Garmin Beechcraft A36, Beechcraft G36 User Manual

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Page 1

Integrated Flight Deck

G1000

Pilot’s Guide

Beechcraft A36/G36

Page 2

SYSTEM OVERVIEW

FLIGHT INSTRUMENTS

EIS

AUDIO PANEL & CNS

FLIGHT MANAGEMENT

HAZARD AVOIDANCE

AFCS

ADDITIONAL FEATURES

APPENDICES

INDEX

Page 3

This manual reﬂects the operation of System Software version 0464.17 or later for the

0858.03 or later for the 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

Beechcraft A36/G36 (WAAS). Some differences in operation may be observed when comparing the information in

Beechcraft A36/G36, or System Software version

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

Garmin® is a registered trademark of Garmin Ltd. or its subsidiaries, and G1000® is a trademark of Garmin Ltd. or its subsidiaries. These trademarks may not be used without the express permission of Garmin.

Bendix/King® and Honeywell® are registered trademarks of Honeywell International, Inc.; Becker® is a registered trademark of Becker Flugfunkwerk GmbH; NavData® is a registered trademark of Jeppesen, Inc.; and XM® is a registered trademark of XM Satellite Radio, Inc.

April 2008 Printed in the U.S.A.

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B

Page 4

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.

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 5

WARNINGS, CAUTIONS, AND NOTES

WARNING:

Navigation and terrain separation must NOT be predicated upon the use of the terrain function. The G1000 Terrain Proximity feature is NOT intended to be used as a primary reference for terrain avoidance and does not relieve the pilot from the responsibility of being aware of surroundings during ﬂight. The Terrain Proximity feature is only to be used as an aid for terrain avoidance and is not certiﬁed for use in applications requiring a certiﬁed terrain awareness system. Terrain data is obtained from third party sources. Garmin is not able to independently verify the accuracy of the terrain data.

WARNING:

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

WARNING:

The 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:

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.

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. Pilots must maneuver the aircraft based only upon ATC guidance or positive visual acquisition of conﬂicting trafﬁc.

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:

GDL 69 Weather should not be used for hazardous weather penetration. Weather information

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

WARNING:

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

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. Bii

Page 6

WARNINGS, CAUTIONS, AND NOTES

WARNING:

The Garmin G1000, as installed in the Hawker Beechcraft A36/G36 aircraft, has a very high degree of functional integrity. However, the pilot must recognize that providing monitoring and/or selftest 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.

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:

To reduce the risk of unsafe operation, carefully review and understand all aspects of the G1000 Pilot’s Guide documentation and the G1000 Integrated Avionics System and GFC 700 AFCS in Beechcraft A36/G36 Airplane Flight Manual. Thoroughly practice basic operation prior to actual use. During ﬂight operations, carefully compare indications from the G1000 to all available navigation sources, including the information from other NAVAIDs, visual sightings, charts, etc. For safety purposes, always resolve any discrepancies before continuing navigation.

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 identiﬁed as severe or giving an intense radar echo.”

WARNING:

Lamp(s) inside this product may contain mercury (HG) and must be recycled or disposed of according to local, state, or federal laws. For more information, refer to our website at www.garmin.com/ aboutGarmin/environment/disposal.jsp.

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 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 Beechcraft A36/G36

iii

Page 7

WARNINGS, CAUTIONS, AND NOTES

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.

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 subject to change and may not reﬂect the most current G1000 system and aviation databases. Depictions of equipment may differ slightly from the actual equipment.

NOTE

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

NOTE

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 yards 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.

NOTE

This product, its packaging, and its components contain chemicals known to the State of California to cause cancer, birth defects, or reproductive harm. This notice is being provided in accordance with California’s Proposition 65. If you have any questions or would like additional information, please refer to our web site at www.garmin.com/prop65.

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. Biv

Page 8

Record of Revisions

REVISION INFORMATION

Part Number

190-00595-00 A 10/16/06 All Initial Release 190-00595-01 A

Revision Date Page Range Description

12/21/07

4/08/08

All All

Updated to GDU SW version 8.10, and added WAAS Change System Software version, update description of two

warning messages, and other minor corrections

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 9

TABLE OF CONTENTS

SECTION 1 SYSTEM OVERVIEW

1.1 System Description ................................................. 1

1.2 Line Replaceable Units (LRU) ................................. 2

1.3 G1000 Controls ........................................................ 6

PFD/MFD Controls ........................................................ 6

Additional AFCS Controls .............................................. 9

Audio Panel Controls .................................................. 10

1.4 Secure Digital Cards .............................................12

1.5 System Power-up ................................................... 12

1.6 System Operation .................................................. 14

Normal Operation ....................................................... 14

Reversionary Mode ..................................................... 14

AHRS Operation .........................................................15

G1000 System Annunciations ...................................... 17

Softkey Function ......................................................... 18

GPS Receiver Operation ..............................................23

1.7 Accessing G1000 Functionality ........................... 28

Menus ....................................................................... 28

MFD Page Groups ....................................................... 28

MFD System Pages .....................................................32

1.8 Display Backlighting ............................................. 46

SECTION 2 FLIGHT INSTRUMENTS

2.1 Flight Instruments ................................................. 50

Airspeed Indicator ......................................................50

Attitude Indicator ....................................................... 53

Altimeter ................................................................... 54

Vertical Speed Indicator (VSI) ....................................... 55

Vertical Deviation ....................................................... 56

Horizontal Situation Indicator (HSI) ..............................57

Course Deviation Indicator (CDI) .................................. 62

2.2 Supplemental Flight Data ....................................69

Temperature Displays ..................................................69

Wind Data .................................................................70

Vertical Navigation (VNV) Indications ...........................71

2.3 PFD Annunciations and Alerting Functions ........ 72

G1000 Alerting System ................................................ 72

Marker Beacon Annunciations ..................................... 73

Trafﬁc Annunciation ....................................................74

TAWS Annunciations (Optional) ................................... 74

Altitude Alerting .........................................................75

Low Altitude Annunciation (WAAS only) .......................75

Minimum Descent Altitude/Decision Height Alerting ...... 76

2.4 Abnormal Operations ...........................................77

Abnormal GPS Conditions ...........................................77

Unusual Attitudes .......................................................78

SECTION 3 ENGINE INDICATION SYSTEM

3.1 Engine Display ....................................................... 81

3.2 Lean Display ........................................................... 83

3.3 System Display ......................................................86

SECTION 4 AUDIO PANEL AND CNS

4.1 Overview ................................................................ 89

MFD/PFD Controls and Frequency Display ..................... 90

Audio Panel Controls .................................................. 92

4.2 COM Operation ...................................................... 94

COM Transceiver Selection and Activation ..................... 94

COM Transceiver Manual Tuning .................................. 95

Quick-Tuning and Activating 121.500 MHz .................... 96

Auto-Tuning the COM Frequency .................................. 97

Frequency Spacing .................................................... 101

Automatic Squelch .................................................... 102

Volume .................................................................... 102

4.3 NAV Operation ..................................................... 103

NAV Radio Selection and Activation ........................... 103

NAV Receiver Manual Tuning ..................................... 104

Auto-Tuning a NAV Frequency from the MFD .............. 106

Marker Beacon Receiver ............................................ 111

DME Tuning (Optional) .............................................. 112

4.4 GTX 33 Mode S Transponder .............................. 113

Transponder Controls ................................................ 113

Transponder Mode Selection ...................................... 114

Entering a Transponder Code ..................................... 117

IDENT Function ........................................................118

Flight ID Reporting ................................................... 119

4.5 Additional Audio Panel Functions .....................120

Power-Up ................................................................. 120

Mono/Stereo Headsets .............................................. 120

Speaker ................................................................... 120

Intercom .................................................................. 121

Passenger Address (PA) System .................................. 123

Clearance Recorder and Player ................................... 123

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. Bvi

Page 10

TABLE OF CONTENTS

Split COM ................................................................ 124

Entertainment Inputs ................................................ 125

4.6 Audio Panel Preﬂight Procedure ....................... 126

4.7 Abnormal Operation ........................................... 127

Stuck Microphone ..................................................... 127

COM Tuning Failure ................................................... 127

Audio Panel Fail-Safe Operation ................................. 127

Reversionary Mode ................................................... 127

SECTION 5 FLIGHT MANAGEMENT

5.1 Introduction ......................................................... 129

Navigation Status Box ............................................... 131

5.2 Using Map Displays ............................................. 132

Map Orientation ....................................................... 132

Map Range .............................................................. 134

Map Panning ............................................................ 136

Measuring Bearing and Distance ................................ 141

Topography .............................................................. 142

Map Symbols ........................................................... 145

Airways ................................................................... 151

Track Vector .............................................................153

Wind Vector ............................................................. 154

Nav Range Ring ....................................................... 155

Fuel Range Ring ....................................................... 156

5.3 Waypoints .............................................................157

Airports ................................................................... 158

Intersections ............................................................164

NDBs ....................................................................... 166

VORs ....................................................................... 168

User Waypoints ........................................................ 170

5.4 Airspaces .............................................................. 175

5.5 Direct-to-Navigation .......................................... 179

5.6 Flight Planning ..................................................... 185

Flight Plan Creation .................................................. 186

Adding Waypoints to an Existing Flight Plan ................ 189

Adding Airways to a Flight Plan .................................191

Adding Procedures to a Stored Flight Plan ..................194

Flight Plan Storage ...................................................201

Flight Plan Editing ....................................................203

Along Track Offsets ................................................... 206

Parallel Track ............................................................ 208

Activating a Flight Plan Leg ....................................... 211

Inverting a Flight Plan ............................................... 212

Flight Plan Views ...................................................... 213

Closest Point of FPL .................................................. 215

5.7 Vertical Navigation ............................................. 216

Altitude Constraints .................................................. 218

5.8 Procedures ...........................................................222

Departures ............................................................... 222

Arrivals ................................................................... 225

Approaches ............................................................. 227

5.9 Trip Planning ........................................................ 233

Trip Planning ............................................................ 233

5.10 RAIM Prediction .................................................. 237

5.11 Navigating a Flight Plan ..................................... 241

5.12 Abnormal Operation ........................................... 268

SECTION 6 HAZARD AVOIDANCE

6.1 XM Satellite Weather .......................................... 271

Activating Services .................................................... 272

Using XM Satellite Weather Products .......................... 273

6.2 WX-500 Stormscope ...........................................295

Setting Up Stormscope on the Navigation Map ...........295

Selecting the Stormscope Page .................................. 299

6.3 Terrain Awareness and Warning System .......... 300

Displaying TAWS Data ............................................... 301

TAWS Page .............................................................. 303

TAWS Alerts .............................................................305

System Status ........................................................... 311

6.4 Trafﬁc Information Service (TIS) ........................ 312

Displaying TRAFFIC Data ........................................... 313

Trafﬁc Map Page ....................................................... 315

TIS Alerts ................................................................. 316

System Status ........................................................... 317

6.5 L-3 Skywatch Trafﬁc Advisory System (TAS) ..... 320

TAS Symbology ......................................................... 320

Operation ................................................................ 321

Altitude Display ........................................................ 323

Trafﬁc Map Page Display Range ................................. 324

TAS Alerts ................................................................325

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

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Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

vii

Page 11

TABLE OF CONTENTS

SECTION 7 AUTOMATIC FLIGHT CONTROL SYSTEM

7.1 AFCS Overview .................................................... 329

Additional AFCS Controls .......................................... 331

7.2 Flight Director Operation ................................... 332

Activating the Flight Director ..................................... 332

AFCS Status Box ....................................................... 333

Flight Director Modes ................................................ 334

Command Bars ......................................................... 334

7.3 Vertical Modes ..................................................... 335

Pitch Hold Mode (PIT) ............................................... 336

Selected Altitude Capture Mode (ALTS) ....................... 337

Altitude Hold Mode (ALT) .......................................... 338

Vertical Speed Mode (VS) .......................................... 339

Flight Level Change Mode (FLC) ................................. 340

Vertical Navigation Modes (VPTH, ALTV) ..................... 342

Glidepath Mode (GP) (WAAS only) ............................. 347

Glideslope Mode (GS) ............................................... 349

Go Around Mode (GA) .............................................. 350

7.4 Lateral Modes ...................................................... 351

Roll Hold Mode (ROL) ...............................................352

Navigation Modes (GPS, VOR, LOC, BC) ...................... 354

Approach Modes (GPS, VAPP, LOC) ............................. 356

7.5 Autopilot and Yaw Damper Operation .............358

Flight Control ........................................................... 358

Engagement ............................................................. 359

Control Wheel Steering ............................................. 359

Disengagement ........................................................ 360

7.6 Example Flight Plan ............................................361

Departure ................................................................362

Intercepting a VOR Radial .......................................... 364

Flying a Flight Plan/GPS Course ................................. 365

Descent ................................................................... 366

Approach ................................................................. 370

Go Around/Missed Approach ..................................... 372

7.7 AFCS Annunciations and Alerts ......................... 374

AFCS Status Alerts .................................................... 374

Overspeed Protection ................................................ 375

SECTION 8 ADDITIONAL FEATURES

8.1 SafeTaxi ................................................................ 377

SafeTaxi Cycle Number and Revision ..........................380

8.2 ChartView ............................................................. 383

ChartView Softkeys ................................................... 383

Terminal Procedures Charts .......................................384

Chart Options ........................................................... 394

Day/Night View ........................................................400

ChartView Cycle Number and Expiration Date ............. 402

8.3 FliteCharts ............................................................ 406

FliteCharts Softkeys .................................................. 406

Terminal Procedures Charts .......................................407

Chart Options ........................................................... 415

Day/Night View ........................................................419

FliteCharts Cycle Number and Expiration Date ............. 421

8.4 XM Radio Entertainment (Optional) ................. 425

Activating XM Satellite Radio Services ........................ 425

Using XM Radio .......................................................427

8.5 Scheduler .............................................................. 431

8.6 Abnormal Operation ........................................... 433

APPENDICES

Annunciations and Alerts ............................................. 435

Alert Level Deﬁnitions ............................................... 437

Aircraft Alerts ........................................................... 437

G1000 System Annunciations .................................... 439

G1000 System Message Advisories ............................. 442

AFCS Alerts .............................................................. 453

TAWS ALERTS ........................................................... 454

SD Card Use ................................................................... 457

Jeppesen Databases .................................................. 457

Garmin Databases .................................................... 458

Glossary .......................................................................... 461

Frequently Asked Questions ........................................ 469

Map Symbols ................................................................. 475

INDEX

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

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. Bviii

Page 12

SECTION 1 SYSTEM OVERVIEW

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

1.1 SYSTEM DESCRIPTION

This section provides an overview of the G1000 Integrated Flight Deck as installed in the Beechcraft A36/G36

Bonanza. The G1000 system is an integrated ﬂight control system that presents ﬂight instrumentation, position, navigation, communication, and identiﬁcation information to the pilot through large-format displays. The system consists of the following Line Replaceable Units (LRUs):

•

GDU 1040

•

GDU 1043/1045

•

GIA 63/63W

•

GDC 74A

•

GEA 71

•

GRS 77

Primary Flight Display (PFD)

Integrated Avionics Unit

Air Data Computer (ADC)

Engine/Airframe Unit

Attitude and Heading Reference System

(AHRS)

•

GMU 44

Magnetometer

Multi Function Display (MFD)

GMA 1347

Beacon Receiver

•

GTX 33

•

GDL 69A

•

GTP 59

•

GSA 81

•

GSM 85

A top-level G1000 system block diagram is shown in Figure 1-1 (it does not include the GSM 85A).

