Garmin G1000 Integrated Flight Deck Pilot’s Guide

®

Integrated Flight Deck

G1000

Pilot’s Guide

Diamond DA40/40F

SYSTEM OVERVIEW

FLIGHT INSTRUMENTS

EIS

AUDIO PANEL & CNS

FLIGHT MANAGEMENT

HAZARD AVOIDANCE

AFCS

ADDITIONAL FEATURES

APPENDICES

INDEX

Copyright © 2006-2008 Garmin Ltd. or its subsidiaries. All rights reserved.

This manual reflects the operation of System Software version 0321.18 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: [phone] Fax: [phone]

Garmin AT, Inc., 2345 Turner Road SE, Salem, OR 97302, U.S.A.
Tel: [phone] Fax: [phone]

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Tel: [phone] Fax: [phone]

Garmin Corporation, No. 68, Jangshu 2nd Road, Shijr, Taipei County, Taiwan
Tel: [phone] Fax: [phone]

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® and G1000® are registered trademarks of Garmin Ltd. or its subsidiaries. FliteCharts®, and SafeTaxi® are trademarks 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.; XM® is a registered trademark of XM Satellite Radio, Inc.; and
Stormscope® is a registered trademark of L-3 Communications.

March 2008 Printed in the U.S.A.

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

190-00592-05 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.

190-00592-05 Rev. A

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

i

WARNINGS, CAUTIONS, AND NOTES

WARNING:

To reduce the risk of unsafe operation, carefully review and understand all aspects of the
G1000 Pilot’s Guide documentation. 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.

WARNING:

The Garmin G1000 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:

WARNING:

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.

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 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 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:

Do not use outdated database information. Databases used in the G1000 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.

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

190-00592-05 Rev. Aii

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 G1000 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:

Use of the Stormscope is not intended for hazardous weather penetration (thunderstorm
penetration). Stormscope information, as displayed on the G1000 MFD, is to be used only for weather
avoidance, not penetration.

WARNING

:

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 Aeronautical Information
Manual (AIM) recommend avoiding “by at least 20 miles any thunderstorm identifi ed as severe or giving
an intense radar echo.”

WARNING:

Because of anomalies in the earth’s magnetic field, operating the G1000 within the following
areas could result in loss of reliable attitude and heading indications. North of 70° North latitude and south
of 70° South latitude. An area north of 65° North latitude between longitude 75º West and 120º West. An
area south of 55° South latitude between longitude 120º East and 165º East.

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 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.

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WARNINGS, CAUTIONS, AND NOTES

NOTE:

When using Stormscope, there are several atmospheric phenomena in addition to nearby thunderstorms
that can cause isolated discharge points in the strike display mode. However, clusters of two or more
discharge points in the strike display mode do indicate thunderstorm activity if these points reappear after
the screen has been cleared.

NOTE:

All visual depictions contained within this document, including screen images of the G1000 panel
and displays, are for example only, are subject to change, and may not reflect the most current G1000
System. Depictions of equipment may differ slightly from the actual equipment.

NOTE:

The GDU 1040/1042/1044 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.

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.

NOTE: Use of polarized eyewear may cause the flight displays to appear dim or blank.

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

190-00592-05 Rev. Aiv

Record of Revisions

REVISION INFORMATION

Part Number

190-00592-00 A 11/10/05 i – I-6 Optional fuel pressure gauge information added
190-00592-01 A 6/16/06 i – I-4 GFC 700 information added
190-00592-02 A 7/20/06 i – I-4 TAWS information added

190-00592-03 A 4/20/07 i – I-6 EIS updated

190-00592-04 A 12/04/07 i – I-6 KAP 140 Autopilot annunciations added
190-00592-05 A 03/31/08 i – I-6 Synthetic Vision System information added

Revision Date Page Range Description

GDL 69A crew muting information added

Airways information added
WAAS information added
VNV information added
Charts information added
Stormscope information added
TAS600 information added

