Garmin G1000, DA40F Diamond DA40
Diamond
DA40/40F
Copyright © 2006 Garmin Ltd. or its subsidiaries. All rights reserved.
This manual reflects the operation of System Software version 369.11 or later for the Diamond DA40 or DA40F. 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.
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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
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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
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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 G1000® is a trademark of Garmin Ltd. or its subsidiaries. These
trademarks may not be used without the express permission of Garmin.
Bendix/King® and Honeywell® are registered trademarks of Honeywell International, Inc.; Becker® is a registered trademark of Becker
®
Flugfunkwerk GmbH; NavData
is a registered trademark of Jeppesen, Inc.; and XM® is a registered trademark of XM Satellite Radio,
Inc..
July 2006 Printed in the U.S.A.
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
190-00592-02 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.
To obtain warranty service, contact your local Garmin Authorized Service Center. For assistance in locating a Service Center near you, visit
the Garmin Website at “http://www.garmin.com” or contact Garmin Customer Service at 800-800-1020.
190-00592-02 Rev. A
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
i
WARNINGS, CAUTIONS, AND NOTES
WARNING:
Navigation and terrain separation must NOT be predicated upon the use of the terrain function.
The G1000 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:
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:
The Garmin G1000, as installed in Diamond DA40/40F aircraft, 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 G1000. 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:
The altitude calculated by G1000 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 G1000 PFD or other pressure altimeters in aircraft.
WARNING:
The Jeppesen database used in the G1000 system must be updated regularly in order to ensure
that its information remains current. Updates are released every 28 days. A database information packet is
included in the G1000 package. Pilots using an outdated database do so entirely at their own risk.
WARNING:
The basemap (land and water data) must not be used for navigation, but rather only for nonnavigational situational awareness. Any basemap indication should be compared with other navigation
sources.
WARNING:
Traffic information shown on the G1000 Multi Function Display is provided as an aid in visually
acquiring traffic. Pilots must maneuver the aircraft 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 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.
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
190-00592-02 Rev. Aii
WARNINGS, CAUTIONS, AND NOTES
WARNING:
CAUTION:
For safety reasons, G1000 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 G1000 utilize GPS as a precision electronic
NAVigation AID (NAVAID). Therefore, as with all NAVAIDs, information presented by the G1000 can be
misused or misinterpreted and, therefore, become unsafe.
CAUTION:
To reduce the risk of unsafe operation, carefully review and understand all aspects of the G1000
Pilot’s Guide documentation and the Diamond DA40/40F Aircraft Flight Manual. Thoroughly practice basic
operation prior to actual use. During flight operations, carefully compare indications from the G1000 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.
CAUTION:
The illustrations in this guide are only examples. Never use the G1000 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 G1000 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 104X 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 G1000 panel
and displays, are subject to change and may not reflect the most current G1000 system. Depictions of
equipment may differ slightly from the actual equipment.
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.
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. If you have any questions or would like additional information, please refer to
our web site at www.garmin.com/prop65.
