Key.

Selecting nearest airport minimum runway length matching criteria:

1) Use the FMS Knob to select the System Setup Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight the minimum length ﬁeld in the Nearest Airport Box.

4) Enter the minimum runway length (zero to 99,999 feet) and press the ENT Key.

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SYSTEM UTILITIES

For ﬂight planning purposes, timers, trip statistics, and a scheduler feature are provided on the AUX - Utility Page. The timers available include a stopwatch-like generic timer, a total time in ﬂight timer, and a record of the time of departure. Trip statistics—odometer, trip odometer, and average trip and maximum groundspeeds—are displayed from the time of the last reset. A scheduler feature is also provided so the pilot can enter reminder messages to be displayed at speciﬁed intervals in the Alerts Window on the PFD (see Figure 1-33).

Figure 1-32 Utility Page

TIMERS

The generic timer can be set to count up or down from a speciﬁed time (HH:MM:SS). When the countdown on the timer reaches zero the digits begin to count up from zero. If the timer is reset before reaching zero on a countdown, the digits are reset to the initial value. If the timer is counting up when reset, the digits are zeroed.

Setting the generic timer:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the small FMS Knob to select the timer counting direction (UP/DN) and press the ENT Key.

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4) If a desired starting time is desired:

a) Use the large FMS Knob to highlight the HH:MM:SS ﬁeld.

SYSTEM OVERVIEW

b) Use the FMS Knob to enter the desired time and press the

5) Turn the

large FMS

Knob to highlight ‘START?’ and press the

ENT

Key.

ENT

Key to start the timer. The ﬁeld changes to

‘STOP?’.

6) To stop the timer, press the ENT Key with ‘STOP?’ highlighted. The ﬁeld changes to ‘RESET?’.

7) To reset the timer, press the ENT Key with ‘RESET?’ highlighted. The ﬁeld changes back to ‘START?’ and the

digits are reset.

The ﬂight timer can be set to count up from zero starting at system power-up or from the time that the

aircraft lifts off; the timer can also be reset to zero at any time.

Setting the ﬂight timer starting criterion:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight the ﬁeld next to the ﬂight timer.

4) Turn the

small FMS

Knob to select the starting criterion (PWR-ON or IN-AIR) and press the

ENT

Key.

Resetting the ﬂight timer:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the

3) With ‘Reset Flight Timer’ highlighted, press the

Key.

ENT

Key.

The G900X records the time at which departure occurs, measured from system power-up or aircraft lift off. The displayed departure time can also be reset to display the current time at the point of reset. The format in which the time is displayed is controlled from the System Setup Page.

Setting the departure timer starting criterion:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight the ﬁeld next to the departure time.

4) Turn the

small FMS

Knob to select the starting criterion (PWR-ON or IN-AIR) and press the

ENT

Key.

Resetting the departure time:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the

3) Use the FMS Knob to highlight ‘Reset Departure Time’ and press the

Key.

ENT

Key.

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TRIP STATISTICS

The odometer and trip odometer record the total mileage traveled from the last reset; these odometers can be reset independently. Resetting the trip odometer also resets the average trip groundspeed. Maximum groundspeed for the period of time since the last reset is also displayed.

Resetting trip statistics readouts:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the

• Reset Trip ODOM/AVG GS—Resets trip average ground speed readout and odometer

• Reset Odometer—Resets odometer readout only

• Reset Maximum Speed—Resets maximum speed readout only

• Reset All—Resets ﬂight timer, departure timer, odometers, and groundspeed readouts

3) Use the FMS Knob to highlight the desired reset option and press the

to zero and begin to display data from the point of reset.

Key. The following reset options for trip statistics are displayed:

ENT

Key. The selected parameters are reset

SCHEDULER

The scheduler feature can be used to enter and display reminder messages (e.g., “Change oil”, “Switch fuel tanks”, “Overhaul”). Messages can be set to display based on a speciﬁc date and time (event), once the message timer reaches zero (one-time; default setting), or recurrently whenever the message timer reaches zero (periodic). Message timers set to periodic alerting automatically reset to the original timer value once the message is displayed. When power is cycled, messages are retained until deleted, and message timer countdown is restarted.

Entering a scheduler message:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight the ﬁrst empty scheduler message naming ﬁeld.

4) Use the FMS Knob to enter the message text to be displayed in the Alerts Window and press the

5) Press the ENT Key again or use the large FMS Knob to move the cursor to the ﬁeld next to ‘Type’.

ENT

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SYSTEM OVERVIEW

6) Turn the small FMS Knob to select set the message alert type:

• Event—Message issued at the speciﬁed date/time

• One-time—Message issued when the message timer reaches zero (default setting)

• Periodic—Message issued each time the message timer reaches zero

7) Press the ENT Key again or use the large FMS Knob to move the cursor to the next ﬁeld.

8) For periodic and one-time message, use the FMS Knob to enter the timer value (HHH:MM:SS) from which to

countdown and press the ENT Key.

9) For event-based messages:

a) Use the FMS Knob to enter the desired date (DD-MMM-YYY) and press the ENT Key.

b) Press the ENT Key again or use the large FMS Knob to move the cursor to the next ﬁeld.

c) Use the FMS Knob to enter the desired time (HH:MM) and press the ENT Key.

10) Press the ENT Key again or use the large FMS Knob to move the cursor to enter the next message.

Deleting a scheduler message:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the FMS Knob momentarily to activate the ﬂashing cursor.

3) Turn the large FMS Knob to highlight the name ﬁeld of the scheduler message to be deleted.

4) Press the CLR Key to clear the message text. If the CLR Key is pressed again, the message is restored.

5) Press the ENT Key to conﬁrm message deletion.

Scheduler messages appear in the Alerts Window on the PFD and cause the ALERTS Softkey label to change to ‘ADVISORY’. Selecting the ADVISORY Softkey opens the Alerts Window and acknowledges the scheduler message. The softkey revers to the ‘ALERTS’ label and when pressed, the Alerts Window is removed from the display and the scheduler message is deleted from the message list.

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PFD

Figure 1-33 PFD Alerts Window

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SYSTEM OVERVIEW

ELECTRONIC CHECKLISTS (OPTIONAL)

NOTE:

The checklists presented in this section are for example only and may not reﬂect checklists actually available. The information described in this section is not intended to replace the checklist information described in the aircraft-speciﬁc Pilot’s Operating Handbook (POH).

NOTE:

Garmin is not responsible for the content of the checklists. User-deﬁned checklists are created by the kitplane builder. Refer to the G900X Installation Manual for details on how to create and upload checklists.

The MFD is able to display optional electronic checklists which allow a pilot to quickly ﬁnd the proper procedure on the ground and during each phase of ﬂight. The G900X accesses the checklists from an SD card inserted into the bezel slot (see Figure 1-3). If the SD card contains an invalid checklist ﬁle or no checklist, the Power-up Splash Screen displays ‘Invalid Checklist File’ or ‘Checklist File Not Present’ and the CHKLIST Softkey is not available.

Figure 1-34 Checklist Page Example

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SYSTEM OVERVIEW

Accessing and navigating checklists:

1) From any page, select the CHKLIST Softkey.

2) Turn the large FMS Knob to select the ‘GROUP’ ﬁeld.

3) Turn the small FMS Knob to select the desired procedure and press the ENT Key.

4) Turn the large FMS Knob to select the ‘Checklist’ ﬁeld.

5) Turn the FMS Knob to select the desired checklist and press the ENT Key.

6) Turn the FMS Knob to scroll through the checklist and highlight the desired checklist item (has a hollow white

box for checkmark).

The following colors are used for checklist items:

• Blue - Items has not been highlighted

• Green - Item has been selected

• White - Item is highlighted for selection

7) Press the ENT Key or DONE Softkey to select the highlighted checklist item (item turns green and a checkmark

• Yellow - Warning notes

is placed in the box next to the item). The next item is automatically highlighted for selection.

Press the CLR Key to remove a check mark from an item.

8) Once the last item in a checklist is selected, ‘Go to the next checklist?’ is highlighted. Press the ENT Key to

advance to the next checklist displayed.