190-00592-05 Rev. A

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

v

TABLE OF CONTENTS

SECTION 1 SYSTEM OVERVIEW

1.1 Line Replaceable Units ......................................... 10

1.2 Secure Digital (SD) Cards ..................................... 15

1.3 System Power-up ................................................... 16

1.4 System Operation .................................................. 17

Display Operation ....................................................... 17

G1000 System Annunciations ...................................... 18

System Status ............................................................. 19

AHRS Operation .........................................................21

GPS Receiver Operation ..............................................22

1.5 G1000

Controls ...................................................... 26

PFD/MFD Controls ...................................................... 26

Softkey Function ......................................................... 28

1.6 Accessing G1000 Functionality ........................... 35

Menus ....................................................................... 35

Data Entry ................................................................. 35

Page Groups .............................................................. 37

System Settings .......................................................... 41

Timers ....................................................................... 46

1.7 Display Backlighting ............................................. 49

SECTION 2 FLIGHT INSTRUMENTS

2.1 Flight Instruments ................................................. 54

Airspeed Indicator ......................................................54

Attitude Indicator ....................................................... 56

Altimeter ................................................................... 57

Vertical Speed Indicator (VSI) ....................................... 59

Vertical Deviation ....................................................... 60

Horizontal Situation Indicator (HSI) ..............................61

Course Deviation Indicator (CDI) .................................. 66

2.2 Supplemental Flight Data ....................................73

Outside Air Temperature ..............................................73

Wind Data .................................................................75

Vertical Navigation (VNV) Indications ...........................76

2.3 PFD Annunciations and Alerting Functions ........

System Alerting .......................................................... 77

Marker Beacon Annunciations ..................................... 78

Traffic Annunciation ....................................................78

TAWS Annunciations ................................................... 79

Altitude Alerting .........................................................80

Low Altitude Annunciation .......................................... 80

Minimum Descent Altitude/Decision Height Alerting ...... 81

77

2.4 Abnormal Operations ...........................................82

Abnormal GPS Conditions ...........................................82

Unusual Attitudes .......................................................83

SECTION 3 ENGINE INDICATION SYSTEM

3.1 EIS Display .............................................................. 86

3.2 Engine Page ........................................................... 88

Fuel Calculations ........................................................ 90

3.3 Leaning Assist Mode .............................................91

3.4 EIS Display in Reversionary Mode ....................... 92

Lean Display .............................................................. 94

System Display ........................................................... 96

SECTION 4 AUDIO PANEL AND CNS

4.1 Overview ................................................................ 99

MFD/PFD Controls and Frequency Display ................... 100

Audio Panel Controls ................................................ 102

4.2 COM Operation .................................................... 104

COM Transceiver Selection and Activation ................... 104

COM Transceiver Manual Tuning ................................ 105

Quick-Tuning and Activating 121.500 MHz .................. 106

Auto-Tuning the COM Frequency ................................ 107

Frequency Spacing ....................................................111

Automatic Squelch .................................................... 112

Volume .................................................................... 112

4.3 NAV Operation .....................................................113

NAV Radio Selection and Activation ........................... 113

NAV Receiver Manual Tuning .....................................114

Auto-Tuning a NAV Frequency from the MFD .............. 116

Marker Beacon Receiver ............................................ 121

ADF/DME Tuning ...................................................... 122

4.4 GTX 33 Mode S Transponder .............................. 126

Transponder Controls ................................................ 126

Transponder Mode Selection ...................................... 127

Entering a Transponder Code ..................................... 130

IDENT Function ........................................................131

4.5 Additional Audio Panel Functions .....................132

Power-Up ................................................................. 132

Mono/Stereo Headsets .............................................. 132

Speaker ................................................................... 132

Intercom .................................................................. 133

Passenger Address (PA) System .................................. 135

Clearance Recorder and Player ................................... 135

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190-00592-05 Rev. Avi

TABLE OF CONTENTS

Entertainment Inputs ................................................ 136