190-00592-02 Rev. A
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
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REVISION INFORMATION
Record of Revisions
Part Number
190-00592-00
190-00592-01
190-00592-02
Revision Date Page Range Description
A
A
A
11/10/05
6/16/06
7/20/06
i – I-6
i – I-4
i – I-4
Initial release (optional fuel pressure gauge information added)
Initial release (GFC 700 information added)
Initial release (TAWS, GDL 69A crew muting information added)
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
190-00592-02 Rev. Aiv
TABLE OF CONTENTS
SECTION 1 SYSTEM OVERVIEW
1.1 System Description ..............................................1-1
1.2 Line Replaceable Units ........................................1-2
1.3 Secure Digital (SD) Cards ....................................1-7
1.4 System Power-up ..................................................1-8
1.5 System Operation .................................................1-9
Normal Display Operation ..........................................1-9
Reversionary Display Operation ..................................1-9
G1000 System Annunciations ...................................1-10
AHRS Operation ......................................................1-11
GPS Receiver Operation ...........................................1-12
1.6 G1000
Controls ...................................................1-15
PFD/MFD Controls ...................................................1-15
Softkey Function ......................................................1-17
1.7 Accessing G1000 Functionality ........................1-22
Menus ....................................................................1-22
Data Entry ..............................................................1-22
Page Groups ...........................................................1-23
System Setup and Status ..........................................1-27
System Utilities ........................................................1-36
Electronic Checklists (Optional) ................................. 1-40
1.8 Display Backlighting ..........................................1-42
SECTION 2 FLIGHT INSTRUMENTS
2.1 Introduction ..........................................................2-1
2.2 Flight Instruments ................................................2-4
Airspeed Indicator .....................................................2-4
Attitude Indicator ......................................................2-6
Altimeter ..................................................................2-7
Vertical Deviation/Glideslope Indicator ........................2-9
Vertical Speed Indicator (VSI) ......................................2-9
Horizontal Situation Indicator (HSI) ...........................2-10
DME Information Window ........................................2-16
2.3 Supplemental Flight Data .................................2-17
Timer/References Window ........................................2-17
Outside Air Temperature ........................................... 2-18
System Time ............................................................2-19
2.4 PFD Annunciations and Alerting Functions .....
Alerts Window .........................................................2-20
Annunciation Window ..............................................2-20
Softkey Annunciations .............................................. 2-21
Marker Beacon Annunciations ..................................2-21
2-20
Traffic Annunciation ................................................. 2-22
TAWS Annunciations ................................................ 2-22
Altitude Alerting ......................................................2-22
Barometric Minimum Descent Altitude .......................2-23
SECTION 3 ENGINE INDICATION SYSTEM
3.1 Engine Display ......................................................3-2
3.2 Lean Display ..........................................................3-4
3.3 System Display .....................................................3-6
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
Stuck Microphone ......................................................4-7
COM Transceiver Manual Tuning .................................4-8
COM Tuning Failure .................................................... 4-8
Quick-tuning and Activating 121.500 MHz ................... 4-9
Auto-tuning the COM Frequency ...............................4-10
Frequency Spacing ................................................... 4-13
Automatic Squelch ................................................... 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 ...........................................4-21
