Garmin G900X Pilot’s Guide
TM
Integrated Flight Deck
G900X
Pilot’s Guide
Copyright © 2007 Garmin Ltd. or its subsidiaries. All rights reserved.
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
LIMITED WARRANTY
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
i
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
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:
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.
190-00726-00 Rev. A
Garmin G900X Pilot’s Guide
iii
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
190-00726-00 Rev. Aiv
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
v
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
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
190-00726-00 Rev. A
Garmin G900X Pilot’s Guide
vii
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
190-00726-00 Rev. Aviii
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
ix
TABLE OF CONTENTS
BLANK PAGE
Garmin G900X Pilot’s Guide
190-00726-00 Rev. Ax
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
190-00726-00 Rev. A
Garmin G900X Pilot’s Guide
1-1
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
190-00726-00 Rev. A1-2
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
190-00726-00 Rev. A
Garmin G900X Pilot’s Guide
1-3
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
190-00726-00 Rev. A1-4
SYSTEM OVERVIEW
GTX 33
Transponder
Reversionary
Control
GEA 71
Engine/Airframe
Unit
GDC 74A
Air Data
Computer
OAT
Airspeed
Altitude
Ve
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
190-00726-00 Rev. A
Garmin G900X Pilot’s Guide
1-5
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
Garmin G900X Pilot’s Guide
190-00726-00 Rev. A1-6
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
190-00726-00 Rev. A
Garmin G900X Pilot’s Guide
1-7
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
Garmin G900X Pilot’s Guide
190-00726-00 Rev. A1-8
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.
190-00726-00 Rev. A
Figure 1-6 G900X Normal Operation
Garmin G900X Pilot’s Guide
1-9
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
OR
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
190-00726-00 Rev. A1-10
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.
190-00726-00 Rev. A
Figure 1-9 Example System Status Page
Garmin G900X Pilot’s Guide
1-11
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.
Garmin G900X Pilot’s Guide
190-00726-00 Rev. A1-12
AHRS OPERATION
Attitude/Heading Invalid
AHRS
no-GP
S
Mode
AHRS Normal
Operation
AHRS no-
Mag Mode
AHRS no-Mag/
no-Air Mode
Heading Invalid
available
available
unavailable
una
vailable
available
unavailable
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.
190-00726-00 Rev. A
Figure 1-10 AHRS Operation
Garmin G900X Pilot’s Guide
1-13
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
190-00726-00 Rev. A1-14
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
190-00726-00 Rev. A
Garmin G900X Pilot’s Guide
1-15
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
Garmin G900X Pilot’s Guide
190-00726-00 Rev. A1-16
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
190-00726-00 Rev. A
Garmin G900X Pilot’s Guide
1-17
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
18
1
2
3
4
5
17
6
7
9
8
10
11
12
16
13
14
15
1
NAV VOL/ID Knob
2
NAV Frequency
Transfer Key
3
NAV Knob
4
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
Garmin G900X Pilot’s Guide
190-00726-00 Rev. A1-18
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