4.6 Audio Panel Preflight Procedure ....................... 137

4.7 Abnormal Operation ........................................... 138

Stuck Microphone ..................................................... 138

COM Tuning Failure ................................................... 138

Audio Panel Fail-Safe Operation ................................. 138

Reversionary Mode ................................................... 138

SECTION 5 FLIGHT MANAGEMENT

5.1 Introduction ......................................................... 139

Navigation Status Box ............................................... 141

5.2 Using Map Displays ............................................. 142

Map Orientation ....................................................... 142

Map Range .............................................................. 144

Map Panning ............................................................ 146

Measuring Bearing and Distance ................................ 151

Topography .............................................................. 152

Map Symbols ........................................................... 155

Airways ................................................................... 161

Track Vector .............................................................163

Wind Vector ............................................................. 164

Nav Range Ring ....................................................... 165

Fuel Range Ring ....................................................... 166

Field of View (SVS) .................................................... 167

5.3 Waypoints .............................................................168

Airports ................................................................... 169

Intersections ............................................................175

NDBs ....................................................................... 177

VORs ....................................................................... 179

User Waypoints ........................................................ 181

5.4 Airspaces ..............................................................

186

5.5 Direct-to-Navigation .......................................... 190

5.6 Flight Planning ..................................................... 197

Flight Plan Creation .................................................. 198

Adding Waypoints to an Existing Flight Plan ................ 201

Adding Airways to a Flight Plan .................................203

Adding Procedures to a Stored Flight Plan ..................206

Flight Plan Storage ...................................................213

Flight Plan Editing ....................................................215

Along Track Offsets ................................................... 218

Parallel Track ............................................................ 220

Activating a Flight Plan Leg ....................................... 223

Inverting a Flight Plan ............................................... 224

Flight Plan Views ...................................................... 225

Closest Point of FPL .................................................. 227

5.7 Vertical Navigation .............................................

Altitude Constraints .................................................. 230

228

5.8 Procedures ...........................................................234

Departures ............................................................... 234

Arrivals ................................................................... 237

Approaches ............................................................. 239

5.9 Trip Planning ........................................................

Trip Planning ............................................................ 245

245

5.10 RAIM Prediction .................................................. 249

5.11 Navigating a Flight Plan ..................................... 253

5.12 Abnormal Operation ........................................... 281

SECTION 6 HAZARD AVOIDANCE

6.1 XM Satellite Weather .......................................... 283

Activating Services .................................................... 284

Using XM Satellite Weather Products .......................... 285

6.2 WX-500

Setting Up Stormscope on the Navigation Map ...........308

Selecting the Stormscope Page .................................. 312

Stormscope ...........................................308

6.3 Terrain Proximity ................................................. 313

Displaying Terrain Proximity Data ............................... 314

Terrain Proximity Page ...............................................316

6.4 Terrain-SVS ........................................................... 318

TERRAIN-SVS Page ................................................... 322

TERRAIN-SVS Alerts .................................................. 324

System Status ........................................................... 326

6.5 Terrain Awareness & Warning System (TAWS) .328

Displaying TAWS Data ............................................... 329

TAWS Page .............................................................. 331

TAWS Alerts .............................................................333

System Status ........................................................... 339

6.6 Traffic Information Service (

Displaying TRAFFIC Data ........................................... 341

Traffic Map Page ....................................................... 343

TIS Alerts ................................................................. 344

System Status ........................................................... 346

TIS) ........................ 340

6.7 Traffic Advisory System ......................................349

TAS Symbology ......................................................... 349

Displaying Traffic Data .............................................. 350

Altitude Display ........................................................ 351