ADF/DME Tuning (Optional) ......................................4-22
4.4 GTX 33 Mode S Transponder ............................. 4-26
Transponder Softkey Controls ...................................4-26
Transponder Mode Selection ..................................... 4-27
Flight ID Reporting ..................................................4-31
4.5 Additional Audio Panel Functions ....................4-32
Power-up and Fail-safe Operation .............................4-32
Mono/Stereo Headsets .............................................4-32
Speaker ..................................................................4-32
Intercom .................................................................4-33
Passenger Address (PA) System ................................. 4-34
Clearance Recorder and Player ..................................4-35
Entertainment Inputs ...............................................4-35
Reversionary Mode ..................................................4-36
4.6 Preflight Procedure for the Audio Panel .........
4-37
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TABLE OF CONTENTS
SECTION 5 GPS NAVIGATION
5.1 Navigation Map (MFD) ........................................5-2
Navigation Map Page Setup and Operation ..................5-2
5.2 PFD Inset Map and Windows ............................5-25
Inset Map ...............................................................5-25
PFD Windows ..........................................................5-26
5.3 Direct-to-Navigation (MFD) .............................5-28
Direct-to Navigation Shortcuts from the MFD .............5-32
5.4 Direct-to-Navigation (PFD) ...............................5-33
5.5 Airport Information ...........................................5-35
5.6 Intersection Information ...................................5-40
5.7 NDB Information ................................................5-42
5.8 VOR Information ................................................. 5-44
5.9 User Waypoint Information ............................... 5-46
5.10 Nearest Airports .................................................5-52
5.11 Nearest Airports (PFD) .......................................5-55
Operations ..............................................................5-55
5.12 Nearest Intersections .........................................
5-57
5.13 Nearest NDB .......................................................5-58
5.14 Nearest VOR ........................................................5-59
5.15 Nearest Frequencies ..........................................5-62
5.16 Nearest Airspaces ............................................... 5-65
5.17 Nearest User Waypoint ......................................5-69
5.18 Flight Planning .................................................... 5-71
Flight Planning from the MFD ................................... 5-71
Trip Planning ........................................................... 5-85
Vertical Navigation .................................................. 5-89
Flight Planning from the PFD ....................................5-92
5.19 Procedures ..........................................................5-96
Departures, Arrivals, and Approaches (MFD) ...............5-96
Departures, Arrivals, and Approaches (PFD) ..............5-106
SECTION 6 HAZARD AVOIDANCE
6.1 XM WX Satellite Weather ....................................6-1
Activating XM WX Satellite Weather and XM Satellite
Radio Services ...........................................................6-1
Using XM WX Satellite Weather Products on the Weather
Data Link Page
Weather Softkeys on the Weather Data Link Page .........6-6
XM WX Satellite Weather on the Navigation Map ....... 6-26
..........................................................6-3
6.2 Terrain Proximity ................................................6-28
Requirements ..........................................................6-28
Limitations ..............................................................6-28
GPS Position and GPS-MSL Altitude ........................... 6-29
Displaying Terrain Proximity Data ..............................6-30
Terrain Proximity Page ..............................................6-31
Navigation Map Page ...............................................6-33
6.3 Terrain Awareness and Warning System (TAWS .....
..............................................................................6-35
Requirements ..........................................................6-35
Limitations ..............................................................6-35
TAWS Alerting Using the GPS Position/GPS-MSL Altitude ....
..............................................................................6-35
Using TAWS ............................................................6-36
6.4 Traffic Information Service (TIS) ....................... 6-47
TIS Symbology .........................................................6-49
Troubleshooting ......................................................6-50
SECTION 7 AUTOMATIC FLIGHT CONTROL SYSTEM
7.1 AFCS Overview .....................................................7-1
AFCS Controls on the MFD .........................................7-2
Additional AFCS Controls ...........................................7-3
7.2 Flight Director Operation ....................................7-4
Activating the Flight Director ...................................... 7-4
Command Bars ..........................................................7-4
AFCS Status Box ........................................................7-5
7.3 Flight Director Modes ..........................................7-6
Pitch Modes ..............................................................7-7
Roll Modes .............................................................. 7-14
7.4 Autopilot Operation ........................................... 7-19
Flight Control ..........................................................7-19
Engaging the Autopilot ............................................7-19
Control Wheel Steering ............................................7-20
Disengaging the Autopilot ........................................7-20
7.5 Example Procedures ...........................................7-21
7.6 AFCS Annunciations and Alerts ........................7-28
AFCS Status Annunciations .......................................7-28
Overspeed Protection ...............................................7-29
SECTION 8 ADDITIONAL FEATURES
8.1 GDL 69A Data Link Receiver – XM Digital Audio
Entertainment (Optional) .................................... 8-1
XM Satellite Radio Service .......................................... 8-1
XM Information Page .................................................8-2
XM Radio Page ..........................................................8-3
Automatic Audio Muting ............................................8-7
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
190-00592-02 Rev. Avi
APPENDICES
Annunciations and Alerts ..............................................A-1
SD Card Use ....................................................................B-1
Glossary ...........................................................................C-1
Frequently Asked Questions .........................................D-1
G1000 Map Datums ....................................................... E-1
General TIS Information ................................................ F-1
Map Symbols ................................................................. G-1
INDEX
TABLE OF CONTENTS
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TABLE OF CONTENTS
BLANK PAGE
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
190-00592-02 Rev. Aviii
SECTION 1 SYSTEM OVERVIEW
1.1 SYSTEM DESCRIPTION
SYSTEM OVERVIEW
NOTE:
The G1000 is an integrated flight deck system that 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 1042
•
GMA 1347
Beacon Receiver
•
GIA 63
•
GDC 74
•
GEA 71
Figure 1-1 shows interactions between the LRUs. Additional/optional equipment are shown in Figure 1-2.