Audio System with Integrated Marker

Mode S Transponder

Satellite Data Link Receiver

Outside Air Temperature (OAT) Probe

AFCS Servos

Servo Gearboxes

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

NOTE:

Refer to the AFCS section for details on the GFC 700 AFCS.

In the Beechcraft A36/G36 Bonanza, the GFC 700 Automated Flight Control System (AFCS) provides the ﬂight

director (FD), autopilot (AP), and yaw damper (YD) functions of the G1000 system.

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 13

SYSTEM OVERVIEW

1.2 LINE REPLACEABLE UNITS (LRU)

SYSTEM

OVERVIEW

• GDU 1040 (1) – The GDU 1040 is conﬁgured as a Primary Flight Displays (PFD) that features a 10.4-inch LCD with 1024 x 768 resolution. The display communicates with the MFD and with the #1 GIA 63/63W Integrated Avionics Unit through a High-Speed Data Bus (HSDB) Ethernet connection.

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

•

GDU 1043/1045

with 1024 x 768 resolution. The display communicates with the PFD and with the #2 GIA 63/63W Integrated Avionics Unit through a High-Speed Data Bus (HSDB) Ethernet connection. The GDU 1045 has a VNV Button, which is needed to enable optional coupled Baro-VNAV AFCS mode.

(1) – The GDU 1043 or GDU 1045 is conﬁgured as an MFD that features a 10.4-inch LCD

HAZARD

AVOIDANCE

AFCS

•

FEATURES

ADDITIONAL

APPENDICESINDEX

GIA 63 or GIA 63W

(2) – Functions as the main communication hub, linking all LRUs with the PFD and MFD. Each GIA 63 contains a GPS receiver, VHF COM/NAV/GS receivers, a ﬂight director (FD) and system integration microprocessors. Each GIA 63W contains a GPS WAAS receiver. Each GIA 63/63W is paired with a display via HSDB connection. The GIA 63/63Ws are not paired together and do not communicate with each other directly.

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B

Page 14

SYSTEM OVERVIEW

•

GDC 74A

pressure altitude, airspeed, vertical speed and OAT information to the G1000 system, and it communicates with the GIA 63(W)s, the displays, and the GRS 77, using an ARINC 429 digital interface (it also interfaces directly with the GTP 59). The GDC 74A is designed to operate in Reduced Vertical Separation Minimum (RVSM) airspace.

•

GEA 71

with both GIA 63(W)s using an RS-485 digital interface.

(1) – Processes data from the pitot/static system as well as the OAT probe. This unit provides

(2) – Receives and processes signals from the engine and airframe sensors. This unit communicates

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& cNS

•

GRS 77

(1) – Provides aircraft attitude and heading information via ARINC 429 to both displays and both GIA 63Ws. The GRS 77 contains advanced sensors (including accelerometers and rate sensors) and interfaces with the GMU 44 to obtain magnetic ﬁeld information, with the GDC 74A to obtain air data, and with both GIA 63/63Ws to obtain GPS information. AHRS modes of operation are discussed later in this document.

•

GMU 44

(1) – Measures local magnetic ﬁeld. Data is sent to the GRS 77 for processing to determine aircraft magnetic heading. This unit receives power directly from the GRS 77 and communicates with the GRS 77 using an RS-485 digital interface.

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 15

SYSTEM OVERVIEW

•

GMA 1347

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

unit also enables the manual control of the display reversionary mode (red communicates with the #1 GIA 63(W), using an RS-232 digital interface.

•

GTX 33

(1) – Solid-state transponder that provides Modes A, C and S capability. The transponder can be controlled from the PFD. The transponder communicates with the GIA 63/63Ws through an RS-232 digital interface.

(1) – Integrates NAV/COM digital audio, intercom system and marker beacon controls. This

DISPLAY BACKUP

button) and

FLIGHT

HAZARD

AFCS

•

MANAGEMENT

AVOIDANCE

•

FEATURES

ADDITIONAL

•

The GSM 85 servo gearbox is responsible for transferring the output torque of the GSA 81 servo actuator to the

APPENDICESINDEX

GDL 69A

(1) – A satellite radio receiver that provides real-time weather information to the G1000 MFD (and, indirectly, to the inset map of the PFD) as well as digital audio entertainment. The GDL 69A communicates with the MFD via HSDB connection. A subscription to the XM Satellite Radio service is required to enable the GDL 69A capability.

GTP 59

GSA 81

(2) – Provides Outside Air Temperature (OAT) data to the GDC 74A.

(4), and

GSM 85

(4) – The GSA 81 servos are used for the automatic control of roll, pitch, yaw, and

pitch trim. These units interface with each GIA 63/63W.

mechanical ﬂight-control surface linkage.

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

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Page 16

SYSTEM OVERVIEW

GTX 33

Transponder

Reversionary

Control

GEA 71

Engine/Airframe

Unit

GDC 74A

Air Data

Computer

OAT

Airspeed

Altitude

rtical Speed

GMU 44

Magnetometer

Heading

Reversionary

Control

GMA 1347

Audio Panel

No. 2 GIA 63/63W

Integrated Avionics Unit

System Integration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS

Glideslope

GPS Output

No. 1 GIA 63/63W

Integrated Avionics Unit

System Inegration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS

Glideslope

GPS Output

GRS 77

AHRS

Attitude

Rate of Turn

Slip/Skid

GDU 1040

Primary Flight Display

GDU 1043/1045

Multi Function Display

L-3 Skywatch

SKY497

Traffic

Advisory System

(optional)

Honeywell

KN 63

DME

(optional)

L-3 WX-500

Stormscope

Lightning Sensor

(optional)

GSA 81 (4)

Servos

GDL 69A

Data Link Weather

and Digital Audio

Entertainment

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

190-00595-01 Rev. B

Figure 1-1 G1000 System Block Diagram

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

Page 17

SYSTEM OVERVIEW

1.3 G1000 CONTROLS

SYSTEM

OVERVIEW

FLIGHT

PFD and MFD are discussed within the following pages of this section.

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

NOTE:

The Audio Panel (GMA 1347) and AFCS controls are also described in the CNS & Audio Panel and

AFCS sections respectively.

The G1000 system controls are located on the PFD and MFD bezels, and the audio panel. The controls for the

PFD/MFD CONTROLS

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

MFD Only

Figure 1-2 PFD/MFD Controls

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B

Page 18

NAV VOL/ID Knob

NAV Frequency Transfer Key

NAV Knob

Heading Knob

Joystick

CRS/BARO Knob

COM Knob

COM Frequency Transfer Key (EMERG)

COM VOL/SQ Knob

SYSTEM OVERVIEW

Turn to control NAV audio volume (shown in the NAV Frequency Box as a percentage) Press to toggle Morse code identiﬁer audio ON/OFF

Transfers the standby and active NAV frequencies

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

Turn to manually select a heading. When operating in Heading Select mode, this knob provides the heading reference to the ﬂight director. Press to display a digital heading momentarily to the left of the HSI and synchronize the Selected Heading to the current heading

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

Turn large knob for altimeter barometric pressure setting Turn the small knob to set the pilot-selected course on the HSI when the VOR1, VOR2, or OBS/SUSP mode is selected. Pressing this knob centers the CDI on the currently selected VOR. The pilot-selected course provides course reference to the pilot-side ﬂight director when operating in Navigation and Approach modes. Press to re-center the CDI and return course pointer directly TO bearing of active waypoint/ station

Turn to tune COM transceiver standby frequencies (large knob for MHz; small for kHz) Press to toggle light blue tuning box between COM1 and COM2 The selected COM (green) is controlled with the COM MIC Key (Audio Panel).

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

Turn to control COM audio volume level (shown as a percentage in the COM Frequency Box) Press to turn the COM automatic squelch ON/OFF

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

Direct-to Key ( )

FPL Key

CLR Key (DFLT MAP)

MENU Key

PROC Key

ENT Key

190-00595-01 Rev. B

Activates the direct-to function and allows the user to enter a destination waypoint and es tablish 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 menu selection or data entry

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

ADDITIONAL

FEATURES

APPENDICES INDEX

Page 19

SYSTEM OVERVIEW

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

FMS Knob (Flight Management System Knob)

Press to turn the selection cursor ON/OFF. Data Entry: With cursor ON, turn to enter data in the highlighted ﬁeld (large knob moves cursor location; small knob selects character for highlighted cursor location) Scrolling: When a list of information is too long for the window/box, a scroll bar appears, indicating more items to view. With cursor ON, turn large knob to scroll through the list. Page Selection: Turn knob on MFD to select the page to view (large knob selects a page group; small knob selects a speciﬁc page from the group)

ALT Knob

Sets the selected altitude in the Selected Altitude Box (the large knob selects the thousands, the small knob selects the hundreds). In addition to providing the standard G1000 altitude alerter function, selected altitude provides an altitude setting for the Altitude Capture/Hold mode of the AFCS.

AP Key

Engages/disengages the Autopilot and Flight Director in the default vertical and lateral modes.

FD Key Activates/deactivates the Flight Director only. Pressing the FD key turns on the Flight Direc-

tor in the default vertical and lateral modes. Pressing the FD key again deactivates the Flight Director and removes the command bars, unless the Autopilot is engaged. If the Autopilot is engaged, the FD key is disabled.

NAV Key

ALT Key

VS Key

FLC Key

Selects/deselects the Navigation mode.

Selects/deselects the Altitude Hold mode.

Selects/deselects the Vertical Speed mode.

Selects/deselects the Flight Level Change mode.

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

YD Key

HDG Key

APR Key

VNV Key (if equipped)

NOSE UP Key

NOSE DN Key

Engages/disengages the Yaw Damper.

Selects/deselects the Heading Select mode.

Selects/deselects the Approach mode.

Selects/deselects Vertical Navigation mode.

Controls the active pitch reference for the Pitch Hold, Vertical Speed, and Flight Level Change modes.

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B

Page 20

SYSTEM OVERVIEW

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

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

OVERVIEW

SYSTEM

Large (Outer)

Knob

Small (Inner)

Knob

Figure 1-3 Dual Concentric Knob

The bottom portion of the MFD bezel features 12 softkeys that are designed to perform various functions depending upon the speciﬁc page being displayed. These softkeys are discussed throughout the Pilot’s Guide documentation.

ADDITIONAL AFCS CONTROLS

The

AP DISC

Switch, and

separately from the AFCS Control Unit. These are discussed in detail in the AFCS section.

(Autopilot Disconnect) Switch,

CWS

(Control Wheel Steering) Button,

MEPT (Manual Electric Pitch Trim) Switch are additional AFCS

GO AROUND

controls and are located in the cockpit,

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

Page 21

SYSTEM OVERVIEW

AUDIO PANEL CONTROLS

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 1-4 Audio Panel Controls (GMA 1347)

NOTE:

COM1 MIC

When a key is selected, a triangular annunciator above the key is illuminated.

– Selects the #1 transmitter for transmitting. COM1 receive is simultaneously selected when this key is pressed allowing received audio from the #1 COM receiver to be heard. COM2 receive can be added by pressing the COM2 Key.

COM1

COM2 MIC

– When selected, audio from the #1 COM receiver can be heard.

– Selects the #2 transmitter for transmitting. COM2 receive is simultaneously selected when this key is pressed allowing received audio from the #2 COM receiver to be heard. COM1 receive can be added by pressing the COM1 Key.

COM2

COM3 MIC

– When selected, audio from the #2 COM receiver can be heard.

– Not used in Beechcraft A36/G36 aircraft.

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B

Page 22

COM3

COM 1/2

SYSTEM OVERVIEW

– Not used in Beechcraft A36/G36 aircraft.

–

Split COM Key. Allows simultaneous transmission on COM1 and COM2 by the pilot and copilot.

OVERVIEW

SYSTEM

TEL

– Not used in Beechcraft A36/G36 aircraft.

