Garmin DA40, DA40F User Manual

5 (2)
Garmin DA40, DA40F User Manual

G1000® Integrated Flight Deck

Pilot’s Guide

System Software 0321.20 or later

SYSTEM OVERVIEW

FLIGHT INSTRUMENTS

EIS

AUDIO PANEL & CNS

FLIGHT MANAGEMENT

HAZARD AVOIDANCE

AFCS

ADDITIONAL FEATURES

APPENDICES

INDEX

Copyright © 2006-2009 Garmin Ltd. or its subsidiaries. All rights reserved.

This manual reflects the operation of System Software version 0321.20 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.

Tel: 503/391.3411

Fax: 503/364.2138

Garmin (Europe) Ltd., Liberty House, Bulls Copse Road, Hounsdown Business Park, Southampton, SO40 9RB, U.K

Tel: 44/0870.8501241

Fax: 44/0870.8501251

Garmin Corporation, No. 68, Jangshu 2nd Road, Shijr, Taipei County, Taiwan

Tel: 886/02.2642.9199

Fax: 886/02.2642.9099

Website Address: www.garmin.com

Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express written permission of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed for personal use, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.

Garmin® 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 2009

Printed in the U.S.A.

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

190-00592-06 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.

190-00592-06 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: For safety reasons, G1000 operational procedures must be learned on the ground.

WARNING: 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.

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

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

iii

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.

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

190-00592-06 Rev. A

Revision Information

Record of Revisions

Part Number

Revision

Date

Page Range

Description

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

 

 

 

 

GDL 69A crew muting information added

190-00592-03

A

4/20/07

i – I-6

EIS updated

 

 

 

 

Airways information added

 

 

 

 

WAAS information added

 

 

 

 

VNV information added

 

 

 

 

Charts information added

 

 

 

 

Stormscope information added

 

 

 

 

TAS600 information added

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

190-00592-06

A

03/25/09

i – I-6

Updated to GDU Software 9.14

190-00592-06 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............................................

2

1.2

Secure Digital (SD) Cards........................................

7

1.3

System Power-up.....................................................

8

1.4

System Operation....................................................

9

 

Display Operation..........................................................

9

 

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

10

 

System Status.............................................................

11

 

AHRS Operation..........................................................

13

 

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

14

1.5

G1000 Controls......................................................

18

 

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

18

 

Softkey Function.........................................................

20

1.6

Accessing G1000 Functionality............................

27

 

Menus........................................................................

27

 

Data Entry..................................................................

27

 

Page Groups...............................................................

29

 

System Settings...........................................................

33

 

Timers........................................................................

38

1.7

Display Backlighting..............................................

41

 

Section 2 Flight Instruments

 

2.1

Flight Instruments..................................................

46

 

Airspeed Indicator.......................................................

46

 

Attitude Indicator........................................................

48

 

Altimeter....................................................................

49

 

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

51

 

Vertical Deviation........................................................

52

 

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

53

 

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

58

2.2

Supplemental Flight Data.....................................

65

 

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

65

 

Wind Data..................................................................

67

 

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

68

2.3

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

69

 

System Alerting...........................................................

69

 

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

70

 

Traffic Annunciation.....................................................

70

 

TAWS Annunciations...................................................

71

 

Altitude Alerting..........................................................

72

 

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

72

 

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

73

2.4

Abnormal Operations............................................

74

 

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

74

 

Unusual Attitudes........................................................

75

 

Section 3 Engine Indication System

 

3.1

EIS Display..............................................................

78

3.2

Engine Page............................................................

80

 

Fuel Calculations.........................................................

82

3.3

Leaning Assist Mode..............................................

83

3.4

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

84

 

Lean Display...............................................................

86

 

System Display............................................................

88

 

Section 4 audio panel and CNS

 

4.1

Overview.................................................................

91

 

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

92

 

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

94

4.2

COM Operation......................................................

96

 

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

96

 

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

97

 

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

98

 

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

99

 

Frequency Spacing.....................................................

103

 

Automatic Squelch....................................................

104

 

Volume....................................................................

104

4.3

NAV Operation.....................................................

105

 

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

105

 

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

106

 

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

108

 

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

113

 

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

114

4.4

GTX 33 Mode S Transponder..............................