The Diamond DA40/40F may also be optionally equipped with a GFC 700 Automated Flight Control System
(AFCS), providing flight director (FD), autopilot (AP), and manual electric trim (MET) functions of the G1000
System.
Refer to the Automatic Flight Control System (AFCS) Section for details on the GFC 700 AFCS.
Primary Flight Display (PFD)
Multi Function Display (MFD)
Audio Panel with Integrated Marker
Integrated Avionics Units (IAU)
Air Data Computer (ADC)
Engine/Airframe Unit
•
GTX 33
•
GRS 77
(AHRS)
•
GMU 44
•
GDL 69/69A
•
GSA 81
•
GSM 85
Mode S Transponder
Attitude and Heading Reference System
Magnetometer
AFCS Servos
Servo Mounts
Data Link Receiver
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Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
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SYSTEM OVERVIEW
1.2 LINE REPLACEABLE UNITS
• GDU 1040/1042 (2) – A GDU 1040 is configured as the Primary Flight Display (PFD) and a GDU 1040 or
1042 (for airframes equipped with the GFC 700) as a Multi Function Display (MFD). Both displays 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.
•
GIA 63
with the PFD. Each IAU contains very high frequency (VHF) communication/navigation/glideslope (COM/
NAV/GS) receivers and system integration microprocessors and is paired with the on-side display via an HSDB
connection. The IAUs are not paired together and do not communicate with each other directly.
– The Audio Panel integrates navigation/communication radio (NAV/COM) digital audio, intercom,
DISPLAY BACKUP
(2) – The Integrated Avionics Units (IAU) function as the main communications hub, linking all LRUs
button; see Section 1.5, System Operation) and communicates
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
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SYSTEM OVERVIEW
GDC 74
(OAT) sensor. The ADC provides pressure altitude, airspeed, vertical speed, and OAT information to the
G1000 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
information 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 1.5, System Operation.
– The solid-state Transponder provides Modes A, C, and S capability and communicates with both IAUs
(2) – The Attitude and Heading Reference System (AHRS) provides aircraft attitude and heading
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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.
•
GDL 69A
PFD Inset Map, as well as digital audio entertainment. The Data Link Receiver communicates with the MFD
via an HSDB connection. A subscription to XM Satellite Radio Service is required to enable Data Link Receiver
capability.
– The Magnetometer measures local magnetic field and sends data to the AHRS for processing to
– The Data Link Satellite Radio Receiver provides real-time weather information to MFD maps and the
•
GSA 81
units interface with each IAU.
The GSM 85 servo mounts are responsible for transferring the output torque of the servo actuators to the
mechanical flight-control surface linkages.
and
GSM 85
– The GSA 81 servos are used for automatic control of pitch, pitch trim, and roll. These
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SYSTEM OVERVIEW
190-00592-02 Rev. A
Figure 1-1 Basic G1000 System Block Diagram
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
1-5
SYSTEM OVERVIEW
�
Figure 1-2 G1000 With Optional/Additional Interfaces
NOTE:
For information on 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.
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SYSTEM OVERVIEW
1.3 SECURE DIGITAL (SD) CARDS
NOTE:
Ensure the G1000 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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Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
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SYSTEM OVERVIEW
1.4 SYSTEM POWER-UP
NOTE:
See the Aircraft Flight Manual (AFM) for specific procedures concerning avionics power application
and emergency power supply operation.
NOTE:
The G1000 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 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
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
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.
Pressing the
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.
ENT Key (or right-most softkey) acknowledges this information, and the Navigation Map Page is
Figure 1-4 PFD Initialization Figure 1-5 MFD Power-Up Splash Screen
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SYSTEM OVERVIEW
1.5 SYSTEM OPERATION
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. Normal and reversionary G1000 display operation, as
well as the various AHRS modes and G1000 System Annunciations are discussed here.
NORMAL DISPLAY OPERATION
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.
Figure 1-6 G1000 Normal Operation
REVERSIONARY DISPLAY OPERATION
NOTE:
In the event of a display failure, the G1000 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.