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TABLE OF CONTENTS

Traffic Map Page Display Range ................................. 352

TAS Alerts ................................................................354

TAS Voice Alerts ........................................................ 354

System Status ........................................................... 355

SECTION 7 AUTOMATIC FLIGHT CONTROL SYSTEM

7.1 AFCS Controls ...................................................... 358

7.2 Flight Director Operation ................................... 360

Activating the Flight Director ..................................... 360

AFCS Status Box ....................................................... 361

Command Bars ......................................................... 362

Flight Director Modes ................................................ 362

7.3 Vertical Modes ..................................................... 363

Pitch Hold Mode (PIT) ............................................... 364

Selected Altitude Capture Mode (ALTS) ....................... 365

Altitude Hold Mode (ALT) .......................................... 366

Vertical Speed Mode (VS) .......................................... 367

Flight Level Change Mode (FLC) ................................. 368

Vertical Navigation Modes (VPTH, ALTV) ..................... 370

Glidepath Mode (GP) (WAAS only) ............................. 375

Glideslope Mode (GS) ............................................... 377

Go Around Mode (GA) .............................................. 378

7.4 Lateral Modes ...................................................... 379

Roll Hold Mode (ROL) ...............................................380

Heading Select Mode (HDG) ...................................... 381

Navigation Modes (GPS, VOR, LOC, BC) ...................... 382

Approach Modes (GPS, VAPP, LOC) ............................. 384

7.5 Autopilot Operation ............................................ 386

Engaging the Autopilot ............................................. 386

Control Wheel Steering ............................................. 387

Disengaging the Autopilot ......................................... 387

7.6 Example Flight Plan ............................................388

Departure ................................................................389

Intercepting a VOR Radial .......................................... 391

Flying a Flight Plan/GPS Course ................................. 392

Descent ................................................................... 393

Approach ................................................................. 397

Go Around/Missed Approach ..................................... 399

7.7 AFCS Annunciations and Alerts ......................... 401

AFCS Status Alerts .................................................... 401

Overspeed Protection ................................................ 402

Annunciations for KAP 140 Autopilot System .............. 402

SECTION 8 ADDITIONAL FEATURES

8.1 Synthetic Vision System (SVS) ...........................404

SVS Operation .......................................................... 405

SVS Features ............................................................ 406

Field of View ............................................................ 411

Reversionary Mode ................................................... 412

Unusual Attitudes ..................................................... 413

8.2 SafeTaxi ................................................................ 414

SafeTaxi Cycle Number and Revision ..........................417

8.3 ChartView ............................................................. 420

ChartView Softkeys ................................................... 420

Terminal Procedures Charts .......................................421

Chart Options ........................................................... 431

Day/Night View ........................................................437

ChartView Cycle Number and Expiration Date ............. 439

8.4 FliteCharts ............................................................ 443

FliteCharts Softkeys .................................................. 443

Terminal Procedures Charts .......................................444

Chart Options ........................................................... 452

Day/Night View ........................................................456

FliteCharts Cycle Number and Expiration Date ............. 458

8.5 XM Radio Entertainment (Optional) ................. 462

Activating XM Satellite Radio Services ........................ 462

Using XM Radio .......................................................464

Automatic Audio Muting ........................................... 468

8.6 Scheduler .............................................................. 469

8.7 Electronic Checklists ........................................... 471

8.8 Abnormal Operation ........................................... 474

SVS Troubleshooting .................................................475

APPENDICES

Annunciations and Alerts ............................................. 477

SVS Terrain Alerts ...................................................... 494

SVS Terrain Status Annunciations ............................... 494

SD Card Use and Databases .........................................

497

Glossary .......................................................................... 501

Frequently Asked Questions ........................................ 507

General TIS Information ............................................... 511

Map Symbols ................................................................. 513

INDEX

Index ................................................................................ I-1

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

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SECTION 1 SYSTEM OVERVIEW

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

NOTE:

Refer to the Automatic Flight Control System (AFCS) Section for details on the GFC 700 AFCS.