9) Select the EXIT Softkey or hold down the CLR Key momentarily to exit the Checklist Page and return to the page

last viewed.

Immediately accessing emergency procedures:

1) From any page, select the CHKLIST Softkey.

2) Select the EMERGCY Softkey.

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Figure 1-35 Sample Checklist

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1.7 DISPLAY BACKLIGHTING

Backlighting of the PFD and MFD, Audio Panel keys, and PFD/MFD Control Unit keys can be adjusted

automatically or manually. The automatic setting (default) uses photocells to adjust for ambient lighting conditions. Photocell calibration curves are pre-conﬁgured to optimize display appearance through a broad range of cockpit lighting conditions. In normal display mode, backlighting can only be adjusted from the PFD. In Reversionary Mode, it can be adjusted from the remaining display.

Adjusting display backlighting manually:

1) Press the PFD MENU Key to display the PFD Setup Menu. ‘AUTO’ is now highlighted next to ‘PFD DSPL’. No

other window can be displayed on the PFD while the PFD Setup Menu is displayed. Pressing the MENU Key while any other PFD window is displayed does not display the PFD Setup Menu.

2) Turn the

3) Use the FMS Knob to enter the desired backlighting then press the

4) Turn the

5) To remove the menu, press the

Adjusting key backlighting manually:

1) Press the PFD

2) Turn the

3) Turn the

4) Turn the

5) Turn the

6) Use the FMS Knob to enter the desired backlighting and press the

7) Turn the

8) Turn the

9) To remove the menu, press the

small FMS

large FMS

small FMS

large FMS

small FMS

large FMS

small FMS

Knob to select ‘MANUAL’ and press the

Knob to highlight ‘AUTO’ next to ‘MFD DSPL’ and repeat steps 2-4.

CLR

Key.

Key to display the PFD Setup Menu. ‘AUTO’ is now highlighted next to ‘PFD DSPL’.

Knob to highlight ‘PFD DSPL’.

Knob in the direction of the green arrowhead to display ‘PFD KEY’.

Knob to highlight ‘AUTO’.

Knob to select ‘MANUAL’ and press the

Knob to highlight ‘MFD DSPL’.

Knob in the direction of the green arrowhead to display ‘MFD KEY’ and repeat steps 4-7.

CLR

Key.

ENT

Key. The intensity value is now highlighted.

ENT

Key. The intensity value is now highlighted.

ENT

Key.

PFD

Figure 1-36 PFD Setup Menu

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SECTION 2 FLIGHT INSTRUMENTS

FLIGHT INSTRUMENTS

WARNING:

In the event that the airspeed, attitude, altitude, or heading indications become unusable, refer

to the backup instruments.

Increased situational awareness is provided by replacing the traditional instruments on the panel with an easyto-scan Primary Flight Display (PFD) that features a large horizon, airspeed, attitude, altitude, vertical speed, and course deviation information. In addition to the ﬂight instruments, navigation, communication, terrain, trafﬁc, and weather information are also presented on the PFD and explained in other sections of this Pilot’s Guide.

The following ﬂight instruments and supplemental ﬂight data are displayed on the PFD:

• Airspeed Indicator, showing

– True airspeed

– Airspeed awareness ranges

– Trend vector

– Reference ﬂags

• Attitude Indicator with slip/skid

indication

• Altimeter, showing

– Trend vector

– Barometric setting

– Selected Altitude

• Vertical Deviation, Glideslope, and Glidepath Indicators

• Vertical Speed Indicator (VSI)

• Horizontal Situation Indicator, showing

– Heading and course indications

– Turn Rate Indicator

– Navigation source

– Course Deviation Indicator

(CDI)

– Bearing pointers and

information windows

• Timer/References Window, showing

– Generic timer

– Vspeed values and ﬂags

– Barometric minimum descent

altitude (MDA; or decision height, DH)

– Flight ID (see Audio Panel and

CNS Section)

• System time

• Wind data

• Vertical Navigation indications

• Outside Air Temperature (OAT)

The PFD also displays various alerts and annunciations.

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NAV Frequency Box

Airspeed Indicator

True Airspeed

Current Heading

Selected Heading Bug

Outside Air Temperature (OAT)

Softkeys

System Time

Transponder Data Box

Horizontal Situation Indicator ( HSI)

Figure 2-1 Primary Flight Display (Default)

Turn Rate Indicator

Altimeter Barometric Setting

Selected Altitude Bug

Vertical Speed Indicator (VSI)

Altimeter

Selected Altitude

COM Frequency Box

Navigation Status Box

Slip/Skid Indicator

Attitude Indicator

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Trafﬁc Annunciation

Vspeed Reference

Flight Plan Window

Annunciation Window

Selected Heading

Wind Data

Inset Map

Bearing Information Windows

Minimum Descent Altitude/Decision Height

Figure 2-2 Primary Flight Display (Additional Information)

Selected Course

Vertical Speed Required

Vertical Deviation Indicator (VDI)

Current VNV Target Altitute

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2.1 FLIGHT INSTRUMENTS

AIRSPEED INDICATOR

NOTE:

G900X Airspeed Indicator markings correspond to Vspeed values provided by the kitplane

manufacturer.

The Airspeed Indicator displays airspeed on a rolling number gauge using a moving tape. The true airspeed (TAS) is displayed in knots below the Airspeed Indicator. The numeric labels and major tick marks on the moving tape are marked at intervals of 10 knots, while minor tick marks on the moving tape are indicated at intervals of 5 knots. Speed indication starts at 20 knots, with 60 knots of airspeed viewable at any time. The actual airspeed is displayed inside the black pointer. The pointer remains black until reaching never-exceed speed (VNE), at which point it turns red.

Airspeed Trend Vector

Vspeed Reference

Actual Airspeed

Speed Ranges

Figure 2-4 Red Pointer Showing Overspeed

True Airspeed

Figure 2-3 Airspeed Indicator

A color-coded (white, green, yellow, and red) speed range strip is located on the moving tape. The colors denote ﬂaps operating range, normal operating range, caution range, and never-exceed speed (V

). A red range

is also present for low speed awareness.

The Airspeed Trend Vector is a vertical, magenta line, extending up or down on the airspeed scale, shown to the right of the color-coded speed range strip. The end of the trend vector corresponds to the predicted airspeed in 6 seconds if the current rate of acceleration is maintained. If the trend vector crosses VNE, the text of the actual airspeed readout changes to yellow. The trend vector is absent if the speed remains constant or if any data needed to calculate airspeed is not available due to a system failure.

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Vspeeds can be changed and their ﬂags turned on/off from the Timer/References Window (Figure 2-5). When active (on), the Vspeeds are displayed at their respective locations to the right of the airspeed scale. By default, all Vspeed values are reset and all ﬂags turned off when power is cycled.

Changing Vspeeds and turning ﬂags on/off:

1) Select the

2) Turn the

TMR/REF

large FMS

Softkey.

Knob to highlight the desired Vspeed.

3) Use the small FMS Knob to change the Vspeed in 1-kt increments (when a speed has been changed from a default value, an asterisk appears next to the speed).

4) Press the

5) Turn the

6) To remove the window, press the

ENT

Key or turn the large FMS Knob to highlight the ON/OFF ﬁeld

small FMS

Knob clockwise to ON or counterclockwise to OFF.

CLR

Figure 2-5 Timer/References Window

Key or the

TMR/REF

Softkey.

Figure 2-6 Timer/References Menu

Turning all Vspeed ﬂags ON/OFF:

1) Select the

2) Press the

3) To view all Vspeed ﬂags, highlight ‘All References On’ and press the

4) To remove all Vspeed ﬂags, turn the FMS Knob to highlight ‘All References Off’ and press the

TMR/REF

Key.

Softkey.

ENT

Key (Figure 2-6).

ENT

Restoring all Vspeed defaults:

1) Select the

2) Press the

3) Turn the

4) Press the

TMR/REF

FMS

ENT

Softkey.

Key.

Knob to highlight ‘Restore Defaults’.

Key.