SPKR

– Not used in Beechcraft A36/G36 aircraft

– Selects and deselects the cabin speaker. COM and NAV receiver audio can be heard on the

speaker.

MKR/MUTE

– Selects marker beacon receiver audio. Mutes the currently received marker beacon receiver audio. Unmutes automatically when new marker beacon audio is received. Also, stops play of recorded COM audio.

HI SENS

DME

NAV1

ADF

NAV2

AUX

MAN SQ

– Press to increase marker beacon receiver sensitivity. Press again to return to low sensitivity.

– Pressing turns optional DME audio on or off.

– When selected, audio from the #1 NAV receiver can be heard.

– Not used in Beechcraft A36/G36 aircraft.

– When selected, audio from the #2 NAV receiver can be heard.

– Not used in Beechcraft A36/G36 aircraft.

– Enables manual squelch for the intercom. When the intercom is active, press the PILOT Knob

to illuminate SQ. Turn the PILOT/PASS Knobs to adjust squelch.

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

PLAY

– Press once to play the last recorded COM audio. Press again while audio is playing and the previous block of recorded audio is played. Each subsequent press plays each previously recorded block. Pressing the

PILOT

COPLT

PILOT Knob

MKR/MUTE

Key during play of a memory block stops play.

– Selects and deselects the pilot intercom isolation.

– Selects and deselects the copilot intercom isolation.

– Press to switch between volume and squelch control as indicated by illumination of VOL or SQ. Turn to adjust intercom volume or squelch. The MAN SQ Key must be selected to allow squelch adjustment.

PASS Knob

– Turn to adjust Copilot/Passenger intercom volume or squelch. The MAN SQ Key must be

selected to allow squelch adjustment.

DISPLAY BACKUP Button

– Manually selects Reversionary Mode.

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 23

SYSTEM OVERVIEW

1.4 SECURE DIGITAL CARDS

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

right portion of the display bezels. Each display bezel is equipped with two SD card slots. SD cards are used for

EIS

AUDIO PANEL

FLIGHT

aviation database and system software updates as well as terrain database storage.

& CNS

MANAGEMENT

NOTE:

Refer to the Appendices for instructions on updating the aviation database.

Ensure that the G1000 system is powered off before inserting the SD card.

The GDU 1040 and GDU 1043/1045 data card slots use Secure Digital (SD) cards and are located on the top

Install an SD card

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.

Remove an SD card

Gently press on the SD card to release the spring latch and eject the card.

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

1.5 SYSTEM POWER-UP

NOTE:

SD Card Slots

Figure 1-6 Display Bezel SD Card Slots

Refer to the Appendices for AHRS initialization bank angle limitations.

See the Appendices for additional information regarding system-speciﬁc annunciations and alerts.

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B

Page 24

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

NOTE:

See the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual (AFM/POH) for speciﬁc

procedures concerning avionics power application and emergency power supply operation.

The G1000 system is integrated with the aircraft electrical system and receives power directly from electrical busses. The G1000 PFDs, 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 1-7. All system annunciations should disappear typically within one minute of power-up. Upon power-up, key annunciator lights also become momentarily illuminated on the audio panels, the control units 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 one minute of power-up. The AHRS can align itself both while taxiing and during level ﬂight.

When the MFD powers up (Figure 1-8), the MFD Power-up Page displays the following information:

• System version

• Copyright

• Land database name and version

• Terrain database name and version

• Obstacle database name and version

• Aviation database name, version, and effective dates

• ChartView or FliteCharts database information

• Safe Taxi database information

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

• Airport Terrain database name and version

Current database information includes the 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 acknowledges this information and displays the Navigation Map Page.

Figure 1-8 MFD Power-up PageFigure 1-7 PFD Initialization

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 25

SYSTEM OVERVIEW

Audio Panel

Primary Flight Display

Multi Function Display

1.6 SYSTEM OPERATION

SYSTEM

OVERVIEW

The displays are connected together via multiple data busses, thus allowing for high-speed communication. As shown in Figure 1-1, each GIA 63/63W is connected to one display. This section discusses the normal and reversionary modes of operation as well as the various AHRS modes of the G1000 system.

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

NORMAL OPERATION

PFD

In normal mode, the PFD presents graphical ﬂight instrumentation (attitude, heading, airspeed, altitude and vertical speed), thereby replacing the traditional ﬂight instrument cluster. The PFD also offers control for COM and NAV frequency selection.

MFD

In normal mode, the right portion of the MFD displays a full-color moving map with navigation information, while the left portion of the MFD is dedicated to the Engine Indication System (EIS).

Figure 1-9 gives an example of the G1000 displays in normal mode.

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 1-9 Normal Operation

REVERSIONARY MODE

NOTE:

In the event of a display failure, the G1000 System automatically switches to reversionary (backup) mode. In

reversionary mode, all important ﬂight information is presented on the remaining display in the same format as in normal operating mode.

If a display fails, the appropriate IAU Ethernet interface to the display is cut off. Thus, the IAU can no longer

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

The G1000 System alerts the pilot when backup paths are utilized by the LRUs. Refer to Appendix A

for further information regarding system-speciﬁc alerts.

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B

Page 26

Figure 1-10 Reversionary Mode Operation

Audio Panel

Primary Flight Display Failed

Multi Function Display

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

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 (refer to the Audio Panel section for further details). Pressing this

button again deactivates reversionary mode.

Pressing the DISPLAY BACKUP

button activates/deactivates

reversionary mode for both the

PFD and the MFD.

Figure 1-11 DISPLAY BACKUP Button

Should the connection between a PFD and the on-side GIA 63/63W become inoperative, the on-side GIA 63/63W can no longer communicate with the remaining PFD (refer to Figure 1-1). As a result, the NAV and COM functions provided to the failed PFD by the on-side GIA 63/63W are ﬂagged as invalid (red “X”) on the remaining PFD (see Figure 1-12).

Figure 1-12 Inoperative Input (NAV1 Shown)

AHRS OPERATION

NOTE:

Refer to the Appendices for speciﬁc AHRS alert information.

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

NOTE:

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

In addition to using internal sensors, the GRS 77 AHRS uses GPS information, magnetic ﬁeld data and air data to assist in attitude/heading calculations. In normal mode, the AHRS relies upon GPS and magnetic ﬁeld measurements. If either of these external measurements is unavailable or invalid, the AHRS uses air data information for attitude determination. Four AHRS modes of operation are available (see Figure 1-13) and depend upon the combination of available sensor inputs. Loss of air data, GPS, or magnetometer sensor inputs is communicated to the pilot by message advisory alerts.

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

APPENDICES INDEX

Page 27

SYSTEM OVERVIEW

Attitude/Heading Invalid

AHRS

no-GP

Mode

AHRS Normal

Operation

AHRS no-

Mag Mode

AHRS no-Mag/

no-Air Mode

Heading Invalid

available

unavailable

una

vailab

available

unavailable

available

Air Data

Magnetometer Data

unavailable

available

GPS Data

Magnetometer Data

Air Data

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

GPS INPUT FAILURE

NOTE:

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

information provided from one of the GPS receivers is unreliable, the AHRS seamlessly transitions to using the other GPS receiver. An alert message informs the pilot of the use of the backup GPS path. If both GPS inputs fail, the AHRS continues to operate in reversionary No-GPS mode so long as the air data and magnetometer inputs are available and valid.

AIR DATA INPUT FAILURE

failure of the air data input while the AHRS is operating in reversionary No-GPS mode results in invalid attitude and heading information on the PFD (as indicated by red “X” ﬂags).

In-ﬂight initialization of AHRS, when operating without any valid source of GPS data and at true air speed values greater than approximately 200 knots, is not guaranteed. Under these rare conditions, it is possible for in-ﬂight AHRS initialization to take an indeﬁnite amount of time which would result in an extended period of time where valid AHRS outputs are unavailable.

The G1000 system provides two sources of GPS information. If a single GPS receiver fails, or if the

A failure of the air data input has no effect on AHRS output while AHRS is operating in normal mode. A

Figure 1-13 AHRS Operation

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B

Page 28

SYSTEM OVERVIEW

MAGNETOMETER FAILURE

If the magnetometer input fails, the AHRS transitions to one of the reversionary No-Magnetometer modes and continues to output valid attitude information. However, if the aircraft is airborne, the heading output on the PFD does become invalid (as indicated by a red “X”).

G1000 SYSTEM ANNUNCIATIONS

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

NOTE:

For a detailed description of all annunciations and alerts, refer to Appendix A. Refer to the (AFM/

POH) for additional information regarding pilot responses to these annunciations.

When an LRU or an LRU function fails, a large red “X” is typically displayed on windows associated with

the failed data (Figure 1-14 displays all possible ﬂags and responsible LRUs). Upon G1000 power-up, certain windows remain invalid as equipment begins to initialize. All windows should be operational within one minute of power-up. If any window remains ﬂagged, the G1000 system should be serviced by a Garminauthorized repair facility.

GIA 63/63W

Integrated

Avionics Units

GEA 71 Engine

Airframe Unit

GIA 63/63W

Integrated Avionics

Unit

GIA 63/63W Integrated Avionics

Units

GDC 74A Air Data Computer

GRS 77 AHRS Or GMU 44 Magnetometer

EIS

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

190-00595-01 Rev. B

GDC 74A Air

Data Computer

Figure 14 G1000 System Failure Annunciations

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

GIA 63/63W Integrated Avionics Units

GTX 33 Transponder Or GIA 63/63W Integrated Avionics Units

ADDITIONAL

FEATURES

APPENDICES INDEX

Page 29

SYSTEM OVERVIEW

SOFTKEY FUNCTION

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

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

Softkey On

Softkey Names (displayed) Bezel-Mounted Softkeys (press)

Figure 1-15 Softkeys (Second-Level PFD Conﬁguration)

PFD SOFTKEYS

The

CDI, IDENT, TMR/REF, NRST,

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

messages remain after acknowledgement, the ALERTS

The PFD softkeys provide control over ﬂight management functions, including GPS, NAV, terrain, trafﬁc, and lightning. Each softkey sublevel has a level. The ALERTS Softkey is visible in all softkey levels. For the top level softkeys and the transponder (XPDR) levels, the IDENT Softkey remains visible.

INSET OFF DCLTR (3)

TRAFFIC TOPO

and

ALERTS

Softkeys undergo a momentary change to black text

Softkey is black on white.

BACK Softkey which can be pressed to return to the previous

Displays Inset Map in PFD lower left corner Removes Inset Map Selects desired amount of map detail; cycles through declutter levels:

DCLTR (No Declutter): All map features visible DCLTR-1: Declutters land data DCLTR-2: Declutters land and SUA data DCLTR-3: Removes everything except for the active ﬂight plan

Displays trafﬁc information on Inset Map Displays topographical data (e.g., coastlines, terrain, rivers, lakes) and elevation scale

on Inset Map

FEATURES

ADDITIONAL

APPENDICESINDEX

TERRAIN STRMSCP NEXRAD XM LTNG PFD DFLTS

WIND OPTN 1 OPTN 2 OPTN 3 OFF

Displays terrain information on Inset Map Displays Stormscope information on Inset Map (optional) Displays NEXRAD weather and coverage on Inset Map (optional) Displays XM lightning information on Inset Map (optional) Displays second-level softkeys for additional PFD conﬁgurations Resets PFD to default settings, including changing units to standard

Displays softkeys to select wind data parameters Longitudinal and lateral components Total direction and speed Total direction with head and crosswind speed components Information not displayed

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B

Page 30

DME BRG1

HSI FRMT

360 HSI ARC HSI BRG2

ALT UNIT

SYSTEM OVERVIEW

Displays/removes the DME Information Window (optional) Cycles the Bearing 1 Information Window between NAV1, and GPS/ waypoint

identiﬁer and GPS-derived distance information

Displays the softkeys for selecting the two HSI formats

Displays HSI as a 360° compass rose Displays HSI as a 140° viewable arc Cycles the Bearing 1 Information Window between NAV2, and GPS/ waypoint

identiﬁer and GPS-derived distance information Displays softkeys for setting the altimeter and BARO settings to metric units

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

METERS IN

HPA

STD BARO OBS

CDI DME

XPDR STBY ON ALT

GND

VFR CODE 0 — 7 BKSP IDENT

TMR/REF NRST ALERTS

When enabled, displays altimeter in meters Press to display the BARO setting as inches of mercury

Press to display the BARO setting as hectopacals

Sets barometric pressure to 29.92 in Hg (1013 hPa if metric units are selected) Selects OBS mode on the CDI when navigating by GPS (only available with active

leg) Cycles through GPS, VOR1, and VOR2 navigation modes on the CDI Displays the DME Tuning Window, allowing tuning and selection of the DME

(optional) Displays transponder mode selection softkeys Selects standby mode (transponder does not reply to any interrogations) Selects Mode A (transponder replies to interrogations) Selects Mode C – altitude reporting mode (transponder replies to identiﬁcation and

altitude interrogations) Manually selects Ground Mode, the transponder does not allow Mode A and

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

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

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

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 31

SYSTEM OVERVIEW

ALERTS

(optional)

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

STRMSCP

ALERTS

(optional)

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

ALT UNIT

METERS IN HPA

ALERTS

HSI FRMT

360 HSI

ARC HSI ALERTS

(optional)

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

Figure 1-16 Top Level PFD Softkeys

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 1-17 INSET Softkeys

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Figure 1-18 PFD Conﬁguration Softkeys

190-00595-01 Rev. B

Page 32

SYSTEM OVERVIEW

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

Select the BACK Softkey to return to the previous level softkeys.