The G1000 Integrated Flight Deck System presents flight instrumentation, position, navigation, communication,

and identification information using flat-panel color displays. The system is distributed across the following Line
Replaceable Units (LRUs):

•

GDU 1040

•

GDU 1040/1042/1044

(MFD)

•

GMA 1347

Beacon Receiver

•

GIA 63/63W

•

GDC 74A

•

GEA 71

Primary Flight Display (PFD)

Multi Function Display

Audio Panel with Integrated Marker

Integrated Avionics Units (IAU)

Air Data Computer (ADC)

Engine/Airframe Unit

•

GTX 33

•

GRS 77

Mode S Transponder

Attitude and Heading Reference System

(AHRS)

•

GMU 44

•

GDL 69/69A

•

GSA 81

•

GSM 85

Magnetometer

AFCS Servos

Servo Mounts

Data Link Receiver

Figure 1-1 shows interactions between the LRUs. Additional/optional equipment are shown in Figure 1-2.

The Diamond DA40/40F may 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.

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

190-00592-05 Rev. A

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

9

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

SYSTEM OVERVIEW

1.1 LINE REPLACEABLE UNITS

SYSTEM

OVERVIEW

• GDU 1040/1042/1044 (2) – A GDU 1040 is configured as the Primary Flight Display (PFD) and a GDU 1040,
1042 or 1044 (1042/1044 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

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

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.

GDU 1040

GDU 1042

GDU 1044

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

DISPLAY BACKUP

button; see Section 1.4, System Operation) and communicates

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

ADDITIONAL

APPENDICESINDEX

•

FEATURES

GIA 63/63W

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

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

190-00592-05 Rev. A10

SYSTEM OVERVIEW

GDC 74A

(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

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

•

GTX 33

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

through an RS-232 digital interface.

•

GRS 77

(2) – The Attitude and Heading Reference System (AHRS) provides aircraft attitude and heading
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 1.4, System Operation.

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

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Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

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SYSTEM OVERVIEW

•

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

•

EIS

& CNS

AUDIO PANEL

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 69/69A

and the PFD Inset Map. The GDL 69A model is also capable of providing 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

FLIGHT

•

MANAGEMENT

The GSM 85 servo mounts are responsible for transferring the output torque of the servo actuators to the

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

GSA 81

and

GSM 85

– The GSA 81 servos are used for automatic control of pitch, pitch trim, and roll. These

units interface with each IAU.

mechanical flight-control surface linkages.

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

190-00592-05 Rev. A12

GSA 81

Roll Servo

Autopilot Calculations

(optional)

GSA 81

Pitch Servo

Autopilot Calculations

(optional)

GSA 81

Pitch Trim Servo

Autopilot Calculations

(optional)

No. 1 GIA 63/63W

Integrated Avionics Unit

System Inegration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS/WAAS

Glideslope

Flight Director (with GFC 700 option)

No. 2 GIA 63/63W

Integrated Avionics Unit

System Integration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS/WAAS

Glideslope

GTX 33

Transponder

High-Speed Data Bus (Ethernet)

Reversionary

Control

GEA 71

Engine/Airframe

Unit

GDC 74A

Air Data

Computer

OAT

Airspeed

Altitude

Ve

rtical Speed

GRS 77

AHRS

Attitude

Rate of Turn

Slip/Skid

GMU 44

Magnetometer

Heading

GPS Output

GPS Output

Reversionary

Control

GMA 1347

Audio Panel

GDU 1040 (PFD)

GDU 1040/1044 (MFD)

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

Figure 1-1 G1000 System Block Diagram

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

NOTE:

190-00592-05 Rev. A

The GDU 1044 is available in systems using the Garmin GFC 700 Automatic Flight Control System.

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

13

SYSTEM OVERVIEW

High-Speed Data Bus (Ethernet)

No. 2 GIA 63/63W

Integrated A

vionics Unit

System Integration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS/WAAS

Glideslope

GDL 69/69A

Data Link Receiver

Real-time Weather and

Digital Audio Entertainment

(subscription-based service)

Avidyne

TAS600-series

Traffic Information

(optional)

L3

Stormscope

Lightning Strike and

Thunderstorm Detection

(optional)

Becker

RA 3502-(1)

ADF Receiver

(optional)

Honeywell

KN 63

DME

(optional)

Honeywell

KAP 140

Autopilot

(optional)

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 1-2 G1000 With Optional/Additional Interfaces

NOTE:

NOTE:

The GDU 1040 is available in systems using the Honeywell KAP 140 Autopilot.