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ATTITUDE INDICATOR

Attitude information is displayed over a virtual blue sky and brown ground with a white horizon line. The

Attitude Indicator displays the pitch, roll, and slip/skid information.

Roll Pointer

Roll Scale

Horizon Line

Aircraft Symbol

Land Representation

Pitch Scale

Slip/Skid Indicator

Sky Representation

Roll Scale Zero

Figure 2-7 Attitude Indicator

The horizon line is part of the pitch scale. Above and below the horizon line, major pitch marks and numeric labels are shown for every 10˚, up to 80˚. Minor pitch marks are shown for intervening 5˚ increments, up to 25˚ below and 45˚ above the horizon line. Between 20˚ below to 20˚ above the horizon line, minor pitch marks occur every 2.5˚.

The inverted white triangle indicates zero on the roll scale. Major tick marks at 30˚ and 60˚ and minor tick marks at 10˚, 20˚, and 45˚ are shown to the left and right of the zero. Angle of bank is indicated by the position of the pointer on the roll scale.

The Slip/Skid Indicator is the bar beneath the roll pointer. The indicator moves with the roll pointer and laterally away from the pointer to indicate lateral acceleration (slip/skid). One bar displacement from the roll pointer is equivalent to one ball displacement on a traditional Slip/Skid Indicator (Figure 2-8).

Figure 2-8 Slip/Skid Indication

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ALTIMETER

The Altimeter displays 600 feet of barometric altitude values at a time on a rolling number gauge using a moving tape. Numeric labels and major tick marks are shown at intervals of 100 feet. Minor tick marks are at intervals of 20 feet. The current altitude is displayed in the black pointer.

The Selected Altitude is displayed above the Altimeter in the box indicated by a selection bug symbol. A bug corresponding to this altitude is shown on the tape; if the Selected Altitude exceeds the range shown on the tape, the bug appears at the corresponding edge of the tape.

Setting the Selected Altitude:

Turn the

ALT

Knob to set the Selected Altitude in 100-ft increments (increments reduce to 10 feet for approach)

up to the aircraft’s service ceiling.

If set, the Minimum Descent Altitude/Decision Height (MDA/DH) value is also available for the Selected Altitude.

Selected Altitude

Selected Altitude Bug

Altitude Trend Vector

Current Altitude

Minimum Descent

Altitude/Decision

Height Bug

Barometric Setting

Figure 2-10 Altimeter (Metric Units)Figure 2-9 Altimeter

Selected and current altitudes can also be displayed in meters (readouts displayed above the normal readouts in feet; Figure 2-10). Note that the altitude tape does not change scale.

Displaying altitude in meters:

1) Select the PFD Softkey to display the second-level softkeys.

2) Select the ALT UNIT Softkey.

3) Select the METERS Softkey to turn on metric altitude readouts.

4) Select the

A magenta Altitude Trend Vector extends up or down the left of the altitude tape, the end resting at the approximate altitude to be reached in 6 seconds at the current vertical speed. The trend vector is not shown if altitude remains constant or if data needed for calculation is not available due to a system failure.

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BACK

Softkey to return to the top-level softkeys.

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The barometric pressure setting is displayed below the Altimeter in inches of mercury (in Hg) or hectopascals (hPa) when metric units are selected. Adjusting the altimeter barometric setting creates discontinuities in VNV vertical deviation, moving the descent path. For large adjustments, it may take several minutes for the aircraft to re-establish on the descent path. If the change is made while nearing a waypoint with a VNV Target Altitude, the aircraft may not re-establish on the descent path in time to meet the vertical constraint.

Selecting the altimeter barometric pressure setting:

Turn the BARO Knob to select the desired setting.

Selecting standard barometric pressure (29.92 in Hg):

1) Select the PFD Softkey to display the second-level softkeys.

2) Select the STD BARO Softkey.

Changing altimeter barometric pressure setting units:

1) Select the PFD Softkey to display the second-level softkeys.

2) Select the ALT UNIT Softkey.

3) Select the IN Softkey to display the barometric pressure setting in inches of mercury (in Hg).

Or, select the HPA Softkey to display the barometric pressure setting in hectopascals (hPa; see Figure 2-10).

4) Select the

BACK

Softkey to return to the top-level softkeys.

VERTICAL SPEED INDICATOR (VSI)

The Vertical Speed Indicator (VSI, Figure 2-11) displays the aircraft vertical speed using a non-moving tape labeled at 1000 and 2000 fpm with minor tick marks every 500 fpm. The current vertical speed is displayed in the pointer along the tape. Digits appear in the pointer when the climb or descent rate is greater than 100 fpm. If the rate of ascent/descent exceeds 2000 fpm, the pointer appears at the corresponding edge of the tape and the rate appears inside the pointer.

A magenta chevron bug is displayed as the Required Vertical Speed Indication (RVSI) for reaching a VNV Target Altitude once the “TOD [Top of Descent] within 1 minute” alert has been generated. See the GPS Navigation Section for details on VNV features, and refer to Section 2.2, Supplemental Flight Data, for more information about VNV indications on the PFD.

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VERTICAL DEVIATION, GLIDESLOPE, AND GLIDEPATH INDICATORS

The Vertical Deviation Indicator (VDI; Figure 2-11) uses a magenta chevron to indicate the baro-VNV vertical deviation when Vertical Navigation (VNV) is being used; the VDI appears in conjunction with the “TOD within 1 minute” alert. The VDI is removed from the display if vertical deviation becomes invalid. See the GPS Navigation Section for details on VNV features, and refer to Section 2.2, Supplemental Flight Data, for more information about VNV indications on the PFD.

The Glideslope Indicator (Figure 2-12) appears to the left of the Altimeter whenever an ILS frequency is tuned in the active NAV ﬁeld. A green diamond acts as the Glideslope Indicator, like a glideslope needle on a conventional indicator. If a localizer frequency is tuned and there is no glideslope, “NO GS” is annunciated.

The glidepath is analogous to the glideslope for GPS approaches supporting WAAS vertical guidance (LNAV+V, L/VNV, LPV) and is generated by the system to reduce pilot workload during approach. When an approach of this type is loaded into the ﬂight plan and GPS is the selected navigation source, the Glidepath Indicator (Figure 2-13) appears as a magenta diamond. If the approach type downgrades past the ﬁnal approach ﬁx (FAF), “NO GP” is annunciated.

Full-scale deﬂection (two dots) is 1000 feet.

Vertical

Deviation

Indicator

Deviation Indicators (VSI and VDI)

VNV Target Altitude

Vertical Speed Indicator

Vertical Speed Pointer

Required Vertical Speed

Figure 2-11 Vertical Speed and

Marker Beacon

Annunciation

Glideslope

Indicator

Figure 2-12 Glideslope Indicator

Glidepath

Indicator

Figure 2-13 Glidepath Indicator

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HORIZONTAL SITUATION INDICATOR (HSI)

The Horizontal Situation Indicator (HSI) displays a rotating compass card in a heading-up orientation. Letters indicate the cardinal points and numeric labels occur every 30˚. Major tick marks are at 10˚ intervals and minor tick marks at 5˚ intervals. A digital reading of the current heading appears on top of the HSI, and the current track is represented on the HSI by a magenta diamond bug. The HSI also presents turn rate, course deviation, bearing, and navigation source information and is available in two formats (360˚ compass rose and 140˚ arc).

Changing the HSI display format:

1) Select the

PFD

Softkey.

2) Select the HSI FRMT Softkey.

3) Select the

360 HSI

ARC HSI

Softkey.

The 360˚ HSI (Figure 2-14) contains a Course Deviation Indicator (CDI), with a Course Pointer, To/From Indicator, and a sliding deviation bar and scale. The course pointer is a single line arrow (GPS, VOR1, and LOC1) or a double line arrow (VOR2 and LOC2) which points in the direction of the set course. The To/From arrow rotates with the course pointer and is displayed when the active NAVAID is received.