ALERTS

(optional)

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

Figure 1-19 XPDR Softkeys

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

APPENDICES INDEX

Page 33

SYSTEM OVERVIEW

MFD SOFTKEYS

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

ENGINE ENGINE LEAN CYL SLCT ASSIST SYSTEM

DEC FUEL INC FUEL RST FUEL MAP TRAFFIC TOPO

TERRAIN AIRWAYS (Default label is

dependent on map setup option selected)

STRMSCP NEXRAD XM LTNG BACK DCLTR (3)

SHW CHRT CHKLIST

Displays second-level softkeys for additional EIS conﬁguration Displays default EIS display Displays EIS lean display Allows selection of engine cylinder to view additional information Enables/disables leaning assist mode Displays system oil pressure and temperature, fuel calculations, and electrical system

information Decreases calculated fuel remaining by 1 lb for each softkey press Increases calculated fuel remaining by 1 lb for each softkey press Resets calculated fuel remaining to default and resets fuel used to zero Enables second-level Navigation Map softkeys Displays trafﬁc information on Navigation Map Displays topographical data (e.g., coastlines, terrain, rivers, lakes) and elevation scale

on Navigation Map Displays terrain information on Navigation Map Displays airways on the map; cycles through the following:

AIRWAYS: No airways are displayed AIRWY ON: All airways are displayed AIRWY LO: Only low altitude airways are displayed AIRWY HI: Only high altitude airways are displayed Displays Stormscope information on Navigation Map (optional)

Displays NEXRAD weather and coverage information on Navigation Map Displays XM lightning information on Navigation Map Returns to top-level softkeys Selects desired amount of map detail; cycles through declutter levels:

DCLTR (No Declutter): All map features visible DCLTR-1: Declutters land data DCLTR-2: Declutters land and SUA data DCLTR-3: Removes everything except for the active ﬂight plan When available, displays optional airport and terminal procedure charts

When available, displays optional checklists

APPENDICESINDEX

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

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Page 34

SYSTEM OVERVIEW

MAP

DCLTR

TOPO

BACK

TERRAIN

DCLTR-2

DCLTR-3

DCLTR-1

Select the BACK Softkey on this level to return to the top softkey level.

NEXRAD

XM LTNG

SHW CHRT

CHKLIST

AIRWAYS

AIRWY LO

AIRWAY HI

AIRWY ON

STRMSCP

TRAFFIC

(optional)

ENGINE

BACK

ENGINE SYSTEM

BACK

ENGINE SYSTEM RST FUELDEC FUEL INC FUEL

LEAN

BACK

ENGINE SYSTEM CYL SLCT ASSIST

LEAN

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& cNS

Figure 1-20 MFD Softkeys

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.

These 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 the sensor annunciation persists, check for a system failure message in the Messages Window on the PFD. If no failure message exists, check the GPS Status Page and compare the information for GPS1 and GPS2. Discrepancies may indicate a problem.

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

1) Use the large FMS Knob to select the Auxiliary Page Group (see Section 1.7 for information on navigating MFD

page groups).

Viewing GPS receiver status information

190-00595-01 Rev. B

2) Use the small FMS Knob to select GPS Status Page.

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 35

SYSTEM OVERVIEW

Selecting the GPS receiver for which data may be reviewed

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

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

2) To change the selected GPS receiver:

a) Press the desired

GPS

Softkey.

Or:

a) Press the MENU Key.

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

Satellite Constellation

Diagram

Satellite Signal

Information Status

GPS Receiver

Status

RAIM Availability

Prediction

SBAS Selected

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Satellite Signal Strength Bars

GPS Selection

Softkeys

RAIM Softkey

Selected

Figure 1-21 GPS Status Page (RAIM or SBAS Selected)

SBAS Softkey

Selected

The GPS Status Page provides the following information:

• Satellite constellation diagram

Satellites currently in view are shown at their respective positions on a sky view diagram. The sky view is

always in a north-up orientation, with the outer circle representing the horizon, the inner circle representing 45° above the horizon, and the center point showing the position directly overhead.

Each satellite is represented by an oval containing the Pseudo-random noise (PRN) number (i.e., satellite

identiﬁcation number). Satellites whose signals are currently being used are represented by solid ovals.

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

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SYSTEM OVERVIEW

• Satellite signal information status

The accuracy of the aircraft’s GPS ﬁx is calculated using Estimated Position Uncertainty (EPU), Dilution of Precision (DOP), and horizontal and vertical ﬁgures of merit (HFOM and VFOM). EPU is the radius of a circle centered on an estimated horizontal position in which actual position has 95% probability of laying. EPU is a statistical error indication and not an actual error measurement.

DOP measures satellite geometry quality (i.e., number of satellites received and where they are relative to each other) on a range from 0.0 to 9.9, with lower numbers denoting better accuracy. HFOM and VFOM, measures of horizontal and vertical position uncertainty, are the current 95% conﬁdence horizontal and vertical accuracy values reported by the GPS receiver.

The current calculated GPS position, time, altitude, ground speed, and track for the aircraft are displayed below the satellite signal accuracy measurements.

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

• 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 differential GPS solution, 3D NAV is indicated as the solution until the 3D differential ﬁx has ﬁnished acquisition. SBAS (Satellite-Based Augmentation System) indicates INACTIVE. When acquisition is complete, the solution status indicates 3D DIFF NAV and SBAS indicates ACTIVE.

• RAIM (Receiver Autonomous Integrity Monitoring) Prediction (

RAIM Softkey is selected)

In most cases performing a RAIM prediction is not necessary. However, in some cases, the selected approach may be outside the WAAS coverage area and it may be necessary to perform a RAIM prediction for the intended approach.

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.

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

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

Because of the tighter protection limit on approaches, there may be times when RAIM is not available. The G1000 automatically monitors RAIM and warns with an alert message when it is not available. If RAIM is not predicted to be available for the ﬁnal approach course, the approach does not become active, as indicated by the messages “Approach is not active” and “RAIM not available from FAF to MAP”. If RAIM is not available when crossing the FAF, the missed approach procedure must be ﬂown.

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

APPENDICES INDEX

Page 37

SYSTEM OVERVIEW

Predicting RAIM availability at a selected waypoint

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

1) Select the GPS Status Page.

2) If necessary, press the RAIM Softkey.

3) Press the

FMS

Knob

. The ‘WAYPOINT’ ﬁeld is highlighted.

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

5) Enter the desired waypoint:

a) Use the FMS Knob to enter the desired waypoint by identiﬁer, facility, or city name and press the ENT Key. Refer

to Section 1.7 for instructions on entering alphanumeric data into the G1000.

Or:

a) Turn the small FMS Knob counter-clockwise to display a list of ﬂight plan waypoints (the FPL list is populated

only when navigating a ﬂight plan).

b) Turn the small FMS Knob clockwise to display the NRST, RECENT, or AIRWAY waypoints, if required.

c) Turn the large FMS Knob clockwise to select the desired waypoint. The G1000 automatically ﬁlls in the identiﬁer,

facility, and city ﬁelds with the information for the selected waypoint.

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

6) Use the FMS Knob to enter an arrival time and press the ENT Key.

7) Use the FMS Knob to enter an arrival date and press the ENT Key.

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

of the following is displayed:

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

• ‘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

Predicting RAIM availability at present position

1) Select the GPS Status Page.

2) If necessary, press the RAIM Softkey.

3) Press the

FMS

Knob

. The ‘WAYPOINT’ ﬁeld is highlighted.

4) Press the MENU Key.

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

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

7) Use the FMS Knob to enter an arrival time and press the ENT Key.

8) Use the FMS Knob to enter an arrival date and press the ENT Key.

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

of the following is displayed:

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B

Page 38

SYSTEM OVERVIEW

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

• ‘COMPUTING AVAILABILITY’—RAIM calculation in progress

OVERVIEW

SYSTEM

• ‘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

• SBAS Selection (SBAS Softkey is selected) In certain situations, such as when the aircraft is outside or on the fringe of the WAAS coverage area, it may

be desireable to disable WAAS (although it is not recommended). When disabled, the SBAS ﬁeld in the GPS Status box indicates DISABLED.

Disabling WAAS

1) Select the GPS Status Page.

2) If necessary, press the SBAS Softkey.

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.

• GPS Satellite Signal Strengths The GPS Status Page can be helpful in troubleshooting weak (or missing) signal levels due to poor satellite

coverage or installation problems. As the GPS receiver locks onto satellites, a signal strength bar is displayed for each satellite in view, with the appropriate satellite PRN number (01-32 or 120-138 for WAAS) below each bar. The progress of satellite acquisition is shown in three stages, as indicated by signal bar appearance:

- No bar—Receiver is looking for the indicated satellite

- Hollow bar—Receiver has found the satellite and is collecting data

- Light blue bar—Receiver has collected the necessary data and the satellite signal can be used

- Green bar—Satellite is being used for the GPS solution

- Checkered bar—Receiver has excluded the satellite (Fault Detection and Exclusion)

- “D” indication—Denotes the satellite is being used as part of the differential computations

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

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).

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

ADDITIONAL

FEATURES

APPENDICES INDEX

Page 39

SYSTEM OVERVIEW

1.7 ACCESSING G1000 FUNCTIONALITY

SYSTEM

OVERVIEW

MENUS

The G1000 has a MENU Key that, when pressed, displays a context-sensitive list of options. This options list

allows the user to access additional features or make settings changes which speciﬁcally relate to the currently

FLIGHT

INSTRUMENTS

displayed window/page. There is no all-encompassing menu. Some menus provide access to additional submenus that are used to view, edit, select, and review options. Menus display ‘NO OPTIONS’ when there are no options for the window/page selected. The main controls used in association with all window/page group operations are described in section 1.3. Softkey selection does not display menus or submenus.

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

Navigating the Page Menu Window

1) Press the MENU Key to display the Page Menu Window.

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

when the option list is longer than the window).

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

4) The CLR Key may be pressed to remove the menu and cancel the operation. Pressing the FMS Knob also

removes the displayed menu.

No Options with NRST Window Displayed on the PFD

Options with FPL Window Displayed

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 1-22 Page Menu Examples

MFD PAGE GROUPS

NOTE:

The page group and active page title box are displayed in the upper center of the screen.

Refer to the Flight Management, Hazard Avoidance, and Additional Features sections for details on

speciﬁc pages.

Page Group Active Page Title

Figure 1-23 Page Title Box

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

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Page 40

SYSTEM OVERVIEW

In the bottom right corner of the screen, the current page group, number of pages available in the group, and

placement of the current page within the group are indicated.

OVERVIEW

SYSTEM

Page Groups

Figure 1-24 Page Group Icons

Pages in Current Group

Selected Page

The MFD displays information in four main page groups; speciﬁc pages within each group can vary depending

on the conﬁguration of optional equipment.

Selecting a page using the FMS Knob

1) Turn the

Turn

large FMS

the

small FMS

Knob until the desired page group is selected.

Knob until the desired page is selected.

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

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

Map Pages (MAP)

Navigation Map

Trafﬁc Map

Stormscope®(optional)

Weather Data Link (service optional)

Terrain

Figure 1-25 Map Pages

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 41

SYSTEM OVERVIEW

Waypoint Pages (WPT)

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

Airport Information pages

- Airport Information (INFO Softkey)

- Departure Information (DP Softkey)

- Arrival Information (STAR Softkey)

- Approach Information (APR Softkey)

- Weather Information (WX Softkey)

Intersection Information

NDB Information

VOR Information

User Waypoint Information

Airport

Information

Pages

Figure 1-26 Waypoint Pages

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Auxiliary Pages (AUX)

Trip Planning

Utility

GPS Status

System Setup

XM Satellite pages

- XM Information (INFO Softkey)

- XM Radio (RADIO Softkey)

System Status

Satellite

Pages

Figure 1-27 Auxiliary Pages

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B

Page 42

Nearest Pages (NRST)

Nearest Airports

Nearest Intersections

Nearest NDB

Nearest VOR

Nearest User Waypoints

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

Nearest Frequencies

Nearest Airspaces

Figure 1-28 Nearest Pages

In addition to the main page groups accessed exclusively using the

FMS Knobs, there are pages for ﬂight planning (FPL) and loading procedures (PROC) which are accessed by a dedicated key. In some instances, softkeys may be used to access the Procedure Pages.

The Flight Plan Pages are accessed using the

FPL Key.. Main pages within this group are selected by turning

the small FMS Knob.

Flight Plan Pages (FPL)

Active Flight Plan

- Wide View, Narrow View (VIEW Softkey)

Flight Plan Catalog

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

Stored Flight Plan (NEW Softkey)

190-00595-01 Rev. B

Figure 1-29 Flight Plan Pages

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

APPENDICES INDEX

Narrow and

Wide View

Page 43

SYSTEM OVERVIEW

The Procedure pages may be accessed at any time on the MFD by pressing the PROC Key. A menu is

SYSTEM

OVERVIEW

initialized, and when a departure, approach, or arrival is selected, the appropriate Procedure Loading Page is opened. Turning the FMS Knob does not scroll through the Procedure pages (note the single page icon in the lower right corner).

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

Procedure Pages (PROC)

Departure Loading

Arrival Loading

Approach Loading

Figure 1-30 Procedure Pages

For some of these pages (Airport Information pages, XM Satellite pages, Procedure pages), the title of the page

may change while the page icon remains the same.

MFD SYSTEM PAGES

In the Auxiliary (AUX) Page Group, there are two system pages: System Setup (page 4 of 6) and System Status (page 6 of 6). The System Setup Page allows management of various system parameters, while the System Status Page displays the status of all G1000 system LRUs.