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.

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

190-00592-05 Rev. A14

SYSTEM OVERVIEW

1.2 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 databases.

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, pushing the card in until the spring latch engages. The front of the card

should remain flush with the face of the display bezel.

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

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

SD Card Slots

Figure 1-3 Display Bezel SD Card Slots

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00592-05 Rev. A

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

15

SYSTEM OVERVIEW

1.3 SYSTEM POWER-UP

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

busses. The PFD, MFD, and supporting sub-systems include both power-on and continuous built-in test features

EIS

that exercise the processor, RAM, ROM, external inputs, and outputs to provide safe operation.

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.

& CNS

AUDIO PANEL

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.

FLIGHT

• System version

• Copyright

MANAGEMENT

• Land database name and version

NOTE:

See the Aircraft Flight Manual (AFM) for specific procedures concerning avionics power application

and emergency power supply operation.

NOTE:

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

The G1000 System is integrated with the aircraft electrical system and receives power directly from electrical

During system initialization, test annunciations are displayed, as shown in Figure 1-4. All system annunciations

On the PFD, the AHRS begins to initialize and displays “AHRS ALIGN: Keep Wings Level”. The AHRS should

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

• Obstacle database name and version

• Terrain database name and version

• Aviation database name, version, and effective dates

HAZARD

information has been reviewed for currency (to ensure that no databases have expired), the pilot is prompted to

AVOIDANCE

continue.

displayed upon pressing the key a second time. When the system has acquired a sufficient number of satellites to

AFCS

ADDITIONAL

APPENDICESINDEX

determine a position, the aircraft’s current position is shown on the Navigation Map Page.

FEATURES

Current database information includes valid operating dates, cycle number, and database type. When this

Pressing the

ENT Key (or right-most softkey) acknowledges this information, and the Navigation Map Page is

Figure 1-4 PFD Initialization Figure 1-5 Example (DA40) MFD Power-up Splash Screen

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

190-00592-05 Rev. A16

1.4 SYSTEM OPERATION

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

NOTE:

Refer to Appendix A for detailed descriptions of all alerts and annunciations. Refer to the Aircraft

Flight Manual (AFM) for additional information regarding pilot responses to these annunciations.

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 allows the units to share information, enabling true
system integration

DISPLAY OPERATION

NOTE:

In normal operating mode, backlighting can only be adjusted from the PFD. 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 Flight Management 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.

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

In the event of a display failure, the G1000 System automatically switches to reversionary (backup) mode. In
Reversionary Mode, all important flight information from the PFD is presented on the remaining display in the
same format as in normal operating mode, with the addition of the EIS. EIS operation while in Reversionary
Mode is discussed in the EIS Section. As when the PFD is operating normally, windows for flight planning,
nearest airports, and procedures are available. The Inset Map is moved to the right side of the display.

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.

190-00592-05 Rev. A

Figure 1-6 G1000 Normal Operation

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

17

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

SYSTEM OVERVIEW

If the system fails to detect a display problem, Reversionary Mode may be manually activated by pressing the

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

Audio Panel’s red

DISPLAY BACKUP

Button. Pressing this button again deactivates Reversionary Mode.