Turn Rate Indicator

Current Track Bug

Lateral Deviation Scale

Navigation Source

Aircraft Symbol

Course Deviation Indicator (CDI)

Rotating Compass Rose

OBS Mode Active

To/From Indicator

Course Pointer

Heading Bug

Flight Phase

Turn Rate/Heading Trend Vector

Current Heading

Lubber Line

Figure 2-14 Horizontal Situation Indicator (HSI)

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The Arc HSI (Figure 2-15) is a 140˚ expanded section of the compass rose. The Arc HSI contains a Course Pointer, To/From Indicator, a sliding deviation indicator (the To/From and deviation indicators are combined), and a deviation scale. Upon station passage, the To/From Indicator ﬂips and points to the tail of the aircraft, just like a conventional To/From ﬂag. Depending on the navigation source, the CDI on the Arc HSI can appear in two different ways: an arrowhead (GPS, VOR, OBS) or a diamond (LOC).

Course Pointer

Navigation Source Flight Phase Annunciation

Lateral Deviation Scale

Figure 2-15 Arc HSI

Course Deviation and To/From Indicator

The Selected Heading is shown to the upper left of the HSI for 3 seconds after being adjusted The light blue bug on the compass rose corresponds to the Selected Heading. While the HSI is displayed as an arc, if the Selected Heading Bug is adjusted off the shown portion of the compass rose, the digital reading displayed.

Adjusting the Selected Heading:

Turn the

Press the HDG Knob to synchronize the bug to the current heading.

HDG

Knob to set the Selected Heading.

The Selected Course is shown to the upper right of the HSI for 3 seconds after being adjusted. While the HSI is displayed as an arc, the Selected Course is displayed whenever the Course Pointer is not within the 140˚ currently shown.

Adjusting the Selected Course:

Turn the

Press the CRS Knob to re-center the CDI and return the course pointer to the bearing of the active waypoint or

CRS

Knob to set the Selected Course.

navigation station (see OBS Mode for adjusting a GPS course).

Current Track Bug

Selected Heading Selected Course

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Figure 2-16 Heading and Course Indications

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Selected Heading Bug

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Navigation angles (track, heading, course, bearing) are corrected to the computed magnetic variation (‘Mag Var’) or referenced to true north (denoted ‘T’), set on the AUX - System Setup Page. When an approach referenced to true north has been loaded into the ﬂight plan, the system generates a message to change the navigation angle setting to ‘True’ at the appropriate time.

Figure 2-17 Heading and Course Indications (True)

Changing the navigation angle setting:

1) Use the FMS Knob to select the AUX - System Setup Page on the MFD.

2) Press the FMS Knob to activate the cursor.

3) Turn the

4) Turn the small FMS Knob to highlight the desired setting and press the ENT Key.

large FMS

Knob to highlight ‘Nav Angle’ in the ‘Display Units’ box (Figure 2-18).

Figure 2-18 System Setup Page,

Navigation Angle Settings

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TURN RATE INDICATOR

The Turn Rate Indicator is located directly above the rotating compass card. Tick marks to the left and right of the lubber line denote half-standard and standard turn rates. A magenta Turn Rate Trend Vector shows the current turn rate. The end of the trend vector gives the heading predicted in 6 seconds, based on the present turn rate. A standard-rate turn is shown on the indicator by the trend vector stopping at the standard turn rate tick mark, corresponding to a predicted heading of 18˚ from the current heading (Figure 2-19). At rates greater than 4 deg/sec, an arrowhead appears at the end of the magenta trend vector and the prediction is no longer valid.

Half-std Turn Rate

Std Turn Rate

Figure 2-19 Turn Rate Indicator and Trend Vector

Arrow Shown for Turn Rate > 4 deg/sec

BEARING INFORMATION

NOTE:

When the Arc HSI is displayed, the Bearing Information windows and pointers are disabled.

Two bearing pointers and associated information can be displayed on the HSI for NAV and GPS sources. The pointers are light blue and are single- (BRG1) or double-lined (BRG2); an icon is shown in the respective information window to indicate the pointer type. The bearing pointers never override the CDI and are visually separated from the CDI by a white ring (shown when bearing pointers are selected but not necessarily visible due to data unavailability).

Distance to

Bearing Source

Bearing

Source

Bearing 1 Information Window

Station

Identiﬁer

Pointer

Icon

Bearing 1

Pointer

Figure 2-20 HSI with Bearing and DME Information

Bearing 2

Pointer

Waypoint

Selected

Pointer

Icon

Bearing 2 Information Window

Bearing

Source

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When a bearing pointer is displayed, its associated information window is also displayed. The Bearing

Information windows (Figure 2-20) are displayed to the lower sides of the HSI and show:

• Bearing source (NAV, GPS)

• Pointer icon (BRG1=single line, BRG2=double line)

• Frequency (NAV)

If the NAV radio is the bearing source and is tuned to an ILS frequency (refer to the Audio Panel and CNS Section for information on tuning the radios), the bearing pointer is removed from the HSI and the frequency is replaced with “ILS”. When NAV1 or NAV2 is the selected bearing source, the frequency is replaced by the station identiﬁer when the station is within range. If GPS is the bearing source, the active waypoint identiﬁer is displayed in lieu of a frequency.

The bearing pointer is removed from the HSI and “NO DATA” is displayed in the information window if:

• The NAV radio is not receiving the tuned VOR

station

Selecting bearing display and changing sources:

1) Select the PFD Softkey.

2) Select a BRG Softkey to display the desired bearing pointer and information window with a NAV source.

3) Select the BRG Softkey again to change the bearing source to GPS.

4) To remove the bearing pointer and information window, select the BRG Softkey again.

• Station/waypoint identiﬁer (NAV, GPS)

• GPS-derived great circle distance to bearing source

• GPS is the bearing source and an active waypoint is not selected

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COURSE DEVIATION INDICATOR (CDI)

NOTE

If a heading change of greater than 105˚ with respect to the course is made, the CDI on the Arc HSI

switches to the opposite side of the deviation scale and displays reverse sensing.

The Course Deviation Indicator (CDI) moves left or right from the course pointer along a lateral deviation scale to display aircraft position relative to the course. If the course deviation data is not valid, the CDI is not displayed.

Flight Phase

Navigation

Source

Scale

Crosstrack Error

CDI

360º HSI

Figure 2-21 Course Deviation Indicator

Navigation Source

Crosstrack Error

CDI Scale

Flight Phase

CDI

Arc HSI

The CDI can display two sources of navigation: GPS or NAV (VOR, localizer). Color indicates the current navigation source: magenta (for GPS) or green (for VOR and LOC). The full scale limits for the CDI are deﬁned by a GPS-derived distance when coupled to GPS. When coupled to a VOR or localizer (LOC), the CDI has the same angular limits as a mechanical CDI. If the CDI exceeds the maximum deviation on the scale (two dots) while coupled to GPS, the crosstrack error (XTK) is displayed below the white aircraft symbol.

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Figure 2-22 Navigation Sources

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Changing navigation sources:

1) Select the CDI Softkey to change from GPS to VOR1 or LOC1. This places the light blue tuning box over the

NAV1 standby frequency in the upper left corner of the PFD.

2) Select the CDI Softkey again to change from VOR1 or LOC1 to VOR2 or LOC2. This places the light blue tuning

box over the NAV2 standby frequency.

3) Select the CDI Softkey a third time to return to GPS.

GPS

Selected

NAV2 Selected

for Tuning

VOR2

CDI

Softkey Cycles Through

Navigation Sources

LOC1

Selected

NAV1 Selected

for Tuning

Selected

Figure 2-23 Selecting a Navigation Source

The system automatically switches from GPS to LOC navigation source and changes the CDI scaling accordingly

when all of the following occur:

• A localizer or ILS approach has been loaded into the active ﬂight plan

• The ﬁnal approach ﬁx (FAF) is the active leg, the FAF is less than 15 nm away, and the aircraft is moving toward the FAF

• A valid localizer frequency has been tuned

• The GPS CDI deviation is less than 1.2 times full-scale deﬂection

GPS steering guidance is still provided after the CDI automatically switches to LOC until LOC capture, up

to the Final Approach Fix (FAF) for an ILS approach, or until GPS information becomes invalid. Activating a Vector-to-Final (VTF; see the GPS Navigation Section) also causes the CDI to switch to LOC navigation source; GPS steering guidance is not provided after this switch.