The G1000 System alerts the pilot when backup paths are utilized by the LRUs. Refer to Appendix A
for further information regarding system-specific alerts.
NOTE:
In normal operating mode, backlighting can only be adjusted from the PFD. In Reversionary Mode, it
can be adjusted from the remaining display.
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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
DISPLAY BACKUP
button. Pressing this button again deactivates Reversionary Mode.
NAV1 and COM1 (provided by the
failed PFD) are flagged as invalid.
Pressing the
activates/deactivates Reversionary Mode.
DISPLAY BACKUP
Button also
Figure 1-7 G1000 Reversionary Mode (Failed PFD)
G1000 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). For a detailed description of all
annunciations and alerts, refer to Appendix A. Refer to the Aircraft Flight Manual (AFM) for additional
information regarding pilot responses to these annunciations.
Upon G1000 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 G1000 should
be serviced by a Garmin-authorized repair facility.
GIA 63
GIA 63
GRS 77 or GMU 44
GEA 71
or
GIA 63
GDC 74
Figure 1-8 G1000 System Failure Annunciations
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
GDC 74
GIA 63
GTX 33 or GIA 63
GIA 63
190-00592-02 Rev. A1-10
AHRS OPERATION
Attitude/Heading Invalid
AHRS
no-GPS
Mode
AHRS Normal
Operation
AHRS no-
Mag Mode
AHRS no-Mag/
no-Air Mode
Heading Invalid
Airspeed Data
Magnetometer
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 G1000 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 (refer
to Appendix A for specific AHRS alert information). 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).
GPS INPUT FAILURE
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.
MAGNETOMETER FAILURE
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’.
AIR DATA INPUT FAILURE
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.
Figure 1-9 AHRS Operation
190-00592-02 Rev. A
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
1-11
SYSTEM OVERVIEW
GPS RECEIVER OPERATION
Each GIA 63 Integrated Avionics Unit (IAU) contains a GPS receiver. 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 1.7 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).
Selecting the GPS receiver for which data is displayed:
1) Use the FMS Knob to select the AUX - GPS Status Page.
2) To change the selected GPS receiver:
a) Press the desired
GPS
Softkey.
OR:
a) Press the MENU Key.
b) Use the FMS Knob to highlight the receiver which is not selected and press the ENT Key.
Satellite Constellation
Diagram
Satellite Signal
Information Status
GPS Receiver
Status
RAIM
Availability
Prediction
Satellite Signal
Strength Bars
Figure 1-10 GPS Status Page
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
190-00592-02 Rev. A1-12
SYSTEM OVERVIEW
The GPS Status Page provides the following information:
• Satellite constellation diagram
Satellites currently in view are shown at their respective positions on a sky view diagram. The sky view is
always in a north-up orientation, 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.
• Satellite signal information status
The accuracy of the aircraft’s GPS fix is calculated using Estimated Position Uncertainty (EPU),
of Precision (DOP), and horizontal and vertical figures of merit (HFOM and VFOM). EPU is the radius of a
circle centered on an estimated horizontal position in which actual position has 95% probability of laying.
EPU is a statistical error indication and not an actual error measurement.
DOP 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. HFOM and VFOM,
measures of horizontal and vertical position uncertainty, are the current 95% confidence horizontal and
vertical accuracy values reported by the GPS receiver.
The current calculated GPS position, time, altitude, ground speed, and track for the aircraft are displayed
below the satellite signal accuracy measurements.
• 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.
When the receiver is in the process of acquiring a 3D navigational GPS solution, 2D NAV is indicated as the
solution since GPS altitude cannot be computed using the acquired satellite signal data. When differential
GPS (DGPS) signals are available, the solution status is indicated as 2D DIFF NAV or 3D DIFF NAV.
Dilution
• 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.
Because of the tighter protection limit on approaches, there may be times when RAIM is not available. The
G1000 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” and “RAIM not available from FAF to MAP”. If RAIM is not available
when crossing the FAF, the missed approach procedure must be flown.
190-00592-02 Rev. A
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
1-13
SYSTEM OVERVIEW
Predicting RAIM availability:
1) Select the GPS Status Page.