118

 

Transponder Controls.................................................

118

 

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

119

 

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

122

 

IDENT Function.........................................................

123

4.5

Additional Audio Panel Functions......................

124

 

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

124

 

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

124

 

Speaker....................................................................

124

 

Intercom...................................................................

125

 

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

127

 

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

127

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

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Table of Contents

 

Entertainment Inputs.................................................

128

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

129

4.7

Abnormal Operation............................................

130

 

Stuck Microphone.....................................................

130

 

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

130

 

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

130

 

Reversionary Mode....................................................

130

 

Section 5 Flight Management

 

5.1

Introduction..........................................................

131

 

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

133

5.2

Using Map Displays.............................................

134

 

Map Orientation.......................................................

134

 

Map Range...............................................................

136

 

Map Panning............................................................

138

 

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

143

 

Topography..............................................................

144

 

Map Symbols............................................................

147

 

Airways....................................................................

153

 

Track Vector..............................................................

155

 

Wind Vector..............................................................

156

 

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

157

 

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

158

 

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

159

5.3

Waypoints.............................................................

160

 

Airports....................................................................

161

 

Intersections.............................................................

167

 

NDBs.......................................................................

169

 

VORs........................................................................

171

 

User Waypoints.........................................................

173

5.4

Airspaces...............................................................

179

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

183

5.6

Flight Planning.....................................................

189

 

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

190

 

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

195

 

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

197

 

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

200

 

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

207

 

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

209

 

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

212

 

Parallel Track.............................................................

214

 

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

217

 

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

218

 

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

219

 

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

221

5.7

Vertical Navigation..............................................

222

 

Altitude Constraints...................................................

224

5.8

Procedures............................................................

228

 

Departures................................................................

228

 

Arrivals ....................................................................

231

 

Approaches .............................................................

233

5.9

Trip Planning.........................................................

239

 

Trip Planning.............................................................

239

5.10

RAIM Prediction...................................................

243

5.11

Navigating a Flight Plan.....................................

247

5.12

Abnormal Operation............................................

275

 

Section 6 Hazard Avoidance

 

6.1

XM Satellite Weather..........................................

277

 

Activating Services....................................................

278

 

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

279

6.2

WX-500 Stormscope............................................

306

 

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

306

 

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

310

6.3

Terrain Proximity..................................................

311

 

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

311

 

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

314

6.4

Terrain-SVS............................................................

316

 

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

320

 

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

322

 

System Status...........................................................

325

6.5

Terrain Awareness & Warning System (TAWS)..

326

 

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

327

 

TAWS-B Page............................................................

329

 

TAWS Alerts..............................................................

331

 

System Status...........................................................

337

6.6

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

339

 

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

340

 

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

342

 

TIS Alerts..................................................................

343

 

System Status...........................................................

345

6.7

Traffic Advisory System.......................................

348

 

TAS Symbology.........................................................

348

 

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

349

 

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

351

 

TAS Alerts.................................................................

353

190-00592-06 Rev. A

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

vii

Table of Contents

 

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

353

 

System Status...........................................................

354

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) (Optional).........

404

 

SVS Operation...........................................................

405

 

SVS Features.............................................................

407

 

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

415

8.2

SafeTaxi.................................................................

417

 

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

420

8.3

ChartView.............................................................

423

 

ChartView Softkeys...................................................

423

 

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

424

 

Chart Options...........................................................

432

 

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

438

 

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

440

8.4

FliteCharts.............................................................

444

 

FliteCharts Softkeys...................................................

444

 

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

445

 

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

8.6

Scheduler..............................................................

467

8.7

Electronic Checklists............................................

469

8.8

Flight Data Logging.............................................

472

8.9

Abnormal Operation............................................

474

 

SVS Troubleshooting..................................................

474

 

Reversionary Mode....................................................

474

 

Unusual Attitudes......................................................

475

 

Appendices

 

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

479

 

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

496

 

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

496

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

499

Glossary..........................................................................

503

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

509

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

513

Map Symbols..................................................................

515

 

Index

 

Index

.................................................................................