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GPS CDI SCALING

When GPS is the selected navigation source, the ﬂight plan legs are sequenced automatically and annunciations appear on the HSI for the ﬂight phase. Flight phase annunciations are normally shown in magenta, but when cautionary conditions exist the color changes to yellow. If the current leg in the ﬂight plan is a heading leg, ‘HDG LEG’ is annunciated in magenta beneath the aircraft symbol.

The current GPS CDI scale setting is displayed as ‘System CDI’ on the AUX - System Setup Page and the fullscale deﬂection setting may also be changed (2.0 nm, 1.0 nm, 0.3 nm, or Auto) from this page ( If the selected scaling is smaller than the automatic setting for enroute and terminal phases, the CDI is scaled accordingly and the selected setting is be displayed rather than the ﬂight phase annunciation.

Changing the selected GPS CDI setting:

1) Use the FMS Knob to select the AUX - System Setup Page on the MFD.

2) Press the FMS Knob to activate the cursor.

Figure 2-24

3) Turn the

4) Turn the small FMS Knob to highlight the desired setting and press the ENT Key.

5) To cancel the selection, press the FMS Knob or the CLR Key.

large FMS

Knob to highlight ‘Selected’ in the ‘GPS CDI’ box.

Figure 2-24 System Setup Page,

GPS CDI Settings

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2.0 nm

Enroute

(Oceanic if >200 nm from nearest airport)

0.3 nm

Missed

Approach

1.0 nm

Approach

1.0 nm

Terminal

1.0 nm

Terminal

0.3 nm

Departure

CDI Full-scale Deflection

31 nm from Destination Airport

30 nm from Departure Airport

Refer to accompanying

approach CDI scaling figures

When set to ‘Auto’ (default), the GPS CDI scale automatically adjusts to the desired limits based upon the

current phase of ﬂight (Figure 2-25, Table 2-1).

Figure 2-25 Automatic CDI Scaling

• Once a departure procedure is activated, the CDI is scaled for departure (0.3 nm).

• The system switches from departure to terminal CDI scaling (1.0 nm) under the following conditions:

- The next leg in the procedure is not aligned with the departure runway

The next leg in the departure procedure is not CA, CD, CF, CI, CR, DF, FA, FC, FD, FM, IF, or TF (see Glossary for leg type deﬁnitions)

- After any leg in the departure procedure that is not CA or FA

• At 30 nm from the departure airport (or at the last departure waypoint if more than 30 nm from the departure airport), the enroute phase of ﬂight is automatically entered and CDI scaling changes to 2.0 nm over a distance of 1.0 nm.

• If after completing the departure procedure the nearest airport is more than 200 nm away from the aircraft and the approach procedure has not yet commenced, the CDI is scaled for oceanic ﬂight (2.0 nm).

• Within 31 nm of the destination airport (terminal area), the CDI scale gradually ramps down from 2.0 nm to 1.0 nm over a distance of 1.0 nm; if a transition back to enroute ﬂight occurs, the CDI scale increases back to 2.0 in the same manner.

• During approach, the CDI scale ramps down even further (see Figures 2-26 and 2-27). This transition normally occurs within 2.0 nm of the ﬁnal approach ﬁx (FAF). The CDI switches to approach scaling automatically once the approach procedure is activated or if Vector-to-Final (VTF) is selected.

- If the active waypoint is the FAF, the ground track and the bearing to the FAF must be within 45° of the

ﬁnal approach segment course.

- If the active waypoint is part of the missed approach procedure, the active leg and preceding missed

approach legs must be aligned with the ﬁnal approach segment course and the aircraft must not have passed the turn initiation point.

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1.0 nm

2 nm

FAF

0.3 nm

course width

Landing

Threshold

CDI Full-scale Deflection

angle based on database information

CDI scale varies if VTF is activated

1.0 nm

2 nm

350 ft

angle set by system

0.3 nm

FAF

CDI Full-scale Deflection

CDI scale is set to the smaller of 0.3 nm

or an angle set by the syste

CDI scale varies if VTF is activated

Figure 2-26 Typical LNAV and LNAV+V Approach CDI Scaling

Figure 2-27 Typical LNAV/VNAV and LPV Approach CDI Scaling

• When a missed approach is activated, the CDI scale changes to 0.3 nm.

• The system automatically switches back to terminal scaling under the following conditions:

- The next leg in the missed approach procedure is not aligned with the ﬁnal approach path

The next leg in the missed approach procedure is not CA, CD, CF, CI, CR, DF, FA, FC, FD, FM, IF, or TF

- After any leg in the missed approach procedure that is not CA or FA

Flight Phase Annunciation Automatic CDI Full-scale Deﬂection

Departure DPRT 0.3 nm Terminal

TERM 1.0 nm

Enroute ENR 2.0 nm Oceanic OCN 2.0 nm

Approach (Non-precision)

Approach (Non-precision with

LNAV

1.0 nm decreasing to 350 feet depending on variables (see Figure 2-26)

LNAV + V

Vertical Guidance) Approach

(LNAV/VNAV) Approach

(LPV)

L/VNAV

LPV

1.0 nm decreasing to a speciﬁed course width, then

0.3 nm, depending on variables (see Figure 2-27)

Missed Approach MAPR 0.3 nm

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Table 2-1 Automatic GPS CDI Scaling

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OBS MODE

NOTE:

VNV is inhibited while automatic waypoint sequencing has been suspended.

Enabling Omni-bearing Selector (OBS) Mode suspends the automatic sequencing of waypoints in a GPS ﬂight plan (GPS must be the selected navigation source), but retains the current “active-to” waypoint as the navigation reference even after passing the waypoint. ‘OBS’ is annunciated to the lower right of the aircraft symbol when OBS Mode is selected (see Figure 2-28).

While OBS Mode is enabled, a course line is drawn through the “active-to” waypoint on the moving map. If desired, the course to/from the waypoint can now be adjusted. When OBS Mode is disabled, the GPS ﬂight plan returns to normal operation with automatic sequencing of waypoints, following the course set in OBS Mode. The ﬂight path on the moving map retains the modiﬁed course line.

Enabling/disabling OBS Mode while navigating a GPS ﬂight plan:

1) Select the OBS Softkey to select OBS Mode.

2) Turn the CRS Knob to select the desired course to/from the waypoint. Press the CRS Knob to synchronize the

Selected Course with the bearing to the next waypoint.

3) Select the OBS Softkey again to return to automatic waypoint sequencing.

GPS Selected

Extended

Course Line

Pressing the

Suspends Waypoint Sequencing

OBS

Softkey

OBS Mode Enabled

Pressing the

Returns to Normal Operation

Figure 2-28 Omni-bearing Selector (OBS) Mode

OBS

Softkey Again

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As the aircraft crosses the missed approach point (MAP), automatic approach waypoint sequencing is

suspended. ‘SUSP’ appears on the HSI (to the lower right of the aircraft symbol) in place of ‘OBS’ and the

OBS

Softkey label changes to SUSP.

SUSP Annunciation

SUSP

Softkey Suspends

Waypoint Sequencing

Figure 2-29 Suspending Automatic Waypoint Sequencing

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2.2 SUPPLEMENTAL FLIGHT DATA

NOTE:

Selecting the DFLTS Softkey (a second-level PFD softkey) turns off metric Altimeter display, the Inset

Map, and wind data display.

In addition to the ﬂight insturments, the PFD also displays various supplemental information, including a generic timer, the Outside Air Temperature (OAT), wind data, the system time, and Vertical Navigation (VNV) indications.

GENERIC TIMER

The Timer/References Window contains a generic timer, which can be set to count up or down from a speciﬁed time (HH:MM:SS). When the countdown on the timer reaches zero, the digits begin to count up from zero. If the timer is reset before reaching zero on a countdown, the digits are reset to the initial value. If the timer is counting up when reset, the digits are zeroed.