NAV1 and COM1 (provided by the

failed PFD) Flagged Invalid

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

DISPLAY BACKUP

Deactivates Reversionary Mode on Both Displays

Figure 1-7 G1000 Reversionary Mode (Failed PFD)

Button Manually Activates/

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). The G1000 System alerts the pilot
when backup paths are utilized by the LRUs. 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 63/63W Integrated Avionics Units

GDC 74A

Air Data

Computer

Database

GEA 71

Engine

Airframe Unit

OR

GIA 63/63W

Integrated

Avionics Unit

Mismatch in the

PFD and MFD

GRS 77 AHRS

OR GMU 44

Magnetometer

APPENDICESINDEX

GDC 74A

Air Data

Computer

GTX 33 Transponder OR GIA 63/63W

Integrated Avionics Units

Figure 1-8 G1000 System Failure Annunciations

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

GIA 63/63W

Integrated

Avionics Units

190-00592-05 Rev. A18

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,

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

a) Press 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.

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

190-00592-05 Rev. A

Figure 1-9 Example System Status Page

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

19

ADDITIONAL

FEATURES

APPENDICES INDEX

SYSTEM OVERVIEW

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

SYSTEM

OVERVIEW

Additional Features sections for more information about databases.

Viewing database information:

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

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

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

a) Press 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 G1000 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) Press the ANN TEST Softkey.

Or:

a) Press the MENU Key.

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

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

190-00592-05 Rev. A20

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

vailab

le

available

unavailable

unavailable

available

Air Data

Magnetometer Data

unavailable

available

GPS Data

Magnetometer Data

Air Data

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

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.

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

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).

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.

Figure 1-10 AHRS Operation

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00592-05 Rev. A

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

21

SYSTEM OVERVIEW

GPS RECEIVER OPERATION

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

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:

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

GPS Receiver

Status

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

RAIM

Availability

Prediction

Satellite

Signal

Strength

Bars

Figure 1-11 GPS Status Page

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

190-00592-05 Rev. A22

SYSTEM OVERVIEW

For WAAS-enabled systems, 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.

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

Disabling WAAS (for WAAS-enabled systems):

1) Select the GPS Status Page.

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

3) Press the

FMS

Knob

. ‘WAAS’ is highlighted.

4) Press the ENT Key to uncheck the box.

5) Press the FMS Knob to remove the cursor.

Figure 1-12 Enable/Disable WAAS

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00592-05 Rev. A

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

23

SYSTEM OVERVIEW

RAIM PREDICTION

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

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 G1000
systems with WAAS enabled, performing RAIM prediction is not necessary in most cases. However, if the
selected approach is outside the WAAS coverage area, 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
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”. 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) Press the RAIM Softkey.

2) Press the

FMS

Knob

. The ‘WAYPOINT’ field is highlighted.

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

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

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 G1000 Pilot’s Guide for the Diamond DA40/40F

190-00592-05 Rev. A24

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.

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

• 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.

• Green signal strength bar—Satellites that are actually being used in the position calculation.

• Blue signal strength bar—Satellite is locked on but not yet being used in the position calculation.

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

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

190-00592-05 Rev. A

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

APPENDICES INDEX

25

SYSTEM OVERVIEW

1.5 G1000 CONTROLS

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

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

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

18

1

2

3

4

5

17

6

7

9

8

10

11

12

16

13

14

15

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 1-13 PFD/MFD Controls

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

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

Large (Outer) Knob

Small (Inner) Knob

Figure 1-14 Dual Concentric Knob

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

190-00592-05 Rev. A26

1

NAV VOL/ID Knob

SYSTEM OVERVIEW

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

percentage)

OVERVIEW

SYSTEM

2

NAV Frequency
Transfer Key

3

NAV Knob

4

Heading Knob

5

Joystick

6

CRS/BARO Knob

7

COM Knob

8

COM Frequency
Transfer Key
(EMERG)

9

COM VOL/SQ Knob

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

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)

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

10

Direct-to Key ( )

11

FPL Key

12

CLR Key
(DFLT MAP)

13

MENU Key

14

PROC Key

15

ENT Key

190-00592-05 Rev. A

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

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

Garmin G1000 Pilot’s Guide for the Diamond DA40/40F

27

ADDITIONAL

FEATURES

APPENDICES INDEX