I-1

viii

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

190-00592-06 Rev. A

System Overview

Section 1 System overview

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 Primary Flight Display (PFD)

GTX 33 Mode S Transponder

GDU 1040/1042/1044 Multi Function Display

GRS 77 Attitude and Heading Reference System

(MFD)

(AHRS)

GMA 1347 Audio Panel with Integrated Marker

GMU 44 Magnetometer

Beacon Receiver

GDL 69/69A Data Link Receiver

 

GIA 63/63W Integrated Avionics Units (IAU)

GSA 81 AFCS Servos

 

GDC 74A Air Data Computer (ADC)

GSM 85 Servo Mounts

 

GEA 71 Engine/Airframe Unit

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.

INDEX APPENDICES ADDITIONALFEATURES AFCS AVOIDANCEHAZARD MANAGEMENTFLIGHT PANELCNSAUDIO& EIS INSTRUMENTSFLIGHT OVERVIEWSYSTEM

190-00592-06 Rev. A

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

1

ADDITIONAL HAZARD FLIGHT AUDIO PANEL FLIGHT SYSTEM INDEX APPENDICES FEATURES AFCS AVOIDANCE MANAGEMENT & CNS EIS INSTRUMENTS OVERVIEW

System Overview

1.1 Line Replaceable Units

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 connection to an IAU. The three GDU models are distinguished by three individual configurations of bezel controls and are made available to accommodate a variety optional system installations.

GMA 1347 – The Audio Panel integrates navigation/communication radio (NAV/COM) digital audio, intercom, and marker beacon controls, and is installed between the displays. This unit also provides manual control of display Reversionary Mode (red DISPLAY BACKUP button; see Section 1.4, System Operation) and communicates with both IAUs using an RS-232 digital interface.

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.

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

190-00592-06 Rev. A

System Overview

GDC 74A – The Air Data Computer (ADC) processes data from the pitot/static system and outside air temperature (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.

EIS FLIGHT SYSTEM INSTRUMENTS OVERVIEW

GEA 71 – The Engine Airframe Unit receives and processes signals from the engine and airframe sensors. This unit communicates with both IAUs using an RS-485 digital interface.

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.

ADDITIONAL AFCS HAZARD FLIGHT PANEL AUDIO FEATURES AVOIDANCE MANAGEMENT CNS &

INDEX APPENDICES

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

3

ADDITIONAL HAZARD FLIGHT AUDIO PANEL FLIGHT SYSTEM INDEX APPENDICES FEATURES AFCS AVOIDANCE MANAGEMENT & CNS EIS INSTRUMENTS OVERVIEW

System Overview

GMU 44 – The Magnetometer measures local magnetic field and sends data to the AHRS for processing to 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 – The Data Link Satellite Radio Receiver provides real-time weather information to MFD maps 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.

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.

The GSM 85 servo mounts are responsible for transferring the output torque of the servo actuators to the mechanical flight-control surface linkages.

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

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System Overview

 

High-Speed Data Bus (Ethernet)

 

GDU 1040 (PFD)

GMA 1347

GDU 1040/1042/1044 (MFD)

Audio Panel

 

Reversionary

Reversionary

 

 

Control

 

Control

 

GDC 74A

Air Data

Computer

No. 1 GIA 63/63W

OAT

No. 2 GIA 63/63W

Integrated Avionics Unit

Airspeed

Integrated Avionics Unit

Altitude

 

 

 

Vertical Speed

 

System Inegration Processors

 

System Integration Processors

I/O Processors

 

I/O Processors

VHF COM

GRS 77

VHF COM

VHF NAV/LOC

VHF NAV/LOC

GPS/WAAS

AHRS

GPS/WAAS

Glideslope

Glideslope

 

Flight Director (with GFC 700 option)

Attitude

 

GPS Output

GPS Output

Rate of Turn

 

 

 

Slip/Skid

 

GMU 44

Magnetometer

Heading

GTX 33

Transponder

GEA 71

Engine/Airframe

Unit

GSA 81

GSA 81

GSA 81

Pitch Servo

Roll Servo

Pitch Trim Servo

Autopilot Calculations

Autopilot Calculations

Autopilot Calculations

(optional)

(optional)

(optional)

Figure 1-1 G1000 System Block Diagram

NOTE: The GDU 1042 and GDU 1044 are equipped with additional bezel controls and are available for use in systems equipped with the Garmin GFC 700 Automatic Flight Control System.