Figure 2-30 Timer/References Window

Setting the generic timer:

1) Select the

2) Turn the

3) Use the FMS Knob to enter the desired time and press the

4) With the UP/DN ﬁeld highlighted, turn the

5) Press the

6) With ‘START?’ highlighted, press the

7) To stop the timer, press the ENT Key with ‘STOP?’ highlighted. The ﬁeld changes to ‘RESET?’.

8) To reset the timer, press the ENT Key with ‘RESET?’ highlighted. The ﬁeld changes back to ‘START?’ and the

digits are reset.

9) To remove the window, press the

TMR/REF

large FMS

ENT

Key.

Softkey.

Knob to select the timer ﬁeld (hh/mm/ss).

ENT

Key.

small FMS

ENT

Key to start the timer. The ﬁeld changes to ‘STOP?’.

CLR

Key or the

Knob to select the timer counting direction.

TMR/REF

Softkey.

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OUTSIDE AIR TEMPERATURE

The Outside Air Temperature (OAT) is displayed in degrees Celsius (°C) in the lower left of the PFD under

normal display conditions, or below the true airspeed in reversionary mode.

Normal Display Reversionary Mode

Figure 2-31 Outside Air Temperature

WIND DATA

Wind direction and speed (relative to the aircraft) in knots can be displayed in a window to the upper left of the HSI. When the window is selected for display, but wind information is invalid or unavailable, the window shows “NO WIND DATA”. Wind data can be displayed in three different ways:

• Head and crosswind components (Option 1)

• Total wind direction and speed (Option 2)

• Total wind direction with head and crosswind speed components (Option 3)

Option 2Option 1

Option 3

Figure 2-32 Wind Data

No Data

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SYSTEM TIME

The system time is displayed in the lower right corner of the PFD. Three display formats are available, local 12-hr, local 24-hr, and Coordinated Universal Time (UTC). Time and date are obtained from the GPS satellites and cannot be changed, although a time offset may be entered (±HH:MM) for local times.

Figure 2-33 System Time

Conﬁguring the system time:

1) Select the AUX - System Setup Page using the FMS Knob.

2) Press the FMS Knob to activate the cursor.

3) Turn the large FMS Knob to highlight the ‘Time Format’ ﬁeld.

4) Turn the small FMS Knob to select the desired format and press the ENT Key to conﬁrm selection. The ‘Time

Offset’ ﬁeld is highlighted.

5) Use the FMS Knob to enter the desired time offset (±HH:MM) and press the ENT Key to conﬁrm selection.

Figure 2-34 System Setup Page,

Date/Time Settings

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VERTICAL NAVIGATION (VNV) INDICATIONS

When a VNV ﬂight plan has been activated, VNV indications (VNV Target Altitude, RSVI, VDI) appear on the PFD in conjunction with the “TOD within 1 minute” message and “Vertical track” voice alert. See the GPS Navigation section for details on VNV features. VNV indications are removed from the PFD according to the criteria listed in Table 2-2.

Top of Descent Message

VNV Target Altitude

Vertical Deviation Indicator

Required Vertical Speed Bug

GPS is Selected

Navigation Source

Figure 2-35 Vertical Navigation Indications (PFD)

Enroute Phase of Flight

VNV Indication Removed

Criteria

Aircraft > 1 min before the next TOD and not on a descent leg Aircraft > 1 min before the next TOD due to ﬂight plan change

Required Vertical

Speed (RSVI)

X X X X X X

Vertical

Deviation (VDI)

VNV Target

Altitude

VNV cancelled (CNCL VNV Softkey selected on MFD) X X X Distance to active waypoint cannot be computed due to

unsupported ﬂight plan leg type (see GPS Navigation Section) Aircraft > 250 feet below active VNV Target Altitude Current crosstrack or track angle error has exceeded limit Active altitude-constrained waypoint can not be reached within

maximum allowed ﬂight path angle and vertical speed

Last altitude-constrained waypoint in active ﬂight plan reached

X X X

X X X X X X

X X

(30 sec before)

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Table 2-2 VNV Indication Removal Criteria

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2.4 PFD ANNUNCIATIONS AND ALERTING FUNCTIONS

The following annunciations and alerting functions are displayed on the PFD. Refer to Appendix A for more

information on alerts and annunciations.

SYSTEM ALERTING

Messages appear in the Alerts Window (in the lower right corner of the PFD; Figure 2-36) when a warning, caution, advisory alert, or G900X message advisory occurs. System alert messages are provided for aware of G900X system problems or status and may not require pilot action. The Alerts Window allows system alerts to be displayed simultaneously. The FMS Knob can be used to scroll through the alert messages. The Alerts Window is enabled/disabled by selecting the message is generated, selecting the ALERTS Softkey to acknowledge the message causes it to turn gray.

The Annunciation Window appears to the right of the Vertical Speed Indicator and displays abbreviated annunciation text for aircraft alerts. Text color is based on alert level: warnings appear in red, cautions in yellow, advisory alerts in white. New alerts, regardless of priority, are displayed at the top of the Annunciation Window, separated by a white line from acknowledged alerts. Once acknowledged, they are sequenced based on priority.

ALERTS

Softkey. If the window is already open when a new

Annunciation Window

Alerts Window

Softkey Annunciation

Figure 2-36 G900X Alerting System

The ALERTS Softkey label changes to display the appropriate annunciation when an alert is issued. The annunciation ﬂashes and the appropriate aural alert sounds until acknowledged by pressing the softkey. The softkey then reverts to the ALERTS Softkey label, and when selected again opens the Alerts Window to display a descriptive message of the alert.

Warnings are time-critical and require immediate pilot attention. A ﬂashing WARNING Softkey annunciation and aural tone (single chime every two seconds) indicate the presence of a warning. The aural tone and ﬂashing

WARNING Softkey annunciation continue until acknowledged (by pressing the

WARNING

Softkey).

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Caution indicates the existence of abnormal conditions on the aircraft that may require pilot intervention. A ﬂashing CAUTION Softkey annunciation and single aural tone (one chime) indicate the presence of a caution. The ﬂashing CAUTION Softkey annunciation continues to ﬂash until acknowledged (by pressing the Softkey).

An advisory provides general information to the pilot that may not need immediate attention. A ﬂashing

ADVISORY Softkey annunciation (no aural tone) indicates the presence of a message advisory. The ﬂashing ADVISORY Softkey annunciation continues to ﬂash until acknowledged (by pressing the

Softkey).

Figure 2-37 Softkey Annunciation (ALERTS Softkey Labels)

CAUTION

ADVISORY

TRAFFIC ANNUNCIATION

The G900X System displays trafﬁc symbolically on the PFD Inset Map, the Navigation Map Page (MFD), and various other MFD page maps. Refer to the Hazard Avoidance Section and Appendix E for more details about the Trafﬁc Information Service (TIS) and optional Trafﬁc Advisory Systems (TAS). When a trafﬁc advisory (TA) is detected, the following automatically occur:

• The PFD Inset Map is enabled and displays trafﬁc

• A ﬂashing black-on-yellow ‘TRAFFIC’ annunciation (Figure 2-38) appears to the top left of the Attitude

Indicator for ﬁve seconds and remains displayed until no TAs are detected in the area

• A single “Trafﬁc” aural alert is generated, unless an optional Trafﬁc Advisory System (TAS) is installed (refer

to the applicable TAS documentation for alerts generated by TAS equipment)

If additional TAs appear, new aural and visual alerts are generated.

TAWS ANNUNCIATIONS (OPTIONAL)

Terrain Awareness and Warning System (TAWS) annunciations appear on the PFD to the upper left of the Altimeter. Refer to the Hazard Avoidance Section and Appendix A for information on TAWS alerts and annunciations.

Inset Map Enabled,

Displaying Trafﬁc

When TA Detected

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Figure 2-38 Trafﬁc and Example TAWS Annunciations

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MARKER BEACON ANNUNCIATIONS

Marker Beacon Annunciations are displayed on the PFD to the left of the Selected Altitude. Outer marker reception is indicated in blue, middle in yellow, and inner in white. Refer to the Audio Panel and CNS Section for more information on Marker Beacon Annunciations.