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

SYSTEM SETUP PAGE

G1000 system settings are managed from the System Setup Page. The following settings can be changed:

• Date/time

• Displayed navigation angle reference, temperature,

and position settings

• Airspace alerts

(see the Flight Management Section)

• Arrival alerts

(see the Flight Management Section)

• Audio alerts

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

• MFD Navigation Status Box ﬁelds (see the Flight Management Section)

• CDI scaling for GPS navigation source (see the Flight Instruments Section)

• COM channel spacing (see the Audio Panel and CNS Section)

• Criteria for displaying nearest airports (see the Flight Management Section)

190-00595-01 Rev. B

Page 44

Restoring system setup defaults:

1) Select the AUX - System Setup Page.

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

2) Press the DFLTS Softkey; or press the MENU Key, highlight ‘Restore Defaults’, and press the ENT Key.

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& cNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

Figure 1-31 System Setup Page

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 45

SYSTEM OVERVIEW

DATE/TIME

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

The G1000 obtains the current Universal Coordinated Time (UTC) date and time directly from the GPS satellite signals (shown on the AUX - GPS Status Page, Figure 1-22). System time (displayed in the lower right corner of the PFD) can be displayed in three formats: local 12-hr, local 24-hr, or UTC. Local time is set by adding/subtracting an offset (hours:minutes) to/from UTC.

Figure 1-32 System Time (Local 24-hr Format)

Conﬁguring the system time:

1) Select the AUX - System Setup Page.

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

2) Press the FMS Knob to activate the cursor.

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

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

Offset’ ﬁeld is highlighted.

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

Figure 1-33 Date/Time Settings (System Setup Page)

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B

Page 46

SYSTEM OVERVIEW

PILOT PROFILES

System settings may be saved under a pilot proﬁle. When the system is powered on, the last selected pilot proﬁle is shown on the MFD Power-up Splash Screen (Figure 1-8). The G1000 can store up to 25 proﬁles; the currently active proﬁle, the amount of memory used, and the amount of memory available are shown at the top of the System Setup Page in the box labeled ‘Pilot Proﬁle’. From here, pilot proﬁles may be created, selected, renamed, or deleted.

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& cNS

Figure 1-34 Display Unit Settings (System Setup Page)

Creating a proﬁle:

1) Select the AUX - System Setup Page.

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

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

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

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

cannot begin with a blank as the ﬁrst letter.

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

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

7) Press the ENT Key.

190-00595-01 Rev. B

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

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 47

SYSTEM OVERVIEW

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

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

Or:

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

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

Selecting an active proﬁle:

1) Select the AUX - System Setup Page.

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

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

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

5) Press the ENT Key. The G1000 loads and displays the system settings for the selected proﬁle.

Renaming a proﬁle:

1) Select the AUX - System Setup Page.

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

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

4) Press the ENT Key.

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

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

6) Press the ENT Key.

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

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

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

Deleting a proﬁle:

1) Select the AUX - System Setup Page.

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

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

4) Press the ENT Key.

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

6) Press the ENT Key.

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

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

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B

Page 48

SYSTEM OVERVIEW

DISPLAY UNITS

Units in which various quantities are displayed on the G1000 screens are listed on the System Setup Page. The Navigation Angle reference, the Temperature units, and the Position units can be set from here.

Category Settings Affected Quantities Exceptions

Navigation Angle

Magnetic (North)* True (North)

Distance and

Nautical* Crosstrack error (HSI)

Speed***

Altitude and Vertical Speed

Temperature

Feet* Meters

Celsius* Fahrenheit

Fuel and Fuel Flow Gallons*

Imperial Gallons Kilograms Liters Pounds

Weight** Pounds*

Kilograms

Position

HDDD°MM.MM’* HDDD°MM’SS.S”

* Default setting ** Contact a Garmin-authorized service center to change this setting *** Not conﬁgurable

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

Airspeed Indicator Bearing distances (information windows) DME distance (information window) Flight plan distances

True Airspeed (PFD)

Wind speed vector

Map range (Trafﬁc Page, Terrain Map ranges DIS, GS, TAS, XTK ﬁelds (Navigation Status Box) All distances on MFD

CDI scaling (System Setup)

Fuel range calculation (EIS) Altitude buffer distance (System Setup) Arrival Alert trigger distance (System Setup) All speeds on MFD

All altitudes on MFD All elevations on MFD

Altimeter

Vertical Speed Indicator

VNV altitudes (Active Flight Plan) All temperatures on PFD

Engine Indication System (EIS) Total Air Temperature (Trip Planning Page)

Fuel parameters (Trip Planning Page)

Engine Indication System (EIS)

N/A N/A

All positions N/A

Proximity/TAWS Page)

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

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AUDIO PANEL

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Changing a display unit setting

1) While on the System Setup Page, press the FMS Knob momentarily to activate the ﬂashing cursor.

2) Turn the large FMS Knob to highlight the desired ﬁeld in the Display Units Box.

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

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SYSTEM OVERVIEW

3) Turn the small FMS Knob to select the desired units.

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4) Press the ENT Key. Press the CLR Key to cancel the action without changing the units.

ARRIVAL ALERTS

The Arrival Alert Box on the System Setup Page allows arrival alerts to be turned on/off and the alert trigger distance set. An arrival alert can be set to notify the pilot with a message upon reaching a userspeciﬁed distance from the ﬁnal destination (the direct-to waypoint or the last waypoint in a ﬂight plan). Once the set distance (up to 99.9 units) has been reached, an “Arrival at [waypoint]” message is displayed in the PFD Navigation Status Box.

Figure 1-35 Arrival Alert Settings (System Setup Page)

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Enabling/disabling an arrival alert:

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

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

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

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

Changing the arrival alert trigger distance:

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

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

3) Turn the large FMS Knob to highlight the distance ﬁeld in the Arrival Alert Box.

4) Use the FMS Knob to enter a trigger distance and press the ENT Key.

AUDIO ALERTS

The Audio Alert Box on the System Setup Page allows the audio alert voice to be set to male or female.

Changing the audio alert voice

1) While on the System Setup Page, press the FMS Knob momentarily to activate the ﬂashing cursor.

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

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

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SYSTEM OVERVIEW

SYSTEM STATUS PAGE

The System Status Page displays the status and software version numbers for all detected system LRUs. Pertinent information on all system databases is also displayed. Active LRUs are indicated by green check marks and failed LRUs are indicated by red “X”s. Failed LRUs should be noted and a service center or Garmin dealer informed.

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Figure 1-36 Example System Status Page

The LRU, ARFRM, and DBASE Softkeys on the System Status Page select the list (LRU Info, Airframe, or Database) through which the FMS Knob can be used to scroll if all the information cannot appear on the screen.

The ANN TEST Softkey, when pressed, causes an annunciation test tone to be played.

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SYSTEM OVERVIEW

UTILITY PAGE

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For ﬂight planning purposes, timers, trip statistics, and a scheduler feature are provided on the AUX Utility Page. The timers available include a stopwatch-like generic timer, a total time in ﬂight timer, and a record of the time of departure. Trip statistics—odometer, trip odometer, and average trip and maximum groundspeeds—are displayed from the time of the last reset. Refer to the Additional Features section for a dicussion on the Scheduler feature.

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Figure 1-37 Utility Page

TIMERS

The G1000 timers available include:

• Stopwatch-like generic timers (available from the PFD Timer/References Window and on the MFD AUX

- Utility Page)

• Total-time-in-ﬂight timer (MFD AUX - Utility Page)

• Time since departure (MFD AUX - Utility Page)

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

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Setting the generic timer (PFD):

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OVERVIEW

SYSTEM

1) Press the

2) Turn the

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

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

press the

6) With ‘START?’ highlighted, press the

TMR/REF

large FMS

ENT

Key.

Softkey.

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

ENT

Key.

small FMS

ENT

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

Knob to select the timer counting direction (UP/DN) and

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

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

digits are reset.

9) To remove the window, press the

CLR

Key or the

TMR/REF

Softkey.

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Figure 1-38 Generic Timer (PFD Timer/References Window)

Setting the generic timer (MFD AUX - Utility Page)

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

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

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

4) If a desired starting time is desired:

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

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

5) Turn the

large FMS

Knob to highlight ‘START?’ and press the

ENT

Key.

ENT

Key to start the timer. The ﬁeld changes to

‘STOP?’.

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

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

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Figure 1-39 Timers (MFD AUX - Utility Page)

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The ﬂight timer can be set to count up from zero starting at system power-up or from the time that the aircraft lifts off; the timer can also be reset to zero at any time.

Setting the ﬂight timer starting criterion

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

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

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

4) Turn the

small FMS

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

ENT

Key.

Resetting the ﬂight timer

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

2) Press the

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

Key.

ENT

Key.

The G1000 records the time at which departure occurs, depending on whether the pilot prefers the time to be recorded from system power-up or from aircraft lift off. The displayed departure time can also be reset to display the current time at the point of reset. The format in which the time is displayed is controlled from the System Setup Page.

Setting the departure timer starting criterion

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

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

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

4) Turn the

small FMS

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

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

ENT

Key.

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Resetting the departure time

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

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

2) Press the

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

Key.

ENT

Key.

TRIP STATISTICS

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

Resetting trip statistics readouts

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

2) Press the

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

• Reset Odometer—Resets odometer readout only

• Reset Maximum Speed—Resets maximum speed readout only

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

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

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

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

ENT

Key. The selected parameters are reset

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SCHEDULER

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The G1000’s Scheduler feature can be used to enter and display reminder messages (e.g., “Change oil”, “Switch fuel tanks”, “Overhaul”) in the Alerts Window on the PFD. Messages can be set to display based on a speciﬁc date and time (event), once the message timer reaches zero (one-time; default setting), or recurrently whenever the message timer reaches zero (periodic). Message timers set to periodic alerting automatically reset to the original timer value once the message is displayed. When power is cycled, messages are retained until deleted, and message timer countdown is restarted.

Figure 1-40 Scheduler (Utility Page)

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Entering a scheduler message:

1) Select the AUX - Utility Page.

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

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

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

ENT

Key.

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

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

• Event—Message issued at the speciﬁed date/time

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

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

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

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

countdown and press the ENT Key.

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9) For event-based messages:

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

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SYSTEM

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

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

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

Deleting a scheduler message:

1) Select the AUX - Utility Page.

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

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

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

5) Press the ENT Key to conﬁrm message deletion.

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

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Figure 1-41 PFD Alerts Window

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SYSTEM OVERVIEW

1.8 DISPLAY BACKLIGHTING

SYSTEM

OVERVIEW

The PFD and MFD display backlighting, the PFD and MFD bezel, and the Audio Panel keys can be adjusted

manually in one of two ways:

• Using the individual dimmer bus control for the desired display, or

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• Using the PFD Setup Menu and the following procedures. In normal operating mode, backlighting can only be

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adjusted from the PFDs. In reversionary mode, adjustments can be made from any remaining displays.

Adjusting display backlighting:

1) Press either PFD

Key to display the PFD Setup Menu. ‘AUTO’ is now highlighted next to ‘PFD1 DSPL’. If

desired, turn the large FMS Knob to select ‘AUTO’ next to ‘MFD DSPL’ or ‘PFD2 DSPL’.

2) Turn the

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

4) To remove the menu, press the

small FMS

Knob to select ‘MANUAL’ and press the

CLR

Key.

ENT

Key. The intensity value is now highlighted.

ENT

Key.

Adjusting key backlighting:

1) Press either PFD

2) Turn the

3) Turn the

large FMS

small FMS

Key to display the PFD Setup Menu. ‘AUTO’ is now highlighted next to ‘PFD1 DSPL’.

Knob to highlight ‘PFD DSPL’, ‘MFD DSPL’, or ‘PFD2 DSPL’, as desired.

Knob in the direction of the green arrowhead to display ‘PFD1 KEY’, ‘MFD KEY’, or ‘PFD2

KEY’.

4) Turn the

5) Turn the

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

large FMS

small FMS

Knob to highlight ‘AUTO’.

Knob to select ‘MANUAL’ and press the

ENT

Key. The intensity value is now highlighted.

ENT

Key.

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ADDITIONAL

APPENDICESINDEX

7) To remove the menu, press the

CLR

Key.

Figure 1-42 PFD Setup Menu

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SECTION 2 FLIGHT INSTRUMENTS

FLIGHT INSTRUMENTS

OVERVIEW

SYSTEM

WARNING:

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

to the backup instruments.

NOTE:

The Automatic Flight Control System (AFCS) provides additional readouts and bugs on selected ﬂight instruments. Refer to the AFCS Section for details on these bugs and readouts, as they appear on the display during certain AFCS modes.

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

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

• Airspeed Indicator, showing

– True Airspeed

– Airspeed awareness ranges

– Reference ﬂags

• Attitude Indicator with slip/skid indication

• Altimeter, showing

• Horizontal Situation Indicator, showing

– Heading and course indications

– Turn Rate Indicator

– Navigation source

– Bearing pointers and information windows

– DME Information Window (optional)

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– Barometric setting

– Selected Altitude

• Vertical Deviation/Glideslope Indicators

• Vertical Speed Indicator (VSI)

• Vertical Navigation indications

The PFD also displays various alerts and annunciations.