INDEX APPENDICES ADDITIONALFEATURES AFCS AVOIDANCEHAZARD MANAGEMENTFLIGHT PANELCNSAUDIO& EIS INSTRUMENTSFLIGHT OVERVIEWSYSTEM

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HAZARD FLIGHT AUDIO PANEL FLIGHT SYSTEM AVOIDANCE MANAGEMENT & CNS EIS INSTRUMENTS OVERVIEW

System Overview

High-Speed Data Bus (Ethernet)

No. 2 GIA 63/63W

Integrated Avionics Unit

System Integration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS/WAAS

Glideslope

Becker

Honeywell

Avidyne

RA 3502-(1)

KN 63

TAS600-series

ADF Receiver

DME

Traffic Information

(optional)

(optional)

(optional)

GDL 69/69A

Data Link Receiver

Real-time Weather and Digital Audio Entertainment (subscription-based service)

L3

Honeywell

Stormscope

KAP 140

Lightning Strike and

Autopilot

Thunderstorm Detection

(optional)

(optional)

 

Figure 1-2 G1000 With Optional/Additional Interfaces

ADDITIONAL INDEX APPENDICES FEATURES AFCS

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

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

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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.

SD Card Slots

AFCS HAZARD FLIGHT PANEL AUDIO EIS FLIGHT SYSTEM AVOIDANCE MANAGEMENT CNS & INSTRUMENTS OVERVIEW

Figure 1-3 Display Bezel SD Card Slots

INDEX APPENDICES ADDITIONALFEATURES

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

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ADDITIONAL HAZARD FLIGHT AUDIO PANEL FLIGHT SYSTEM INDEX APPENDICES FEATURES AFCS AVOIDANCE MANAGEMENT & CNS EIS INSTRUMENTS OVERVIEW

System Overview

1.3 System Power-up

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 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

• Obstacle database name and version

• Copyright

• Terrain database name and version

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

Figure 1-4 PFD Initialization

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

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

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System Overview

1.4 System Operation

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.

Figure 1-6 G1000 Normal Operation

AFCS HAZARD FLIGHT PANEL AUDIO EIS FLIGHT SYSTEM AVOIDANCE MANAGEMENT CNS & INSTRUMENTS OVERVIEW

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.

INDEX APPENDICES ADDITIONALFEATURES

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ADDITIONAL HAZARD FLIGHT AUDIO PANEL FLIGHT SYSTEM INDEX APPENDICES FEATURES AFCS AVOIDANCE MANAGEMENT & CNS EIS INSTRUMENTS OVERVIEW

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) Flagged Invalid

DISPLAY BACKUP Button Manually Activates/

Deactivates Reversionary Mode on Both Displays

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). 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

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Mismatch in the

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Engine

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

PFD and MFD

Airframe Unit

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

GRS 77 AHRS

OR

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

OR GMU 44

GIA 63/63W

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Magnetometer

Integrated

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Avionics Unit

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

GIA 63/63W

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Integrated

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

GDC 74A

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Avionics Units

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Air Data

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Computer

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

GTX 33 Transponder

 

OR GIA 63/63W

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Integrated Avionics Units

 

 

 

 

 

Figure 1-8

G1000 System Failure Annunciations

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

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System Overview

System Status

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

Viewing LRU information:

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

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

a)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.

Figure 1-9 Example System Status Page

INDEX APPENDICES ADDITIONALFEATURES AFCS AVOIDANCEHAZARD MANAGEMENTFLIGHT PANELCNSAUDIO& EIS INSTRUMENTSFLIGHT OVERVIEWSYSTEM

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ADDITIONAL HAZARD FLIGHT AUDIO PANEL FLIGHT SYSTEM INDEX APPENDICES FEATURES AFCS AVOIDANCE MANAGEMENT & CNS EIS INSTRUMENTS OVERVIEW

System Overview

Pertinent information on all system databases is also displayed on this page. Refer to the Appendices and Additional Features sections for more information about databases.

Viewing database information:

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

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

a)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.

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

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System Overview

AHRS Operation

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.