Inner MarkerMiddle MarkerOuter Marker

Altimeter

Figure 2-39 Marker Beacon Annunciations

ALTITUDE ALERTING

The Altitude Alerting function provides visual and aural alerts when the aircraft is approaching the Selected Altitude. Whenever the Selected Altitude is changed, the Altitude Alerter is reset. The Altitude Alerter is independent of the installed AFCS. The following occur when approaching the Selected Altitude:

• Upon passing through 1000 feet of the Selected Altitude, the Selected Altitude (shown above the Altimeter)

changes to black text on a light blue background, ﬂashes for 5 seconds, and an aural tone is generated.

• When the aircraft passes within 200 ft of the Selected Altitude, the Selected Altitude changes to light blue text

on a black background and ﬂashes for 5 seconds.

• After reaching the Selected Altitude, if the aircraft ﬂies outside the deviation band (±200 feet of the Selected

Altitude), the Selected Altitude changes to yellow text on a black background, ﬂashes for 5 seconds, and an

aural tone is generated.

Within 1000 feet Within 200 feet Deviation of ±200 feet

Figure 2-40 Altitude Alerting Visual Annunciations

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LOW ALTITUDE ANNUNCIATION

FLIGHT INSTRUMENTS

NOTE:

This annunciation is not shown for systems with TAWS, unless TAWS is inhibited.

When the Final Approach Fix (FAF) is the active waypoint in a GPS WAAS approach using vertical guidance, a Low Altitude Annunciation may appear if the current aircraft altitude is at least 164 feet below the prescribed altitude at the FAF. A black-on-yellow ‘LOW ALT’ annunciation appears to the top right of the Altimeter, ﬂashing for several seconds then remaining displayed until the condition is resolved.

Altimeter

Figure 2-41 Low Altitude on GPS WAAS Approach

MINIMUM DESCENT ALTITUDE/DECISION HEIGHT ALERTING

For altitude awareness, a barometric Minimum Descent Altitude (MDA, or Decision Height, DH) can be set in the Timer/References Window and is reset when the power is cycled. When active, the altitude setting is displayed to the lower left of the Altimeter and with a bug at the corresponding altitude along the Altimeter (once the altitude is within the range of the tape). The following visual annunciations occur when approaching the MDA/DH:

• When the aircraft altitude descends to within 2500 feet of the MDA/DH setting, the ‘BARO MIN’ box appears

with the altitude in light blue text. The bug appears on the altitude tape in light blue once in range.

• When the aircraft passes through 100 feet of the MDA/DH, the bug and text turn white.

• Once the aircraft reaches the MDA/DH, the bug and text turn yellow and the aural alert, “Minimums

Minimums”, is generated.

Alerting is inhibited while the aircraft is on the ground and until the aircraft reaches 150 feet above the setting for the alert. If the aircraft proceeds to climb after having reached the MDA/DH, once it reaches 50 feet above the MDA/DH, alerting is disabled.

Altitude ReachedWithin 100 feetWithin 2500 feet

MDA/DH Bug

MDA/DH Setting

Figure 2-42 Minimum Descent Altitude/Decision Height Alerting Visual Annunciations

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Setting the barometric minimum descent altitude/decision height and bug:

1) Select the

2) Turn the large FMS Knob to highlight the ‘Minimums’ ﬁeld (Figure 2-43).

3) Turn the small FMS Knob to select BARO. OFF is selected by default. Press the ENT Key or turn the large FMS

TMR/REF

Softkey.

Knob to highlight the next ﬁeld.

4) Use the small FMS Knob to enter the desired altitude (from zero to 16,000 feet).

5) To remove the window, press the

Figure 2-43 Minimum Descent Altitude/Decision Height

CLR

Key or the

Setting (Timer/References Window)

TMR/REF

Softkey.

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2.5 ABNORMAL OPERATIONS

ABNORMAL GPS CONDITIONS

The annunciations listed in Table 2-3 can appear on the HSI when abnormal GPS conditions occur; see Figure 2-44 for examples. Refer to the GPS Navigation Section for more information on Dead Reckoning Mode.

Annunciation Location Description

LOI

WARN

INTEG OK

Lower left of

aircraft symbol

Lower left of

aircraft symbol

Lower left of

aircraft symbol

Upper right of

aircraft symbol

Loss of Integrity Monitoring–GPS integrity is insufﬁcient for the current phase of ﬂight

Warning–RAIM function detects excessive GPS position errors

Integrity OK–GPS integrity has been restored to within normal limits (annunciation displayed for 5 seconds)

Dead Reckoning–System is using projected position rather than GPS position to compute navigation data and sequence active ﬂight plan waypoints

Table 2-3 Abnormal GPS Conditions Annunciated on HSI

Figure 2-44 Example HSI Annunciations

Dead Reckoning Mode causes the CDI to be removed from the display (when GPS is the selected navigation source) and the following items on the PFD to be shown in yellow:

• Current Track Bug

• Wind Data (calculated based on GPS information)

• Distances in the Bearing Information windows

• GPS bearing pointers

These items should be veriﬁed when operating in Dead Reckoning Mode.

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FLIGHT INSTRUMENTS

UNUSUAL ATTITUDES

When the aircraft enters an unusual pitch attitude, red extreme pitch warning chevrons pointing toward the

horizon are displayed on the Attitude Indicator, starting at 50˚ above and 30˚ below the horizon line.

Nose LowNose High

Figure 2-45 Pitch Attitude Warnings

If pitch exceeds +30˚/-20˚ or bank exceeds 65˚, some information displayed on the PFD is removed. The Altimeter and Airspeed, Attitude, Vertical Speed, and Horizontal Situation indicators remain on the display and the Bearing Information, Alerts, and Annunciation windows can be displayed during such situations. The following information is removed from the PFD (and corresponding softkeys are disabled) when the aircraft experiences unusual attitudes:

• Trafﬁc Annunciations

• Inset Map

• Outside air temperature (OAT)

• Wind data

• Transponder Status Box

• System Time

• PFD Setup Menu

• Windows displayed in the lower right corner of the PFD:

– Timer/References

– Nearest Airports

– Flight Plan

– Alerts

– Procedures

• Barometric Minimum Descent Altitude readout

• Vertical Deviation, Glideslope, and Glidepath Indicators

• Altimeter Barometric Setting

• Selected Altitude

• VNV Target Altitude

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ENGINE INDICATION SYSTEM

SECTION 3 ENGINE INDICATION SYSTEM

NOTE:

during the software conﬁguration process. Engine gauges, ranges, color bands, and caution and warning indications are established based on the engine manufacturer’s recommended guidance.

The G900X Engine Indication System (EIS) displays critical engine, electrical, fuel, and other system parameters on the left side of the MFD during normal operations (Figure 3-1). EIS information can be fully expanded to an entire page (EIS - Engine Page) using the ENGINE Softkey (see Section 3.1).

EIS Display

The G900X Engine Indication System (EIS) is established based on the installed engine selected

Green bands on the instruments indicate normal ranges of operation; yellow and red bands indicate caution and warning, respectively. White or uncolored bands indicate areas outside of normal operation not yet in the caution or warning ranges. When unsafe operating conditions occur, the corresponding readouts ﬂash to indicate cautions and warnings. If sensory data to an instrument becomes invalid or unavailable, a red “X” is displayed across the instrument.

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Figure 3-1 MFD

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3-1

Page 94

ENGINE INDICATION SYSTEM

EIS indicators shown depend on the engine installed and the aircraft model. The EIS is available for the kitbuilt aircraft/engine combinations listed in Table 3-1. Screenshots in this section attempt to depict example aircraft/engine combinations for which all sensors have been conﬁgured . Not all possible displays are shown, nor are the conditions shown on the indicators meant to approximate realistic ﬂight conditions.