– Course Deviation Indicator (CDI)

• DME Tuning Window (optional)

• Outside air temperature (OAT)

• System time

• Wind data

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NAV Frequency Box

Airspeed Indicator

True Airspeed

Altimeter Barometric Setting

Vertical Speed Indicator (VSI)

Selected Altitude Bug

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Current Heading

Horizontal Situation Indicator ( HSI)

Outside Air Temperature (OAT)

Softkeys

System Time

Transponder Data Box

Selected Heading Bug

Turn Rate Indicator

Figure 2-1 Primary Flight Display (Default)

Altimeter

Selected Altitude

COM Frequency Box

AFCS Status Box

Navigation Status Box

Slip/Skid Indicator

Attitude Indicator

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Trafﬁc Annunciation

Alerts Window

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Selected Heading

Inset Map

DME Information Window

Bearing Information Windows

Selected Course

Barometric Minimum Descent Altitude

Annunciation Window

Vertical Deviation/Glideslope Indicator

Marker Beacon Annunciation

AFCS Status Annunciation

Figure 2-2 Additional PFD Information

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FLIGHT INSTRUMENTS

2.1 FLIGHT INSTRUMENTS

SYSTEM

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AIRSPEED INDICATOR

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NOTE:

Refer to the Pilot’s Operating Handbook (POH) and FAA Approved Airplane Flight Manual (AFM) for

speed criteria and Vspeed values.

The Airspeed Indicator displays airspeed on a rolling number gauge using a moving tape. The true airspeed

(TAS) is displayed in knots below the Airspeed Indicator.

The numeric labels and major tick marks on the moving tape are marked at intervals of 10 knots, while minor

tick marks on the moving tape are indicated at intervals of 5 knots. Speed indication starts at 20 knots, with 60 knots of airspeed viewable at any time. The actual airspeed is displayed inside the black pointer. The pointer remains black until reaching never-exceed speed (VNE), at which point it turns red.

Airspeed

Trend

Vector

Actual

Airspeed

Speed

Ranges

True

Airspeed

Vspeed

References

Figure 2-4 Red Pointer

Showing Airspeed Above V

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Figure 2-3 Airspeed Indicator

A color-coded (white, green, yellow, and red) speed range strip is located on the moving tape. The colors

denote ﬂaps operating range, normal operating range, caution range, and never-exceed speed (VNE). Speeds above the never-exceed speed (VNE), appear in the high speed warning range, represented on the airspeed tape by red/white “barber pole” coloration.

A red low speed awareness range extends up to the low speed awareness velocity, V

. An aural stall warning

LSA

is generated as the aircraft approaches a stall condition.

The Airspeed Trend Vector is a vertical, magenta line, extending up or down on the airspeed scale, located

to the right of the color-coded speed range strip. The end of the trend vector displays approximately what airspeed will be reached in 6 seconds if the current acceleration is maintained. If the trend vector crosses VNE, the text of the actual airspeed readout changes to yellow while the pointer remains black. The trend vector is absent if the speed remains constant or if any data needed to calculate airspeed is not available due to a system failure.

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Black reference markers along the right side of the airspeed scale denote GLIDE, VX, and VY. GLIDE, VX, and VY may be set and displayed using the Timer/References window. By default, all Vspeed values are reset and all ﬂags turned off when power is cycled.

Vspeed Flag

GLIDE G

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Table 2-1 Vspeed Flag Labels

Figure 2-5 VSpeed References

A solid white triangle is automatically set at the maximum landing gear extension speed. This indication is always displayed and cannot be turned off by the pilot.

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Figure 2-6 Maximum Landing Gear

Extended Speed Reference

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NOTE:

Refer to the Pilot’s Operating Handbook (POH) and FAA Approved Airplane Flight Manual (AFM) for

speed criteria and Vspeed values.

Changing Vspeeds and turning Vspeed ﬂags on/off:

1) Press the

2) Turn the

TMR/REF

large FMS

Softkey.

Knob to highlight the desired Vspeed.

3) Use the small FMS Knob to change the Vspeed in 1-kt increments (when a speed has been changed from a

default value, an asterisk appears next to the speed).

4) Press the

5) Turn the

6) To remove the window, press the

ENT

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

small FMS

Knob clockwise to ON or counterclockwise to OFF.

CLR

Key or the

TMR/REF

Softkey.

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Figure 2-7 Vspeed References

(Timer/References Window)

Vspeed ﬂags can be turned on or off and values restored all at once.

Modifying Vspeeds (on, off, restore defaults):

1) Press the

2) Press the

TMR/REF

Key.

Softkey.

3) Turn the FMS Knob to highlight the desired selection.

4) Press the

ENT

Key.

5) To remove the window, press the CLR Key or the TMR/REF Softkey.

Figure 2-8 Page Menu

(Timer/References Window)

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FLIGHT INSTRUMENTS

ATTITUDE INDICATOR

Attitude information is displayed over a virtual blue sky and brown ground with a white horizon line. The Attitude Indicator displays the pitch (indicated by the yellow symbolic aircraft on the pitch scale), roll, and slip/skid information.

Roll Pointer

Roll Scale

Horizon Line

Aircraft Symbol

Land Representation

Pitch Scale

Slip/Skid Indicator

Sky Representation

Roll Scale Zero

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Figure 2-9 Attitude Indicator

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

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

The Slip/Skid Indicator is the bar beneath the roll pointer. The indicator moves with the roll pointer and moves laterally away from the pointer to indicate lateral acceleration. Slip/skid is indicated by the location of the bar relative to the pointer. One bar displacement is equal to one ball displacement on a traditional Slip/Skid Indicator.

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Figure 2-10 Slip/Skid Indication

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ALTIMETER

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

The Selected Altitude is displayed above the Altimeter in the box indicated by a selection bug symbol. A bug corresponding to this altitude is shown on the tape; if the Selected Altitude exceeds the range shown on the tape, the bug appears at the corresponding edge of the tape. See the AFCS Section for more information about how the G1000 uses the Selected Altitude.

Setting the Selected Altitude:

Turn the

ALT SEL

Knob to set the Selected Altitude in 100-ft increments (if baro-min reference is set, the selected

altitude can be set in 10 feet increments to match the baro-min value).

If an altitude is set in the Minimum Descent Altitude/Decision Height (MDA/DH), it is also available for the

altitude preslector Selected Altitude.

Selected Altitude

Bug

Altitude

Trend

Vector

Selected

Altitude

Current

Altitude

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Minimum Descent

Altitude/Decision

Height Bug

Barometric

Setting

Figure 2-11 Altimeter

Figure 2-12 Altimeter (Metric Units)

Selected and current altitudes can also be displayed in meters (readouts displayed above the normal readouts in feet; Figure 2-12). Note that the altitude tape does not change scale.

Displaying altitude in meters:

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

2) Press the ALT UNIT Softkey.

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

4) Press the

BACK

Softkey to return to the top-level softkeys.

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FLIGHT INSTRUMENTS

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

OVERVIEW

SYSTEM

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

Selecting the altimeter barometric pressure setting:

Turn the BARO Knob to select the desired setting.

Selecting standard barometric pressure (29.92 in Hg):

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

2) Press the STD BARO Softkey.

Changing altimeter barometric pressure setting units:

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

2) Press the ALT UNIT Softkey.

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

Or, press the HPA Softkey to display the barometric pressure setting in hectopascals (hPa; see Figure 2-12).

4) Press the

BACK

Softkey to return to the top-level softkeys.

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

VERTICAL SPEED INDICATOR (VSI)

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

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

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 67

FLIGHT INSTRUMENTS

VERTICAL DEVIATION

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

NOTE:

The Vertical Deviation Indicator (VDI; Figure 2-13) uses a magenta chevron to indicate the baro-VNV vertical deviation when Vertical Navigation (VNV) is being used; the VDI appears in conjunction with the “TOD within 1 minute” alert. Full-scale deﬂection (two dots) is 1000 feet. The VDI is removed from the display if vertical deviation becomes invalid. See the Flight Management Section for details on VNV features, and refer to Section

2.2, Supplemental Flight Data, for more information about VNV indications on the PFD.

The Glideslope Indicator (Figure 2-14) appears to the left of the Altimeter whenever an ILS frequency is tuned in the active NAV ﬁeld and the heading is less than 105° from the inbound course. A green diamond acts as the Glideslope Indicator, like a glideslope needle on a conventional indicator. If a localizer frequency is tuned and there is no glideslope, “NO GS” is annunciated.

The Glidepath Indicator is only shown for aircraft with GIA 63W Integrated Avionics Units when

WAAS is available.

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

The glidepath is analogous to the glideslope for GPS approaches supporting WAAS vertical guidance (LNAV+V, L/VNV, LPV) and is generated by the system to reduce pilot workload during approach. When an approach of this type is loaded into the ﬂight plan and GPS is the selected navigation source, the Glidepath Indicator (Figure 2-15) appears as a magenta diamond. If the approach type downgrades past the ﬁnal approach ﬁx (FAF), “NO GP” is annunciated.

VNV Target

Altitude

Vertical

Deviation

Indicator

Figure 2-13 Vertical Speed and

Deviation Indicators (VSI and VDI)

Vertical

Speed

Indicator

Vertical

Speed

Pointer

Required

Vertical

Speed

Indicator

Glideslope

Indicator

Figure 2-14 Glideslope Indicator

Marker Beacon

Annunciation

Glidepath

Indicator

Figure 2-15 Glidepath Indicator

APPENDICESINDEX

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

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FLIGHT INSTRUMENTS

HORIZONTAL SITUATION INDICATOR (HSI)

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

Changing the HSI display format:

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

1) Press the

PFD

Softkey.

2) Press the HSI FRMT Softkey.

3) Press the

360 HSI

ARC HSI

Softkey.

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

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

190-00595-01 Rev. B

Turn Rate Indicator

Current Track Indicator

Lateral Deviation Scale

Navigation Source

Aircraft Symbol

Course Deviation Indicator (CDI)

Rotating Compass Rose

OBS Mode Active

To/From Indicator

Course Pointer

Heading Bug

Flight Phase

Lubber Line

Turn Rate/Heading Trend Vector

Current Heading

Figure 2-16 Horizontal Situation Indicator (HSI)

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

ADDITIONAL

FEATURES

APPENDICES INDEX

Page 69

FLIGHT INSTRUMENTS

The Arc HSI is a 140˚ expanded section of the compass rose. The Arc HSI contains a Course Pointer,

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

To/From Indicator, a sliding deviation indicator (the To/From and deviation indicators are combined), and a deviation scale. Upon station passage, the To/From Indicator ﬂips and points to the tail of the aircraft, just like a conventional To/From ﬂag. Depending on the navigation source, the CDI on the Arc HSI can appear in two different ways: an arrowhead (GPS, VOR, OBS) or a diamond (LOC).

Course Pointer

Navigation Source

Lateral Deviation Scale

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

Adjusting the Selected Heading:

Flight Phase Annunciation

Course Deviation and

To/From Indicator

Figure 2-17 Arc HSI

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

Turn the

HDG

Knob to set the Selected Heading.

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

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

Adjusting the Selected Course:

Turn the

CRS

Knob to set the Selected Course.

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

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

Current Track

Indicator

Selected Heading

Figure 2-18 Heading and Course Indications

Current Heading

Selected Course

Selected Heading Bug

APPENDICESINDEX

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

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Page 70

FLIGHT INSTRUMENTS

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

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

Figure 2-19 Heading and Course Indications (True)

Changing the navigation angle setting:

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

2) Press the FMS Knob to activate the cursor.

3) Turn the

large FMS

Knob to highlight ‘Nav Angle’ in the ‘Display Units’ box (Figure 2-20).

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

• TRUE - References angles to true north (denoted with ‘T’)

• MAGNETIC - Angles corrected to the computed magnetic variation (‘Mag Var’)

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

190-00595-01 Rev. B

Figure 2-20 Navigation Angle Settings

(AUX-System Setup Page)

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

ADDITIONAL

FEATURES

APPENDICES INDEX

Page 71

FLIGHT INSTRUMENTS

TURN RATE INDICATOR

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

The Turn Rate Indicator is located directly above the rotating compass card. Tick marks to the left and right

of the lubber line denote half-standard and standard turn rates. A magenta Turn Rate Trend Vector shows the current turn rate. The end of the trend vector gives the heading predicted in 6 seconds, based on the present turn rate. A standard-rate turn is shown on the indicator by the trend vector stopping at the standard turn rate tick mark, corresponding to a predicted heading of 18˚ from the current heading. At rates greater than 4 deg/sec, an arrowhead appears at the end of the magenta trend vector and the prediction is no longer valid.

Half Standard

Turn Rate

Standard

Turn Rate

Figure 2-21 Turn Rate Indicator and Trend Vector

Arrow Shown

for Turn Rate

> 4 Degrees

per Second

BEARING POINTERS AND INFORMATION WINDOWS

NOTE:

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

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

Two bearing pointers and associated information can be displayed on the HSI for NAV and GPS sources.

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Tuning Mode

Frequency

Distance

DME Information Window

(optional)

Distance to

Bearing Source

Bearing

Source

Bearing 1 Information Window

Station

Identiﬁer

Pointer

Icon

Figure 2-22 HSI with Bearing and DME Information

Bearing 1

Pointer

Bearing 2

Pointer

Waypoint

Selected

Pointer

Icon

Bearing 2 Information Window

Bearing

Source

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

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FLIGHT INSTRUMENTS

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

Information windows (Figure 2-22) are displayed to the lower sides of the HSI and show:

OVERVIEW

SYSTEM

• Bearing source (NAV, GPS)

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

• Frequency (NAV)

• Station/waypoint identiﬁer (NAV, GPS)

• GPS-derived great circle distance to bearing source

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

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

• The NAV radio is not receiving the tuned VOR

station

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

Selecting bearing display and changing sources:

1) Press the PFD Softkey.

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

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

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

DME INFORMATION WINDOW

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

NOTE:

DME radio installation is optional.

The DME Information Window is displayed above the BRG1 Information Window and shows the DME

label, tuning mode (NAV1, NAV2, or HOLD), frequency, and distance. When a signal is invalid, the distance

AFCS

is replaced by “–.– – NM”. Refer to the Audio Panel and CNS Section for information on tuning the radios.

Displaying the DME Information Window:

1) Press the PFD Softkey.