FLIGHT SYSTEM INSTRUMENTS OVERVIEW

GPS Data

 

availab

 

 

unavailab

 

Magnetometer Data

 

 

Magnetometer Data

 

availab

 

 

 

 

unavailab

 

 

 

 

 

Air Data

 

 

 

 

availab

 

 

 

unavailab

 

 

 

 

AHRS noAHRS no-Mag/

AHRS Normal

Mag Mode

 

no-Air Mode

Operation

 

 

 

Heading Invalid

 

 

 

 

 

 

 

 

availab

 

unavailab

 

 

Air Data

 

 

 

 

 

availab

 

 

una

 

 

 

 

 

v

 

 

 

 

 

 

ailab

 

 

 

 

 

 

le

 

 

AHRS

 

 

 

no-GPS

Attitude/Heading Invalid

Mode

Figure 1-10 AHRS Operation

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.

INDEX APPENDICES ADDITIONAL AFCS HAZARD FLIGHT PANEL AUDIO EIS FEATURES AVOIDANCE MANAGEMENT CNS &

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ADDITIONAL HAZARD FLIGHT AUDIO PANEL FLIGHT SYSTEM INDEX APPENDICES FEATURES AFCS AVOIDANCE MANAGEMENT & CNS EIS INSTRUMENTS OVERVIEW

System Overview

GPS Receiver Operation

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

Viewing GPS receiver status information:

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

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

3)To change the selected GPS receiver: 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.

 

 

 

 

 

GPS Receiver

Satellite Constellation

Satellite Signal

Diagram

 

Information

Status

 

 

 

 

 

 

 

 

 

 

 

 

 

 

RAIM

Availability

Prediction

Satellite

Signal

Strength

Bars

Figure 1-11 GPS Status Page

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

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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 or MSAS (used only in Japan) coverage area, it may be desirable to disable WAAS or MSAS (although it is not recommended). When disabled, the SBAS field in the GPS Status box indicates DISABLED. There may be a small delay for the GPS Status box to be updated upon WAAS and MSAS enabling/disabling.

Disabling WAAS or MSAS

1)Select the GPS Status Page.

2)If necessary, press the SBAS Softkey.

3)Press the FMS Knob, and turn the large FMS Knob to hightlight ‘MSAS’ or ‘WAAS’.

4)Press the ENT Key to uncheck the box.

5)Press the FMS Knob to remove the cursor.

Figure 1-12 Enable/Disable WAAS

INDEX APPENDICES ADDITIONALFEATURES AFCS AVOIDANCEHAZARD MANAGEMENTFLIGHT PANELCNSAUDIO& EIS INSTRUMENTSFLIGHT OVERVIEWSYSTEM

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ADDITIONAL HAZARD FLIGHT AUDIO PANEL FLIGHT SYSTEM INDEX APPENDICES FEATURES AFCS AVOIDANCE MANAGEMENT & CNS EIS INSTRUMENTS OVERVIEW

System Overview

RAIM Prediction

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

The RAIM prediction function also indicates whether RAIM is available at a specified date and time. RAIM computations predict satellite coverage within ±15 min of the specified arrival date and time. In 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.

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

‘COMPUTINGAVAILABILITY’—RAIM calculation in progress

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

‘RAIM NOTAVAILABLE’—RAIM is predicted to be unavailable for the specified waypoint, time, and date

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

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System Overview

Satellite Information

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

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

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

Hollow signal strength bar—Receiver has found the satellite and is collecting data. Each satellite has a 30- second data transmission that must be collected (signal strength bar is hollow) before the satellite may be used for navigation (signal strength bar becomes solid).

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

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

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

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

INDEX APPENDICES ADDITIONALFEATURES AFCS AVOIDANCEHAZARD MANAGEMENTFLIGHT PANELCNSAUDIO& EIS INSTRUMENTSFLIGHT OVERVIEWSYSTEM

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ADDITIONAL HAZARD FLIGHT AUDIO PANEL FLIGHT SYSTEM INDEX APPENDICES FEATURES AFCS AVOIDANCE MANAGEMENT & CNS EIS INSTRUMENTS OVERVIEW

System Overview

1.5 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

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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

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

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