Lancair Van’s

Aircraft IV/IV-P

Engine

Models

ES/ES-P Legacy RV-7/7A RV-9/9A RV-10

TSIO-550-E

IO-550-N

IO-360-A*, -C*, -D*, -J*, -K*, -AIO-360*

(200 hp)

IO-360-M1A, -M1B, -B* (not -B1C or -B1A),

-E*, -F* (180 hp)

O-360-A* (not A1C or A4FN), -C* (not -C2B

or -C2D)

O-320-B*, -D*

Table 3-1 G900X EIS Supported Combinations

IO-540-D4A5, -D4B5,

-N1A5, -T4A5D,

-T4B5, -T4B5D,

-T4C5D, -V4A5D

O-540-A*, -B*, -D*

(not D2J), -E*

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3.1 EIS DISPLAY

ENGINE INDICATION SYSTEM

Engine Manifold Pressure

Gauge (MAN IN HG)

Tachometer (RPM)

Fuel Quantity Indicator

(FUEL QTY GAL)

Displays manifold pressure in inches of Mercury (in Hg) to indicate engine power

Displays propeller speed in revolutions per minute (rpm)

Displays the amount of fuel in gallons (gal) for each side (left-L, right-R) of

a standard fuel tank. Standard fuel tank quantities are based on published kitplane manufacturing data.

A light blue marker is displayed next to the selected fuel tank (optional)

Aircraft

IV/IV-P

ES-P 52.5

Legacy 32.5 RV-7/7A RV-9/9A

RV-10

Maximum Standard Fuel

Quantity (gal) Per Side

47.5

21 18 30

Fuel Flow Indicator

(FFLOW GPH)

Oil Pressure Indicator

(OIL PSI)

Oil Temperature Indicator

(OIL °F)

Exhaust Gas Temperature

Indicator (EGT °F)

Turbo Inlet Temperature

Indicator (TIT °F)

TSIO-550-E only

Carburetor Temperature

Indicator

O-540-series, O-360-series, O-320-series

Cylinder Head Temperature

Indicator (CHT °F)

Table 3-2 Displayed Fuel Quantities

Displays fuel ﬂow in gallons per hour (gph)

Displays oil pressure in pounds per square inch (psi)

Displays oil temperature in degrees Fahrenheit (°F)

Displays the Exhaust Gas Temperature of the hottest cylinder (number is

shown in pointer) in °F

Displays the temperature for the right (R) and left (L) turbo inlets in °F; the

left readout corresponds to the “L” indication, and the right readout to the “R” indication

Displays carburetor temperature in °F; the blue range indicates where

carburetor icing is most likely to occur

Displays the head temperature of the hottest cylinder (number is shown in

pointer) in °F

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ENGINE INDICATION SYSTEM

Flap Position and Trim

Indicators (FLAPS, ELEV TRIM, RUDDER TRIM, AILERON TRIM)

Displays ﬂap position and elevator, rudder, and aileron trim along slide bars

Up to three trim indicators may be installed; aileron and rudder trim are

mutually exclusive.

TSIO-550-E

Figure 3-2 EIS Displays

IO-550-N

(IV/IV-P Shown)

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ENGINE INDICATION SYSTEM

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IO-540-series

Garmin G900X Pilot’s Guide

O-540-series

Figure 3-3 EIS Displays

(RV-10 Shown)

3-5

Page 98

ENGINE INDICATION SYSTEM

IO-360-series

(180 hp)

Garmin G900X Pilot’s Guide

IO-360-series

(200 hp)

Figure 3-4 EIS Displays

(RV-9/9A Shown)

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ENGINE INDICATION SYSTEM

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O-360-series

Garmin G900X Pilot’s Guide

O-320-series

Figure 3-5 EIS Displays

(RV-9/9A Shown)

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ENGINE INDICATION SYSTEM

ENGINE

Select the ENGINE Softkey to return to the top-level softkeys.

INC FUEL

RST FUEL

DCLTR

ASSIST

DEC FUEL

ENGINE

CO RST

(optional)

3.2 ENGINE PAGE

Selecting the ENGINE Softkey accesses the EIS - Engine Page, which displays all engine, fuel, fuel calculation,

electrical, and trim information.

Figure 3-6 Engine Page Softkeys

ENGINE DCLTR ASSIST CO RST DEC FUEL INC FUEL RST FUEL

Engine Manifold Pressure

Displays EIS - Engine Page and second-level engine softkeys; press again to exit page Turns off CHT and EGT cylinder readouts Accesses Leaning Assist Mode Resets CO Guardian; softkey enabled when carbon monoxide alert generated ( Decreases displayed fuel remaining in 1-gal increments Increases displayed fuel remaining in 1-gal increments Resets displayed fuel remaining to maximum fuel capacity for aircraft and fuel used to zero

Gauge (MAN IN HG)

Tachometer (RPM)

Electrical Group

(ELECTRICAL)

Engine Temperature Group

(TEMPERATURE)

optional)

Displays manifold pressure in inches of Mercury (in Hg) to indicate engine power

Displays propeller speed in revolutions per minute (rpm) Overspeed warning: 2700 rpm for all but IO-540 (2575 rpm)

Displays alternator (ALT A) and battery (BATT A) currents in amperes (A)

and main (MAIN V) and essential (ESS V) bus voltages (V) for 14- or 28V systems; an Auxiliary Ammeter can be displayed if an optional standby alternator or battery is installed

The ammeter scales are dependent on the installed alternator.

Displays exhaust gas (EGT) and head (CHT) temperatures of all cylinders in °F

TSIO-550-E only: Displays Turbo Inlet Temperature (TIT) in °F O-540-series, O-360-series, O-320-series: Displays carburetor temperature

(CARB) in °F; the blue range indicates where carburetor icing is most likely to occur

Fuel Calculations Group

(FUEL CALC)

Displays calculated fuel used (GAL USED), endurance (ENDUR), and range

(in nautical miles, RANGE NM), and fuel efﬁciency (in statute miles per gallon, MPG) based on the displayed fuel remaining (GAL REM) and the fuel ﬂow totalizer

Garmin G900X Pilot’s Guide

190-00726-00 Rev. A3-8

Garmin G900X Pilot’s Guide

Specifications and Main Features

Frequently Asked Questions

User Manual

SECTION 1 SYSTEM OVERVIEW

1.1 LINE REPLACEABLE UNITS

1.2 SECURE DIGITAL (SD) CARDS

1.3 SYSTEM POWER-UP

1.4 SYSTEM OPERATION

DISPLAY OPERATION

G900X SYSTEM ANNUNCIATIONS

SYSTEM STATUS

AHRS OPERATION

GPS RECEIVER OPERATION

1.5 G900X CONTROLS

PFD/MFD CONTROLS

MFD/PFD CONTROL UNIT (OPTIONAL)

SOFTKEY FUNCTION

1.6 ACCESSING G900X FUNCTIONALITY

MENUS

DATA ENTRY

PAGE GROUPS

SYSTEM SETTINGS

SYSTEM UTILITIES

ELECTRONIC CHECKLISTS (OPTIONAL)

1.7 DISPLAY BACKLIGHTING

SECTION 2 FLIGHT INSTRUMENTS

2.1 FLIGHT INSTRUMENTS

AIRSPEED INDICATOR

ATTITUDE INDICATOR

ALTIMETER

VERTICAL SPEED INDICATOR (VSI)

VERTICAL DEVIATION, GLIDESLOPE, AND GLIDEPATH INDICATORS

HORIZONTAL SITUATION INDICATOR (HSI)

COURSE DEVIATION INDICATOR (CDI)

2.2 SUPPLEMENTAL FLIGHT DATA

GENERIC TIMER

OUTSIDE AIR TEMPERATURE

WIND DATA

SYSTEM TIME

VERTICAL NAVIGATION (VNV) INDICATIONS

2.4 PFD ANNUNCIATIONS AND ALERTING FUNCTIONS

SYSTEM ALERTING

TRAFFIC ANNUNCIATION

TAWS ANNUNCIATIONS (OPTIONAL)

MARKER BEACON ANNUNCIATIONS

ALTITUDE ALERTING

LOW ALTITUDE ANNUNCIATION

MINIMUM DESCENT ALTITUDE/DECISION HEIGHT ALERTING

2.5 ABNORMAL OPERATIONS

ABNORMAL GPS CONDITIONS

UNUSUAL ATTITUDES

SECTION 3 ENGINE INDICATION SYSTEM

3.1 EIS DISPLAY

3.2 ENGINE PAGE