FEATURES

2) Press the DME Softkey to display the DME Information Window above the BRG1 Information Window.

3) To remove the DME Information Window, press the DME Softkey again.

APPENDICES INDEX

ADDITIONAL

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 73

FLIGHT INSTRUMENTS

COURSE DEVIATION INDICATOR (CDI)

SYSTEM

OVERVIEW

NOTE

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

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

The Course Deviation Indicator (CDI) moves left or right from the course pointer along a lateral deviation

FLIGHT

INSTRUMENTS

scale to display aircraft position relative to the course. If the course deviation data is not valid, the CDI is not displayed.

360º HSI

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

Arc HSI

Flight Phase

CDI

Navigation

Source

CDI

Flight

Phase

Navigation

Scale

Crosstrack

Error

Figure 2-23 Course Deviation Indicator

Source

Crosstrack

Error

CDI Scale

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

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 2-24 Navigation Sources

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B62

Page 74

FLIGHT INSTRUMENTS

Changing navigation sources:

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

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

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

box over the NAV2 standby frequency.

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

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

NAV2 Selected for Tuning

CDI

Softkey

Cycles Through

Navigation Sources

GPS

Selected

NAV1 Selected for Tuning

LOC1

Selected

Figure 2-25 Selecting a Navigation Source

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

when all of the following occur:

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

VOR2

Selected

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

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

• A valid localizer frequency has been tuned

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

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

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

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

ADDITIONAL

FEATURES

APPENDICES INDEX

Page 75

FLIGHT INSTRUMENTS

GPS CDI SCALING

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

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

The current GPS CDI scale setting is displayed as ‘System CDI’ on the AUX - System Setup Page and the fullscale deﬂection setting may also be changed (2.0 nm, 1.0 nm, 0.3 nm, or Auto) from this page (

Figure 2-26

). If the selected scaling is smaller than the automatic setting for enroute and terminal phases, the CDI is scaled accordingly and the selected setting is be displayed rather than the ﬂight phase annunciation.

Changing the selected GPS CDI setting:

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

2) Press the FMS Knob to activate the cursor.

3) Turn the

large FMS

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

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

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

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 2-26 GPS CDI Settings

(AUX-System Setup Page)

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

current phase of ﬂight (Figure 2-27, 2-28, 2-29, Table 2-2).

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B64

Page 76

FLIGHT INSTRUMENTS

0.3 nm

Missed

Approach

2.0 nm

Enroute

(Oceanic if >200 nm from nearest airport)

1.0 nm

Terminal

1.0 nm

Terminal

0.3 nm

Departure

CDI Full-scale Deflection

Refer to accompanying

approach CDI scaling figures

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

Figure 2-27 Automatic CDI Scaling

• When a departure procedure is active, the CDI is scaled for departure (0.3 nm).

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

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

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

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

• At 30 nm from the departure airport the enroute phase of ﬂight is automatically entered and CDI scaling changes to 2.0 nm over a distance of 1.0 nm, except under the following conditions:

- When navigating with an active departure procedure, the ﬂight phase and CDI scale does not change

until the aircraft arrives at the last departure waypoint (if more than 30 nm from the departure airport) or the leg after the last departure waypoint has been activated or a direct-to waypoint is activated.

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

• Within 31 nm of the destination airport (terminal area), the CDI scale gradually ramps down from 2.0 nm to 1.0 nm over a distance of 1.0 nm; except under the following conditions:

- When navigating with an active arrival route, the ﬂight phase and CDI scale does not change until the

aircraft arrives at the ﬁrst waypoint in the arrival route (if within 31 nm from the destination airport).

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

190-00595-01 Rev. B

• During approach, the CDI scale ramps down even further (see Figures 2-28 and 2-29). This transition normally occurs within 2.0 nm of the ﬁnal approach ﬁx (FAF). The CDI switches to approach scaling automatically once the approach procedure is activated or if Vector-to-Final (VTF) is selected.

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

ﬁnal approach segment course.

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

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

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

APPENDICES INDEX

Page 77

FLIGHT INSTRUMENTS

1.0 nm

2 nm

350 ft

angle set by system

0.3 nm

FAF

CDI Full-scale Deflection

CDI scale is set to the smaller of 0.3 nm

or an angle set by the syste

CDI scale varies if VTF is activated

1.0 nm

2 nm

FAF

0.3 nm

course width

Landing

Threshold

CDI Full-scale Deflection

angle based on database information

CDI scale varies if VTF is activated

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

Figure 2-28 Typical LNAV and LNAV+V Approach CDI Scaling

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

Figure 2-29 Typical LNAV/VNAV and LPV Approach CDI Scaling

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

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

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

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

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

Flight Phase Annunciation Automatic CDI Full-scale Deﬂection

Departure DPRT 0.3 nm Terminal

TERM 1.0 nm

Enroute ENR 2.0 nm Oceanic OCN 2.0 nm

Approach (Non-precision)

Approach (Non-precision with

LNAV

1.0 nm decreasing to 350 feet depending on variables (see Figure 2-30)

LNAV + V

Vertical Guidance) Approach

(LNAV/VNAV) Approach

(LPV)

L/VNAV

LPV

1.0 nm decreasing to a speciﬁed course width, then

0.3 nm, depending on variables (see Figure 2-31)

Missed Approach MAPR 0.3 nm

APPENDICESINDEX

Table 2-2 Automatic GPS CDI Scaling

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B66

Page 78

OBS MODE

FLIGHT INSTRUMENTS

OVERVIEW

SYSTEM

NOTE:

VNV is inhibited while automatic waypoint sequencing has been suspended.

Enabling Omni-bearing Selector (OBS) Mode suspends the automatic sequencing of waypoints in a GPS ﬂight plan (GPS must be the selected navigation source), but retains the current “active-to” waypoint as the navigation reference even after passing the waypoint. ‘OBS’ is annunciated to the lower right of the aircraft symbol when OBS Mode is selected (see Figure 2-30).

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

GPS

Selected

Extended

Course

Line

OBS

Mode

Enabled

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

Pressing the

Softkey Suspends

Waypoint Sequencing

OBS

Figure 2-30 Omni-bearing Selector (OBS) Mode

Pressing the

Softkey Again Returns

to Normal Operation

OBS

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 79

FLIGHT INSTRUMENTS

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

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

1) Press the OBS Softkey to select OBS Mode.

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

Selected Course with the bearing to the next waypoint.

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

As the aircraft crosses the missed approach point (in approach mode), automatic approach waypoint

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

OBS

Softkey label changes to SUSP.

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

SUSP

Softkey Suspends

Waypoint Sequencing

SUSP

Annunciation

Figure 2-31 Suspending Automatic Waypoint Sequencing

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B68

Page 80

2.2 SUPPLEMENTAL FLIGHT DATA

FLIGHT INSTRUMENTS

OVERVIEW

SYSTEM

NOTE:

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

Map, and wind data display.

In addition to the ﬂight instruments, the PFD also displays various supplemental information, including

temperatures, wind data, and Vertical Navigation (VNV) indications.

TEMPERATURE DISPLAYS

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

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

Normal Display

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

Reversionary Mode

Figure 2-32 Outside Air Temperature

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 81

FLIGHT INSTRUMENTS

WIND DATA

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

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

Option 2Option 1

Option 3

Figure 2-33 Wind Data

No Data

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Displaying wind data:

1) Press the PFD Softkey.

2) Press the WIND Softkey to display wind data below the Selected Heading.

3) Press one of the OPTN softkeys to change how wind data is displayed:

• OPTN 1: Head and crosswind components

• OPTN 2: Total wind direction and speed

• OPTN 3: Total wind direction with head and crosswind speed components

4) To remove the window, press the OFF Softkey.

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

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Page 82

FLIGHT INSTRUMENTS

VERTICAL NAVIGATION (VNV) INDICATIONS

When a VNV ﬂight plan has been activated, VNV indications (VNV Target Altitude, RVSI, VDI) appear on the PFD in conjunction with the “TOD within 1 minute” message and “Vertical track” voice alert. See the Flight Management section for details on VNV features. VNV indications are removed from the PFD according to the criteria listed in Table 2-3.

Top of Descent Message

VNV Target

Altitude

Vertical

Deviation

Indicator

Required

Vertical

Speed

Indicator

GPS is

Selected

Navigation

Source

Enroute

Phase of

Flight

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

Figure 2-34 Vertical Navigation Indications (PFD)

VNV Indication Removed

Criteria

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

Required Vertical

Speed (RVSI)

X X X X X X

Vertical

Deviation (VDI)

VNV Target

Altitude

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

unsupported ﬂight plan leg type (see Flight Management

X X X

Section) Aircraft > 250 feet below active VNV Target Altitude Current crosstrack or track angle error has exceeded limit Active altitude-constrained waypoint can not be reached within

maximum allowed ﬂight path angle and vertical speed

Last altitude-constrained waypoint in active ﬂight plan reached

X X X X X X

X X

(30 sec before)

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Table 2-3 VNV Indication Removal Criteria

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 83

FLIGHT INSTRUMENTS

2.3 PFD ANNUNCIATIONS AND ALERTING FUNCTIONS

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

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

information on alerts and annunciations.

G1000 ALERTING SYSTEM

Messages appear in the Alerts Window (in the lower right corner of the PFD; Figure 2-35) when a warning, caution, advisory alert, or G1000 message advisory occurs. System alert messages are provided for awareness of G1000 system problems or status and may not require pilot action. The Alerts Window allows system alerts to be displayed simultaneously. The FMS Knob can be used to scroll through the alert messages. The Alerts Window is enabled/disabled by selecting the message is generated, selecting the ALERTS Softkey to acknowledge the message causes it to turn gray.

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

ALERTS

Softkey. If the window is already open when a new

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

Annunciation

Window

Alerts

Window

Softkey

Annunciation

Figure 2-35 G1000 Alerting System

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

APPENDICESINDEX

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

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Page 84

FLIGHT INSTRUMENTS

Warnings are time-critical and require immediate attention. A ﬂashing WARNING Softkey annunciation and

aural tone (single chime every two seconds) indicate the presence of a warning. The aural tone and ﬂashing

WARNING Softkey annunciation continue until acknowledged (by pressing the

WARNING

Softkey).

OVERVIEW

SYSTEM

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

CAUTION

Softkey).

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

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

ADVISORY

Softkey).

Figure 2-36 Softkey Annunciation (ALERTS Softkey Labels)

MARKER BEACON ANNUNCIATIONS

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

Inner MarkerMiddle MarkerOuter Marker

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

190-00595-01 Rev. B

Altimeter

Figure 2-37 Marker Beacon Annunciations

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

Page 85

FLIGHT INSTRUMENTS

TRAFFIC ANNUNCIATION

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

The G1000 System displays trafﬁc symbolically on the PFD Inset Map, the Navigation Map Page (MFD), and various other MFD page maps. Refer to the Hazard Avoidance Section and Appendix E for more details about the Trafﬁc Information Service (TIS) and optional Trafﬁc Advisory Systems (TAS). When a trafﬁc advisory (TA) is detected, the following automatically occur:

• The PFD Inset Map is enabled and displays trafﬁc

• A ﬂashing black-on-yellow ‘TRAFFIC’ annunciation (Figure 2-39) appears to the top left of the Attitude

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

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

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

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

Trafﬁc

Symbol

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 2-38 Inset Map with Trafﬁc Displayed

TAWS ANNUNCIATIONS (OPTIONAL)

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

Inset Map Enabled,

Displaying Trafﬁc

When TA Detected

Figure 2-39 Trafﬁc and Example TAWS Annunciations

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B74

Page 86

FLIGHT INSTRUMENTS

ALTITUDE ALERTING

The Altitude Alerting function provides the pilot with visual and aural alerts when approaching the Selected Altitude. Whenever the Selected Altitude is changed, the Altitude Alerter is reset. The Altitude Alerter is independent of the GFC 700 AFCS, but alerting tones are generated only when the GFC 700 is installed. The following occur when approaching the Selected Altitude:

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

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

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

on a black background and ﬂashes for 5 seconds.

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

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

aural tone is generated.

Within 1000 ft Within 200 ft Deviation of ±200 ft

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

Figure 2-40 Altitude Alerting Visual Annunciations

LOW ALTITUDE ANNUNCIATION (WAAS ONLY)

NOTE:

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

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

The Low Altitude Annunciation is available only for aircraft with GIA 63W Integrated Avionics Units

Altimeter

Figure 2-41 Low Altitude on GPS WAAS Approach

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 87

FLIGHT INSTRUMENTS

MINIMUM DESCENT ALTITUDE/DECISION HEIGHT ALERTING

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

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

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

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

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

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

Minimums”, is generated.

Altitude ReachedWithin 100 feetWithin 2500 feet

MDA/DH Bug

MDA/DH Setting

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

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

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

1) Press the

TMR/REF

Softkey.

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

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

Knob to highlight the next ﬁeld.

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

5) To remove the window, press the

Figure 2-43 Minimum Descent Altitude/Decision Height Setting

CLR

Key or the

(Timer/References Window)

TMR/REF

Softkey.

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

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B76

Page 88

2.4 ABNORMAL OPERATIONS

FLIGHT INSTRUMENTS

OVERVIEW

SYSTEM

ABNORMAL GPS CONDITIONS

The annunciations listed in Table 2-4 can appear on the HSI when abnormal GPS conditions occur; see Figure

2-44 for examples. Refer to the Flight Management Section for more information on Dead Reckoning Mode.