2) Press the
3) Turn the small FMS Knob to display the Waypoint Information Window.
4) Enter the desired waypoint:
a) Use the FMS Knob to enter the desired waypoint by identifier, facility, or city name and press the ENT Key. Refer
FMS
Knob
. The ‘WAYPOINT’ field is highlighted.
to Section 1.7 for instructions on entering alphanumeric data into the G1000.
OR:
a) Use the large FMS Knob to scroll to the Most Recent Waypoints List.
b) Use the small FMS Knob to highlight the desired waypoint in the list and press the ENT Key. The G1000
automatically fills in the identifier, facility, and city fields with the information for the selected waypoint.
c) Press the ENT Key to accept the waypoint 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) Use the FMS Knob to enter an arrival time and press the ENT Key.
6) Use the FMS Knob to 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
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
• GPS Satellite Signal Strengths
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) below each bar. The progress of
satellite acquisition is shown in three stages, as 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
- 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)
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).
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
190-00592-02 Rev. A1-14
SYSTEM OVERVIEW
1.6 G1000 CONTROLS
The G1000 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 and Audio
Panel. PFD and MFD controls and softkeys are discussed in this section. See the Audio Panel and CNS Section
for more information about Audio Panel and NAV/COM controls. AFCS controls (on the bezel of the MFD) are
described in the AFCS section.
PFD/MFD CONTROLS
18
1
2
3
4
Figure 1-11 PFD/MFD Controls
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
5
Joystick
190-00592-02 Rev. A
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 Horizontal Situation
Indicator (HSI) and synchronize the Selected Heading to the and current heading
Turn to change map range
Press to activate Map Pointer and move in desired direction to pan map
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
1-15
SYSTEM OVERVIEW
6
CRS/BARO Knob
7
COM Knob
8
COM Frequency
Transfer Key
(EMERG)
9
COM VOL/SQ Knob
10
Direct-to Key ( )
11
FPL Key
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 two 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
12
CLR Key
(DFLT MAP)
13
MENU Key
14
PROC Key
15
ENT Key
16
FMS Knob
(Flight Management
System Knob)
17
Softkey Selection
Keys
18
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 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)
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
190-00592-02 Rev. A1-16
SYSTEM OVERVIEW
INSET
XPDR
IDENT
TMR/REF
NRST
ALERTS
OBS
PFD
CDI
ADF/DME
(optional)
Press the CDI Softkey to cycle through
navigation sources:
- GPS
- NAV1 (VOR/LOC)
- NAV2 (VOR/LOC)
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 1-12 Dual Concentric Knob
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.
In the following descriptions, top level softkeys are denoted with bullets.
Softkey
On
Bezel-Mounted
Softkeys (Press)
Figure 1-13 Softkeys (Second-Level PFD Configuration)
Softkey Selection
Box (Light Blue)
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
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
BACK Softkey which can be selected to return to the
Softkey Names
(Displayed)
190-00592-02 Rev. A
Figure 1-14 Top-level PFD Softkeys
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
1-17
SYSTEM OVERVIEW
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
XPDR
IDENT
TMR/REF
NRST
ALERTS
OBS
PFD
CDI
ADF/DME
(optional)
Press the CDI Softkey to cycle through
navigation sources:
- GPS
- NAV1 (VOR/LOC)
- NAV2 (VOR/LOC)
• 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)
optional)
• PFD
METRIC
DFLTS
DME
BRG1
360 HSI
ARC HSI
Figure 1-15 INSET Softkeys
Displays second-level softkeys for additional PFD configuration
Displays Selected and current altitudes additionally in meters and changes barometric
setting to hectopascals (hPa) from inches of mercury (in Hg)
Resets PFD to default settings, including changing units to standard
Displays/removes DME Information Window (
optional)
Cycles the Bearing 1 Information Window through:
NAV1: Waypoint frequency/identifier and DME information
GPS: Waypoint identifier and GPS distance information
ADF: Waypoint frequency
Off: Removes window
Displays the HSI as a 360° compass rose
Displays the HSI as a 140° viewable arc (Bearing Information Windows unavailable)
190-00592-02 Rev. A1-18
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
SYSTEM OVERVIEW
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
XPDR
IDENT
TMR/REF
NRST
ALERTS
OBS
PFD
CDI
ADF/DME
(optional)
Press the CDI Softkey to cycle through
navigation sources:
- GPS
- NAV1 (VOR/LOC)
- NAV2 (VOR/LOC)
ARC HSI
STD BARO
BACK
ALERTS
METRIC
DFLTS
360
HSI
PFD
BRG
1
BRG
2
DME
(optional)
Press the BRG1/BRG2 softkeys to display/
remove the Bearing Information windows
and cycle through bearing sources:
- NAV1/NAV2
- GPS
- ADF
Press the STD BARO or BACK Softkey
to return to the top-level softkeys.
BRG2
Cycles the Bearing 2 Information Window through:
NAV2: Waypoint frequency/identifier and DME information
GPS: Waypoint identifier and GPS distance information
ADF: Waypoint frequency
Off: Removes window
STD BARO Sets barometric pressure to 29.92 in Hg (1013 hPa if METRIC Softkey is selected)
• OBS
• CDI
Selects OBS Mode on the CDI when navigating by GPS (only available with active leg)
Cycles CDI through GPS, NAV1 (VOR/LOC), and NAV2 (VOR/LOC) navigation sources
• ADF/DME Displays/removes ADF/DME Radio Tuning Window (optional; may appear as ADF, DME, or
ADF/DME depending on installation)
• XPDR
• IDENT
• TMR/REF
• NRST
• ALERTS
STBY
ON
ALT
VFR
CODE
0 — 7
BKSP
Figure 1-16 PFD Configuration Softkeys
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)
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
190-00592-02 Rev. A
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
1-19
SYSTEM OVERVIEW
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
XPDR
IDENT
TMR/REF
NRST
ALERTS
OBS
PFD
CDI
ADF/DME
(optional)
Press the CDI Softkey to cycle through
navigation sources:
- GPS
- NAV1 (VOR/LOC)
- NAV2 (VOR/LOC)
ARC HSI
STD BARO
BACK
ALERTS
METRIC
DFLTS
360
HSI
PFD
BRG
1
BRG
2
DME
(optional)
Press the BRG1/BRG2 softkeys to display/
remove the Bearing Information windows
and cycle through bearing sources:
- NAV1/NAV2
- GPS
- ADF
Press the STD BARO or BACK Softkey
to return to the top-level softkeys.
Press the BACK Softkey to return
to the top-level softkeys.
Press the IDENT or BACK Softkey
to return to the top-level softkeys.
XPDR
STBY
ON
ALT
VFR
IDENT
BACK
ALERTS
CODE
IDENT
BACK
ALERTS
0
1
2
3
4
5
6
7
BKSP
MAP
ENGINE
CHKLIST
CHKLIST
DCLTR
DCLTR-2
DCLTR-3
DCLTR-1
MFD SOFTKEYS
Figure 1-17 XPDR Softkeys
MFD softkeys vary depending on the page selected. EIS and Navigation Map Page (default MFD page)
softkeys are described here.
• ENGINE
Displays second-level engine softkeys (Figure 1-19; see the EIS Section for more
Figure 1-18 Navigation Map Page Softkeys
information)
LEAN
SYSTEM
• MAP
TRAFFIC
TOPO
Displays the EIS Lean Display (softkeys for engine leaning assist are shown when selected)
Displays the EIS System Display (softkeys for fuel calculations are shown when selected)
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
TERRAIN
NEXRAD
XM LTNG
BACK
Displays/removes terrain information on Navigation Map Page
Displays/removes NEXRAD weather and coverage information on Navigation Map Page
(optional)
Displays/removes XM lightning information on Navigation Map Page (optional)
Returns to top-level softkeys
Garmin G1000 Pilot’s Guide for the Diamond DA40/40F
190-00592-02 Rev. A1-20
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