Annunciation Location Description

LOI

WARN

INTEG OK

Lower left of

aircraft symbol

Lower left of

aircraft symbol

Lower left of

aircraft symbol

Upper right of

aircraft symbol

Table 2-4 Abnormal GPS Conditions Annunciated on HSI

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

Warning–RAIM function detects excessive GPS position errors

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

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

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

Figure 2-44 Example HSI Annunciations

Dead Reckoning Mode causes the CDI to be removed from the display (when GPS is the selected navigation

source) and the following items on the PFD to be shown in yellow:

• Current Track Bug

• Wind Data (calculated based on GPS information)

• Distances in the Bearing Information windows

• GPS bearing pointers

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

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 89

FLIGHT INSTRUMENTS

UNUSUAL ATTITUDES

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

• Trafﬁc Annunciations

• AFCS Annunciations

HAZARD

• Flight director Command Bars

AVOIDANCE

• Inset Map

• Outside air temperature (OAT)

• DME Information Window

AFCS

• Wind data

• Transponder Status Box

When the aircraft enters an unusual pitch attitude, red extreme pitch warning chevrons pointing toward the horizon are displayed on the Attitude Indicator, starting at 50˚ above and 30˚ below the horizon line.

Nose High

Figure 2-45 Pitch Attitude Warnings

Nose Low

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

(optional)

• PFD Setup Menu

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

– Timer/References

– Nearest Airports

– Flight Plan

– Alerts

– Procedures

– DME Tuning (optional)

• Minimum Descent Altitude/ Decision Height readout

• Vertical Deviation, Glideslope, and Glidepath Indicators

• Altimeter Barometric Setting

• Selected Altitude

• Selected Course

• Selected Heading

• VNV Target Altitude

• System Time

FEATURES

ADDITIONAL

APPENDICESINDEX

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B78

Page 90

SECTION 3 ENGINE INDICATION SYSTEM

ENGINE INDICATION SYSTEM

OVERVIEW

SYSTEM

NOTE:

Refer to the Pilot’s Operating Handbook (POH) and FAA Approved Airplane Flight Manual (AFM) for

operating limitations.

The G1000 Engine Indication System (EIS) displays critical engine, electrical, fuel quantity and fuel ﬂow parameters on the left side of the Multi Function Display (MFD) during normal operations (Figure 3-1). In Reversionary Mode, the displays are re-conﬁgured to present Primary Flight Display (PFD) symbology together with the EIS (Figure 3-2).

EIS

Display

Figure 3-1 MFD (Normal Operations)

Failed NAV/COM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

EIS

Display

Figure 3-2 PFD (Reversionary Mode)

Green bands on the instrument scales indicate normal ranges of operation; yellow and red bands indicate caution and warning, respectively. White or uncolored bands indicate areas outside of normal operation not yet in the caution or warning ranges. When an unsafe operating condition occurs, readouts, pointers and labels change color corresponding to the level of the condition; warnings also ﬂash. If the sensor data for a parameter becomes invalid or unavailable, a red “X” is displayed across the indicator and/or readout.

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 91

ENGINE INDICATION SYSTEM

ENGINE

BACKSYSTEM

LEAN

BACK

DEC FUEL

SYSTEM

LEAN

INC FUEL

ENGINE

Press the ENGINE Softkey to return to the default Engine Page level.

Press the BACK Softkey to return to the previous softkey level.

BACK

SYSTEM

LEAN

Press the ENGINE or BACK Softkey to return to the default Engine Page level.

ASSISTCYL SLCT

ENGINE

RST FUEL

EIS information is presented in three displays, accessed using the ENGINE Softkey on the MFD:

SYSTEM

• Engine Display – Default display, shows all critical engine, fuel and electrical indicators.

OVERVIEW

• Lean Display – Provides engine leaning information.

• System Display – Shows numeric readouts of critical engine, fuel and electrical indicators.

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 3-3 Engine Softkey Flowchart

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B80

Page 92

3.1 ENGINE DISPLAY

ENGINE INDICATION SYSTEM

OVERVIEW

SYSTEM

NOTE:

Refer to the Pilot’s Operating Handbook (POH) and FAA Approved Airplane Flight Manual (AFM) for

operating limitations.

The Engine Display is the default EIS display and can be selected by pressing the ENGINE or BACK Softkey when another EIS display is currently shown. Beneath the dial gauges are the horizontal bar indicators for fuel ﬂow, cylinder head temperature, oil temperature and pressure, alternator load, bus voltage and fuel quantity.

Fuel Flow

Leaning

Pointer

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

Figure 3-4 Engine Display

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 93

ENGINE INDICATION SYSTEM

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

Engine Manifold Pressure

Gauge (MAN IN HG)

Tachometer (RPM)

Fuel Flow Indicator

(FFLOW GPH)

Cylinder Head Temperature

(CHT)

Oil Temperature

(OIL TEMP)

Oil Pressure (OIL PRES)

Ammeter (ALT LOAD)

Bus Voltage (BUS VOLTS)

Fuel Quantity Indicator

(FUEL QTY GAL)

Displays engine power in inches of Mercury (in Hg)

Displays propeller speed in revolutions per minute (rpm); the red band

indicates propeller overspeed

Displays current fuel ﬂow in gallons per hour (gph)

Fuel Flow Leaning Pointer (light blue) provide a leaning reference during

a cruise or max power climb (MPC). The pointer is displayed below the Fuel Flow Indicator if the propeller speed exceeds 2530 rpm or fuel ﬂow exceeds a speciﬁed value based on altitude during a cruise or max power (MPC) climb

The pointer, displaying the cylinder number, shows the highest cylinder

head temperature

Displays the oil temperature

Displays pressure of oil supplied to the engine

Displays load for alternators 1 and 2

Displays the primary bus voltage for buses 1 and 2

Displays the quantity of fuel in each tank in gallons

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B82

Page 94

3.2 LEAN DISPLAY

ENGINE INDICATION SYSTEM

OVERVIEW

SYSTEM

NOTE:

The pilot should follow the engine manufacturer’s recommended leaning procedures as described in

the Pilot’s Operating Handbook (POH) and FAA Approved Airplane Flight Manual (AFM).

The Lean Display is accessed by pressing the ENGINE Softkey followed by the LEAN Softkey and provides information for assistance during engine leaning.

Manifold Gauge, Tachometer and digital Fuel Flow Indication remain on the Lean Display. Exhaust Gas Temperature (EGT) and Cylinder Head Temperature (CHT) are displayed graphically with numeric readouts for the selected cylinder.

Bars for cylinders whose EGT and CHT are within normal range are shown in white. On the CHT bar graph, caution and warning conditions for each cylinder are indicated by color change of the bar to yellow or red, respectively. By default, the cylinder with the hottest EGT and CHT is selected (bar indicated in light blue) when the LEAN Softkey is pressed. The readouts below the bar graphs correspond to the selected cylinder.

Accessing the EIS Lean Display:

1) Press the ENGINE Softkey.

2) Press the LEAN Softkey.

3) To return to the default Engine Display, press the ENGINE or BACK Softkey.

From the Lean Display, the CYL SLCT and ASSIST Softkeys can be utilized to obtain information about speciﬁc cylinders on both the EGT and CHT graphs. Pressing the CYL SLCT Softkey cycles through the cylinders; the selected cylinder is displayed in light blue. The CYL SLCT Softkey is disabled during warning or caution conditions or when the ASSIST Softkey is pressed.

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

Monitoring the desired cylinder’s EGT and CHT:

From the Lean Display, press the CYL SLCT Softkey to cycle through each cylinder and view its EGT and CHT.

The ASSIST Softkey may be used to assist in the leaning process by identifying the peak of the ﬁrst cylinder whose temperature falls. The peaked cylinder is selected and a light blue bar appears above the cylinder’s bar to indicate EGT peak. A readout showing the temperature deviation from peak (∆PEAK) is displayed above the EGT bar graph. If the temperature of the peaked cylinder exceeds the peak value, the peak value is not updated.

Monitoring of the cylinder continues until the ASSIST Softkey is pressed again which disables lean assist and removes the peak line from the bar graph and the temperature deviation from peak (∆PEAK). The system then returns to seeking the hottest cylinder.

Selecting the Engine Lean Assist function:

From the Lean Display, press the ASSIST Softkey to identify the EGT peak.

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

Page 95

ENGINE INDICATION SYSTEM

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

Light Blue Bar

Representing

EGT Peak

Temperature

Deviation

From Peak

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 3-5 Lean Display

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B84

Page 96

ENGINE INDICATION SYSTEM

OVERVIEW

SYSTEM

Engine Manifold Pressure

Gauge (MAN IN HG)

Tachometer (RPM)

Fuel Flow

(FFLOW GPH)

Exhaust Gas Temperature

Bar Graph (EGT °C)

Cylinder Head Temperature

Bar Graph (CHT °C)

Displays engine power in inches of Mercury (in Hg)

Displays propeller speed in revolutions per minute (rpm); the red band

indicates propeller overspeed

Displays current fuel ﬂow in gallons per hour (gph)

The number of the cylinder with the highest Exhaust Gas Temperature

(EGT) is highlighted in light blue and its readout given below the bar graph in degrees Celsius (°C).

A light blue bar appears above the cylinder’s bar to represent the peak

EGT for the selected cylinder when the ASSIST Softkey is pressed.

The number of the cylinder with the highest head temperature is

highlighted in light blue and its readout given below the bar graph in degrees Celsius (°C).

A caution or warning condition is denoted by color change of a cylinder’s

bar to yellow or red, respectively.

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

Page 97

ENGINE INDICATION SYSTEM

3.3 SYSTEM DISPLAY

SYSTEM

OVERVIEW

NOTE:

Fuel calculations do not use the aircraft Fuel Quantity Indicator and are calculated from the last time

the fuel was reset.

FLIGHT

INSTRUMENTS

EIS

below the Manifold Pressure Gauge and Tachometer are grouped into three categories: System (Oil), Fuel Calculations and Electrical.

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

NOTE:

Refer to the Pilot’s Operating Handbook (POH) and FAA Approved Airplane Flight Manual (AFM) for

operating limitations.

The System Display is accessed by pressing the ENGINE Softkey followed by the SYSTEM Softkey. Readouts

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 3-6 System Display

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B86

Page 98

Engine Manifold Pressure

Gauge (MAN IN HG)

Tachometer (RPM)

Oil Temperature (OIL °C)

ENGINE INDICATION SYSTEM

Displays engine power in inches of Mercury (in Hg)

Displays propeller speed in revolutions per minute (rpm); the red band

indicates propeller overspeed

Displays oil temperature in degrees Celsius (°C)

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

Oil Pressure (OIL PSI)

Fuel Flow (FFLOW GPH)

Calculated Fuel Remaining

(GAL REM)

Calculated Fuel Used

Displays oil pressure in pounds per square inch (psi)

Displays current fuel ﬂow in gallons per hour (gph)

Displays the totalizer-based fuel remaining in gallons, adjusted using the

DEC FUEL and INC FUEL Softkeys

Displays fuel used in gallons, based on fuel ﬂow

(GAL USED)

Calculated Endurance

Displays the calculated endurance in hours:minutes (HH:MM)

(ENDUR)

Calculated Range

Displays the calculated range in nautical miles (nm)

(RANGE NM)

Ammeter

Displays load for alternators 1 and 2 as a percentage of the capacity

(ALT LOAD)

Voltmeter

Displays the primary bus voltage for buses 1 and 2

(BUS VOLTS)

Fuel calculations are based on the fuel ﬂow totalizer and the displayed fuel remaining (GAL REM), adjusted using the following softkeys:

• DEC FUEL – Decreases totalizer-based fuel remaining in one-gallon increments

• INC FUEL – Increases totalizer-based fuel remaining in one-gallon increments

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

• RST FUEL – Resets totalizer-based fuel remaining to the aircraft’s fuel capacity

Accessing the EIS System Display:

1) Press the ENGINE Softkey.

2) Press the SYSTEM Softkey.

3) To return to the default Engine Display, press the ENGINE or BACK Softkey.

Adjusting the fuel totalizer quantity:

From the System Display, press the

Resetting the fuel totalizer:

From the System Display, press the

190-00595-01 Rev. B

remaining (GAL REM).

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

DEC FUEL or INC FUEL

RST FUEL

Softkey. This also resets the fuel remaining (GAL REM) to zero.

Softkey to obtain the desired number of gallons

ADDITIONAL

FEATURES

APPENDICES INDEX

Page 99

ENGINE INDICATION SYSTEM

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

BLANK PAGE

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

190-00595-01 Rev. B88

Page 100

SECTION 4 AUDIO PANEL AND CNS

AUDIO PANEL AND CNS

OVERVIEW

SYSTEM

4.1 OVERVIEW

The Communication/Navigation/Surveillance (CNS) system includes the Audio Panel, communication radios, navigation radios, and Mode S transponder. The System Overview Section provides a block diagram description of the Audio Panel and CNS system interconnection.

CNS operation in Beechcraft A36/G36 aircraft is performed by the following Line Replaceable Units (LRUs):

• Primary Flight Display (PFD)

• Multi Function Display (MFD)

• Integrated Avionics Unit (2)

The MFD/PFD controls are used to tune the communication transceivers and navigation radios.

The Audio Panel provides the traditional audio selector functions of microphone and receiver audio selection. The Audio Panel includes an intercom system (ICS) between the pilot, copilot, and passengers, a marker beacon receiver, and a COM clearance recorder. Ambient noise from the aircraft radios is reduced by a feature called Master Avionics Squelch (MASQ). When no audio is detected, MASQ processing further reduces the amount of background noise from the radios.

The Mode S transponder is controlled with softkeys and the (PFD). The Transponder Data Box is located to the left of the System Time Box. The data box displays the active four-digit code, mode, and reply status (Figure 4-1).

• Audio Panel

• Mode S Transponder

FMS Knob located on the Primary Flight Display

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

190-00595-01 Rev. B

Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX