Garmin A36, G36 Pilot's Guide

Page 1

Beechcraft A36/G36

Page 2

This manual reﬂects the operation of System Software version 0464.05 or later. Some differences in operation may be observed when comparing the information in this manual to earlier or later software versions.

Garmin International, Inc., 1200 East 151st Street, Olathe, Kansas 66062, U.S.A. Tel: 913/397.8200 Fax: 913/397.8282

Garmin AT, Inc., 2345 Turner Road SE, Salem, OR 97302, U.S.A. Tel: 503/391.3411 Fax: 503/364.2138

Garmin (Europe) Ltd., Unit 5, The Quadrangle, Abbey Park Industrial Estate, Romsey, Hampshire S051 9DL, U.K Tel: 44/1794.519944 Fax: 44/0870.8501251

Garmin Corporation, No. 68, Jangshu 2nd Road, Shijr, Taipei County, Taiwan Tel: 886/02.2642.9199 Fax: 886/02.2642.9099

Website Address: www.garmin.com

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

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

NavData® is a registered trademark of Jeppesen, Inc.; Stormscope® is a registered trademark of L-3 Communications; Ryan® is a registered trademark of Avidyne Corporation

October 2006 Printed in the U.S.A

, and XM® is a registered trademark of XM Satellite Radio, Inc.

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

190-00595-00 Rev. A

Page 3

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 Web site at “http://www.garmin.com” or contact Garmin Customer Service at 800-800-1020.

190-00595-00 Rev. A

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

Page 4

WARNINGS, CAUTIONS, AND NOTES

WARNING:

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

WARNING:

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

WARNING:

The Garmin G1000, as installed in the Beechcraft A36/G36, has a very high degree of functional integrity. However, the pilot must recognize that providing monitoring and/or self-test capability for all conceivable system failures is not practical. Although unlikely, it may be possible for erroneous operation to occur without a fault indication shown by the G1000. It is thus the responsibility of the pilot to detect such an occurrence by means of cross-checking with all redundant or correlated information available in the cockpit.

WARNING:

For safety reasons, G1000 operational procedures must be learned on the ground.

WARNING:

The altitude calculated by G1000 GPS receivers is geometric height above Mean Sea Level and could vary signiﬁcantly from the altitude displayed by pressure altimeters, such as the GDC 74A Air Data Computer, or other altimeters in aircraft. GPS altitude should never be used for vertical navigation. Always use pressure altitude displayed by the G1000 PFD or other pressure altimeters in aircraft.

WARNING:

The Jeppesen database used in the G1000 system must be updated regularly in order to ensure that its information remains current. Updates are released every 28 days. A database information packet is included in the G1000 package. Pilots using an outdated database do so entirely at their own risk.

WARNING:

The basemap (land and water data) must not be used for navigation, but rather only for nonnavigational situational awareness. Any basemap indication should be compared with other navigation sources.

CAUTION:

The illustrations in this guide are only examples. Never use the G1000 to attempt to penetrate a thunderstorm. Both the FAA Advisory Circular, Subject: Thunderstorms, and the Airman’s Information Manual (AIM) recommend avoiding “by at least 20 miles any thunderstorm identiﬁed as severe or giving an intense radar echo.”

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

190-00595-00 Rev. Aii

Page 5

WARNINGS, CAUTIONS, AND NOTES

CAUTION:

The United States government operates the Global Positioning System and is solely responsible for its accuracy and maintenance. The GPS system is subject to changes which could affect the accuracy and performance of all GPS equipment. Portions of the Garmin G1000 utilize GPS as a precision electronic NAVigation AID (NAVAID). Therefore, as with all NAVAIDs, information presented by the G1000 can be misused or misinterpreted and, therefore, become unsafe.

CAUTION:

To reduce the risk of unsafe operation, carefully review and understand all aspects of the G1000 Pilot’s Guide documentation. Thoroughly practice basic operation prior to actual use. During ﬂight operations, carefully compare indications from the G1000 to all available navigation sources, including the information from other NAVAIDs, visual sightings, charts, etc. For safety purposes, always resolve any discrepancies before continuing navigation.

CAUTION:

The Garmin G1000 does not contain any user-serviceable parts. Repairs should only be made by an authorized Garmin service center. Unauthorized repairs or modiﬁcations could void both the warranty and the pilot’s authority to operate this device under FAA/FCC regulations.

CAUTION:

The GDU 1040 PFD and MFD displays use a lens coated with a special anti-reﬂective coating that is very sensitive to skin oils, waxes, and abrasive cleaners. CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI-REFLECTIVE COATING. It is very important to clean the lens using a clean, lint-free cloth and an eyeglass lens cleaner that is speciﬁed as safe for anti-reﬂective coatings.

NOTE:

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

NOTE:

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

NOTE:

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. Avoid the clusters to avoid the thunderstorms. In the cell display mode, even a single discharge point may represent thunderstorm activity and should therefore be avoided.

190-00595-00 Rev. A

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

iii

Page 6

REVISION INFORMATION

Record of Revisions

Part Number

190-00595-00 A 10/16/06 ALL Initial release

Revision Date Page Range Description

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

190-00595-00 Rev. Aiv

Page 7

TABLE OF CONTENTS

SECTION 1 SYSTEM OVERVIEW

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

1.2 Line Replaceable Units ........................................1-2

1.3 Secure Digital (SD) Cards .................................... 1-7

1.4 System Power-up ..................................................1-8

1.5 System Operation .................................................1-9

Normal Display Operation ..........................................1-9

Reversionary Display Operation ..................................1-9

G1000 System Annunciations ...................................1-10

AHRS Operation ......................................................1-11

1.6 G1000

Controls ...................................................1-12

PFD/MFD Controls ...................................................1-12

Softkey Function ......................................................1-14

1.7 Accessing G1000 Functionality ........................1-19

Menus ....................................................................1-19

Data Entry ..............................................................1-19

Page Groups ...........................................................1-20

System Setup and Status ..........................................1-24

Electronic Checklists (Optional) .................................1-33

1.8 Display Backlighting .......................................... 1-35

SECTION 2 FLIGHT INSTRUMENTS

2.1 Introduction ..........................................................2-1

2.2 Flight Instruments ................................................ 2-4

Airspeed Indicator .....................................................2-4

Attitude Indicator ......................................................2-6

Altimeter ..................................................................2-7

Vertical Deviation/Glideslope Indicator ........................ 2-9

Vertical Speed Indicator (VSI) ......................................2-9

Horizontal Situation Indicator (HSI) ...........................2-10

2.3 Supplemental Flight Data .................................2-18

Timer/References Window ........................................2-18

Outside Air Temperature ...........................................2-19

System Time ............................................................ 2-20

2.4 PFD Annunciations and Alerting Functions .....

Softkey Annunciations ..............................................2-21

Alerts Window .........................................................2-22

Annunciation Window ..............................................2-22

Altitude Alerting ......................................................2-23

Marker Beacon Annunciations .................................. 2-23

Trafﬁc Annunciation .................................................2-24

2-21

TAWS Annunciations ................................................2-24

Barometric Minimum Descent Altitude .......................2-25

SECTION 3 ENGINE INDICATION SYSTEM (EIS)

3.1 Introduction ..........................................................3-1

3.2 Engine Display ......................................................3-2

3.3 Lean Display ..........................................................3-4

3.4 System Display .....................................................3-6

SECTION 4 AUDIO PANEL AND CNS

4.1 Overview ...............................................................4-1

PFD/MFD Controls and Frequency Display .................... 4-2

Audio Panel Controls .................................................4-4

4.2 COM Operation .....................................................4-6

COM Transceiver Selection and Activation ....................4-6

Stuck Microphone ......................................................4-7

COM Transceiver Manual Tuning .................................4-8

COM Tuning Failure ....................................................4-8

Quick-Tuning and Activating 121.500 MHz ...................4-9

Auto-Tuning the COM Frequency ...............................4-10

Frequency Spacing ...................................................4-14

Automatic Squelch ................................................... 4-15

4.3 NAV Operation ....................................................4-16

NAV Radio Selection and Activation ..........................4-16

NAV Receiver Manual Tuning ....................................4-17

Auto-Tuning the NAV Frequency ................................4-19

Marker Beacon Receiver ...........................................4-24

DME Tuning (Optional) .............................................4-25

4.4 GTX 33 Mode S Transponder .............................4-26

Transponder Softkey Controls ...................................4-26

Transponder Mode Selection .....................................4-27

Flight ID Reporting ..................................................4-31

4.5 Additional Audio Panel Functions ....................4-32

Power-Up and Fail-safe Operation .............................4-32

Mono/Stereo Headsets .............................................4-32

Speaker ..................................................................4-32

Intercom ................................................................. 4-33

Passenger Address (PA) System .................................4-34

Clearance Recorder and Player ..................................4-35

Split COM ...............................................................4-35

Entertainment Inputs ...............................................4-36

Reversionary Mode .................................................. 4-37

190-00595-00 Rev. A

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

Page 8

TABLE OF CONTENTS

4.6 Preﬂight Procedure for the GMA 1347 ............4-38

SECTION 5 GPS NAVIGATION

5.1 Introduction ..........................................................5-1

5.2 Navigation Map (MFD) ........................................5-2

Navigation Map Page .................................................5-2

5.3 PFD Inset Map and Windows ............................5-24

Inset Map ...............................................................5-24

PFD Windows ..........................................................5-25

5.4 Direct-to-Navigation (MFD) ............................. 5-27

Selecting a Direct-to Waypoint ..................................5-27

Direct-to Navigation Shortcuts using the FMS Knob ....5-32

5.5 Direct-to-Navigation (PFD) ..............................5-34

Operations .............................................................. 5-34

5.6 Airport Information (MFD) ................................

5-37

5.7 Intersection Information (MFD) ........................5-42

5.8 NDB Information (MFD) .....................................5-43

5.9 VOR Information (MFD) .....................................5-44

5.10 User Waypoint Information (MFD) ...................5-45

5.11 Nearest Airports (MFD) .....................................5-49

5.12 Nearest Intersections (MFD) .............................5-52

5.13 Nearest NDB (MFD) ............................................5-53

5.14 Nearest VOR (MFD) ............................................5-54

5.15 Nearest User Waypoint (MFD) ..........................5-56

5.16 Nearest Frequencies (MFD) ...............................5-58

5.17 Nearest Airspaces (MFD) ...................................5-61

5.18 Nearest Airports (PFD) .......................................5-65

Operations .............................................................. 5-65

5.19 Flight Planning (MFD) .......................................5-67

Flight Planning Operations .......................................5-67

Vertical Navigation ..................................................5-76

light Planning (PFD) ........................................5-79

5.20 F

Operations .............................................................. 5-79

5.21 Procedures

Departures, Arrivals, and Approaches ......................... 5-83

5.22 Procedures

Operations .............................................................. 5-91

(MFD) ............................................... 5-83

(PFD) ................................................ 5-91

SECTION 6 HAZARD AVOIDANCE

6.1 XM WX Satellite Weather ....................................6-1

Activating XM Weather and Radio Services ..................6-1

Using XM WX Satellite Weather Products ..................... 6-3

Weather Softkeys on the Weather Data Link Page ......... 6-5

Setting Up the Weather Data Link Page .....................6-23

Setting Up XM Weather on the Navigation Map .........6-27

6.2 Stormscope (WX-500) ..........................................6-29

Setting Up Stormscope on the Navigation Map ..........6-29

Selecting the Stormscope Page .................................6-33

6.3 Terrain Proximity .................................................... 6-36

Requirements ..........................................................6-36

GPS Position and GPS-MSL Altitude ...........................6-36

Displaying Terrain Proximity Data ..............................6-37

Terrain Proximity Page ..............................................6-39

Navigation Map Page ...............................................6-41

6.4 TAWS

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

6.6 L-3 SKYWATCH

......................................................................6-43

Requirements ..........................................................6-43

TAWS Alerting Using GPS Position/GPS MSL Altitude ...6-43

Using TAWS ............................................................6-44

TAWS Symbols ........................................................6-48

TAWS Alerts ............................................................6-48

6-55

TIS Symbology .........................................................6-55

TIS Power-Up Test ................................................... 6-59

Operating Modes .....................................................6-60

(SKY497) ..................................6-62

User-Initiated Test ....................................................6-62

SKYWATCH TAS Symbology ......................................6-63

SECTION 7 AUTOMATIC FLIGHT CONTROL SYSTEM

7.1 AFCS Overview .....................................................7-1

AFCS Controls on the MFD .........................................7-2

Additional AFCS Controls ...........................................7-3

7.2 Flight Director Operation .................................... 7-4

Activating the Flight Director ......................................7-4

Command Bars ..........................................................7-4

AFCS Status Box ........................................................ 7-5

7.3 Flight Director Modes ..........................................7-6

Pitch Modes .............................................................. 7-7

Roll Modes .............................................................. 7-14

7.4 Autopilot Operation ........................................... 7-19

Flight Control ..........................................................7-19

Engaging the Autopilot and Yaw Damper ...................7-20

Control Wheel Steering ............................................7-20

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

190-00595-00 Rev. Avi

Page 9

Disengaging the Autopilot and Yaw Damper ...............7-21

7.5 Example Procedures ...........................................7-22

7.6 AFCS Annunciations and Alerts ........................7-30

AFCS Status Alerts ................................................... 7-30

Overspeed Protection ...............................................7-31

SECTION 8 ADDITIONAL FEATURES

8.1 GDL 69A Data Link Receiver – XM Digital Audio

Entertainment (Optional) .............................................. 8-1

XM Satellite Radio Service ..........................................8-1

XM Information Page .................................................8-2

XM Radio Page ..........................................................8-3

APPENDICES

Annunciations and Alerts ..............................................A-1

Alert Level Deﬁnitions ................................................A-2

A36/G36 Aircraft Annunciations & Alerts ......................A-3

AFCS Alerts ...............................................................A-5

TAWS ALERTS ............................................................A-6

TAWS System Status Annunciations .............................A-7

Trafﬁc Voice Alerts .....................................................A-7

G1000 System Annunciations .....................................A-7

G1000 System Alert Messages ..................................A-10

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

B-1

TABLE OF CONTENTS

Glossary ...........................................................................C-1

Frequently Asked Questions .........................................D-1

G1000 Map Datums ....................................................... E-1

General TIS Information ................................................ F-1

Map Symbols ................................................................. G-1

INDEX

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

190-00595-00 Rev. A

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

vii

Page 10

TABLE OF CONTENTS

BLANK PAGE

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

190-00595-00 Rev. Aviii

Page 11

SECTION 1 SYSTEM OVERVIEW

1.1 SYSTEM DESCRIPTION

SYSTEM OVERVIEW

NOTE:

The G1000 is an integrated ﬂight deck system that presents ﬂight instrumentation, position, navigation, communication, and identiﬁcation information to the pilot using ﬂat-panel color displays. The system consists of the following Line Replaceable Units (LRUs):

•

GDU 1040

•

GDU 1042

•

GMA 1347

Beacon Receiver

•

GIA 63

•

GDC 74

•

GEA 71

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

The Beechcraft A36/G36 is equipped with a GFC 700 Automated Flight Control System (AFCS), providing ﬂight director (FD), autopilot (AP), and manual electric trim (MET) operation.

Refer to Section 7 for a description of the GFC 700 AFCS.

Primary Flight Display (PFD)

Multi Function Display (MFD)

Audio Panel with Integrated Marker

Integrated Avionics Units (IAU)

Air Data Computer (ADC)

Engine/Airframe Unit

•

GTX 33

•

GRS 77

(AHRS)

•

GMU 44

•

GDL 69/69A

•

GSA 81

•

GSM 85

Mode S Transponder

Attitude and Heading Reference System

Magnetometer

Data Link Receiver

AFCS Servos

Servo Mounts

190-00595-00 Rev. A

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

1-1

Page 12

SYSTEM OVERVIEW

1.2 LINE REPLACEABLE UNITS

• GDU 1040/1042 (2) – A GDU 1040 is conﬁgured as the Primary Flight Display (PFD) and a GDU 1040 or 1042 (for airframes equipped with the GFC 700) as a Multi Function Display (MFD). Both displays feature

10.4-inch LCD screens with 1024 x 768 resolution. The displays communicate with each other through a High-speed Data Bus (HSDB) Ethernet connection. Each display is also paired with an Ethernet connection to an IAU.

•

GMA 1347

and marker beacon controls, and is installed between the displays. This unit also provides manual control of display Reversionary Mode (red with both IAUs using an RS-232 digital interface.

•

GIA 63

with the PFD. Each IAU contains very high frequency (VHF) communication/navigation/glideslope (COM/ NAV/GS) receivers and system integration microprocessors and is paired with the on-side display via an HSDB connection. The IAUs are not paired together and do not communicate with each other directly.

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

DISPLAY BACKUP

(2) – The Integrated Avionics Units (IAU) function as the main communications hub, linking all LRUs

button; see Section 1.5, System Operation) and communicates

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

190-00595-00 Rev. A1-2

Page 13

SYSTEM OVERVIEW

GDC 74

(OAT) sensor. The ADC provides pressure altitude, airspeed, vertical speed, and OAT information to the G1000 System, and it communicates with the primary IAU, displays, and AHRS using an ARINC 429 digital interface.

•

GEA 71

unit communicates with both IAUs using an RS-485 digital interface.

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

– The Engine Airframe Unit receives and processes signals from the engine and airframe sensors. This

•

GTX 33

through an RS-232 digital interface.

•

GRS 77

information via ARINC 429 to both the PFD and the primary IAU. The AHRS contains advanced sensors (including accelerometers and rate sensors) and interfaces with the Magnetometer to obtain magnetic ﬁeld information, with the ADC to obtain air data, and with both IAUs to obtain GPS information. AHRS operation is discussed in Section 1.5, System Operation.

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

(2) – The Attitude and Heading Reference System (AHRS) provides aircraft attitude and heading

190-00595-00 Rev. A

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

1-3

Page 14

SYSTEM OVERVIEW

•

GMU 44

determine aircraft magnetic heading. This unit receives power directly from the AHRS and communicates with it via an RS-485 digital interface.

•

GDL 69A

PFD Inset Map, as well as digital audio entertainment. The Data Link Receiver communicates with the MFD via an HSDB connection. A subscription to XM Satellite Radio Service is required to enable Data Link Receiver capability.

– The Magnetometer measures local magnetic ﬁeld and sends data to the AHRS for processing to

– The Data Link Satellite Radio Receiver provides real-time weather information to MFD maps and the

•

GSA 81

units interface with each IAU.

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

mechanical ﬂight-control surface linkages.

and

GSM 85

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

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

190-00595-00 Rev. A1-4

Page 15























































































































SYSTEM OVERVIEW

190-00595-00 Rev. A

Figure 1-1 Basic G1000 System Block Diagram

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

1-5

Page 16

SYSTEM OVERVIEW









































Figure 1-2 G1000 System Block Diagram With Options

NOTE:

For information on additional equipment shown in Figure 1-2, consult the applicable optional interface user’s guide. This document assumes that the reader is already familiar with the operation of this additional equipment.

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

190-00595-00 Rev. A1-6

Page 17

SYSTEM OVERVIEW

1.3 SECURE DIGITAL (SD) CARDS

NOTE:

Ensure the G1000 System is powered off before inserting an SD card.

NOTE:

Refer to Appendix B for instructions on updating the aviation database.

The PFD and MFD data card slots use Secure Digital (SD) cards and are located on the upper right side of the

display bezels. Each display bezel is equipped with two SD card slots. SD cards are used for aviation database and system software updates as well as terrain database storage.

Installing an SD card:

1) Insert the SD card in the SD card slot (the front of the card should be ﬂush with the face of the display bezel).

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

SD Card Slots

Figure 1-3 Display Bezel SD Card Slots

190-00595-00 Rev. A

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

1-7

Page 18

SYSTEM OVERVIEW

1.4 SYSTEM POWER-UP

NOTE:

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

and emergency power supply operation.

NOTE:

The G1000 System is integrated with the aircraft electrical system and receives power directly from electrical busses. The PFD, MFD, and supporting sub-systems include both power-on and continuous built-in test features that exercise the processor, RAM, ROM, external inputs, and outputs to provide safe operation.

During system initialization, test annunciations are displayed, as shown in Figure 1-4. All system annunciations should disappear typically within the ﬁrst minute of power-up. Upon power-up, key annunciator lights also become momentarily illuminated on the Audio Panel and the display bezels.

On the PFD, the AHRS begins to initialize and displays “AHRS ALIGN: Keep Wings Level”. The AHRS should display valid attitude and heading ﬁelds typically within the ﬁrst minute of power-up. The AHRS can align itself both while taxiing and during level ﬂight.

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

• System version

• Copyright

• Land database name and version

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

• Obstacle database name and version

• Terrain database name and version

• Aviation database name, version, and effective dates

Current database information includes valid operating dates, cycle number, and database type. When this information has been reviewed for currency (to ensure that no databases have expired), the pilot is prompted to continue.

Pressing the displayed upon pressing the key a second time. When the system has acquired a sufﬁcient number of satellites to determine a position, the aircraft’s current position is shown on the Navigation Map Page.

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

Figure 1-4 PFD Initialization Figure 1-5 MFD Power-Up Splash Screen

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

190-00595-00 Rev. A1-8

Page 19

SYSTEM OVERVIEW

1.5 SYSTEM OPERATION

The displays are connected together via a single Ethernet bus for high-speed communication. As shown in Figure 1-1, each IAU is connected to the on-side display. Normal and reversionary G1000 display operation, as well as the various AHRS modes and G1000 System Annunciations are discussed here.

NORMAL DISPLAY OPERATION

In normal operating mode, the PFD presents graphical ﬂight instrumentation (attitude, heading, airspeed, altitude, vertical speed), replacing the traditional ﬂight instrument cluster (see the Flight Instruments Section for more information). The MFD normally displays a full-color moving map with navigation information (see the GPS Navigation Section), while the left portion of the MFD is dedicated to the Engine Indication System (EIS; see the EIS Section). Both displays offer control for COM and NAV frequency selection.

Figure 1-6 G1000 Normal Operation

REVERSIONARY DISPLAY OPERATION

NOTE:

In the event of a display failure, the G1000 System automatically switches to reversionary (backup) mode. In Reversionary Mode, all important ﬂight information is presented on the remaining display in the same format as in normal operating mode.

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

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

for further information regarding system-speciﬁc alerts.

NOTE:

In normal operating mode, backlighting can only be adjusted from the PFD. In Reversionary Mode, it

can be adjusted from the remaining display.

190-00595-00 Rev. A

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

1-9

Page 20

SYSTEM OVERVIEW

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

Audio Panel’s red

DISPLAY BACKUP

button. Pressing this button again deactivates Reversionary Mode.

NAV1 and COM1 (provided by the failed PFD) are ﬂagged as invalid.

Pressing the activates/deactivates Reversionary Mode.

DISPLAY BACKUP

Button also

Figure 1-7 G1000 Reversionary Mode (Failed PFD)

G1000 SYSTEM ANNUNCIATIONS

When an LRU or an LRU function fails, a large red ‘X’ is typically displayed over the instrument experiencing failed data (Figure 1-8 displays all possible ﬂags and responsible LRUs). For a detailed description of all annunciations and alerts, refer to Appendix A. Refer to the Aircraft Flight Manual (AFM) for additional information regarding pilot responses to these annunciations.

Upon G1000 power-up, certain instruments remain invalid as equipment begins to initialize. All instruments should be operational within one minute of power-up. If any instrument remains ﬂagged, the G1000 should be serviced by a Garmin-authorized repair facility.

GIA 63

GRS 77 or GMU 44

GEA 71

GIA 63

GDC 74

Figure 1-8 G1000 System Failure Annunciations

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

GDC 74

GIA 63

GTX 33 or GIA 63

GIA 63

190-00595-00 Rev. A1-10

Page 21

AHRS OPERATION

Attitude/Heading Invalid

AHRS

no-GPS

Mode

AHRS Normal

Operation

AHRS no-

Mag Mode

AHRS no-Mag/

no-Air Mode

Heading Invalid











Airspeed Data

Magnetometer





GPS

SYSTEM OVERVIEW

NOTE:

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

The Attitude and Heading Reference System (AHRS) performs attitude, heading, and vertical acceleration calculations for the G1000 System, utilizing GPS, magnetometer, and air data in addition to information from its internal sensors. Attitude and heading information are updated on the PFD while the AHRS receives appropriate combinations of information from the external sensor inputs.

Loss of GPS, magnetometer, or air data inputs is communicated to the pilot by message advisory alerts (refer to Appendix A for speciﬁc AHRS alert information). Any failure of the internal AHRS inertial sensors results in loss of attitude and heading information (indicated by red ‘X’ ﬂags over the corresponding ﬂight instruments).

GPS INPUT FAILURE

Two GPS inputs are provided to the AHRS. If GPS information from one of the inputs fails, the AHRS uses the remaining GPS input and an alert message is issued to inform the pilot. If both GPS inputs fail, the AHRS can continue to provide attitude and heading information to the PFD as long as magnetometer and airspeed data are available and valid.

MAGNETOMETER FAILURE

If the magnetometer input fails, the AHRS continues to output valid attitude information; however, the heading output on the PFD is ﬂagged as invalid with a red ‘X’.

AIR DATA INPUT FAILURE

Failure of the air data input has no effect on the AHRS output while AHRS is receiving valid GPS information. Invalid/unavailable airspeed data in addition to GPS failure results in loss of all attitude and heading information.

Figure 1-9 AHRS Operation

190-00595-00 Rev. A

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

1-11

Page 22

SYSTEM OVERVIEW

1.6 G1000 CONTROLS

The G1000 controls have been designed to simplify operation of the system and minimize workload and the time required to access sophisticated functionality. Controls are located on the PFD and MFD bezels and Audio Panel. PFD and MFD controls and softkeys are discussed in this section. See the Audio Panel and CNS Section for more information about Audio Panel and NAV/COM controls. AFCS controls (on the bezel of the MFD) are described in the AFCS section.

PFD/MFD CONTROLS

Figure 1-10 PFD/MFD Controls

NAV VOL/ID Knob

NAV Frequency Transfer Key

NAV Knob

Heading Knob

Joystick

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

percentage)

Press to toggle Morse code identiﬁer audio on/off

Transfers the standby and active NAV frequencies

Turn to tune NAV receiver standby frequencies (large knob for MHz; small for kHz)

Press to toggle light blue tuning box between NAV1 and NAV2

Turn to manually select a heading

Press to display a digital heading momentarily to the left of the Horizontal Situation

Indicator (HSI) and synchronize the Selected Heading to the and current heading

Turn to change map range

Press to activate Map Pointer and move in desired direction to pan map

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

190-00595-00 Rev. A1-12

Page 23

SYSTEM OVERVIEW

CRS/BARO Knob

COM Knob

COM Frequency Transfer Key (EMERG)

COM VOL/SQ Knob

Direct-to Key ( )

FPL Key

Turn large knob for altimeter barometric pressure setting

Turn small knob to adjust course (only when HSI is in VOR or OBS Mode)

Press to re-center the CDI and return course pointer directly TO bearing of active

waypoint/station

Turn to tune COM transceiver standby frequencies (large knob for MHz; small for

kHz)

Press to toggle light blue tuning box between COM1 and COM2

The selected COM (green) is controlled with the

COM MIC Key (Audio Panel).

Transfers the standby and active COM frequencies

Press and hold two seconds to tune the emergency frequency (121.5 MHz)

automatically into the active frequency ﬁeld

Turn to control COM audio volume level (shown as a percentage in the COM

Frequency Box)

Press to turn the COM automatic squelch on/off

Activates the direct-to function and allows the user to enter a destination waypoint

and establish a direct course to the selected destination (speciﬁed by identiﬁer, chosen from the active route)

Displays ﬂight plan information

CLR Key (DFLT MAP)

MENU Key

PROC Key

ENT Key

FMS Knob

(Flight Management System Knob)

Softkey Selection Keys

ALT Knob

Erases information, cancels entries, or removes menus

Press and hold to display the MFD Navigation Map Page (MFD only).

Displays a context-sensitive list of options for accessing additional features or making

setting changes

Gives access to IFR departure procedures (DPs), arrival procedures (STARs), and

approach procedures (IAPs) for a ﬂight plan or selected airport

Validates/conﬁrms selection or data entry

Press to turn the selection cursor on/off

Data Entry: With cursor on, turn to enter data in the highlighted ﬁeld (large

knob moves cursor location; small knob selects character for highlighted cursor location)

Scrolling: When a list of information is too long for the window/box, a scroll bar

appears, indicating more items to view. With cursor on, turn large knob to scroll through the list.

Page Selection: Turn knob on MFD to select the page to view (large knob selects a

page group; small knob selects a speciﬁc page from the group)

Press to select softkey shown above the bezel key on the PFD/MFD display

Sets the Selected Altitude, shown above the Altimeter (the large knob selects the

thousands, the small knob selects the hundreds)

190-00595-00 Rev. A

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

1-13

Page 24

SYSTEM OVERVIEW

INSET

XPDR

IDENT

TMR/REF

NRST

ALERTS

OBS

PFD

CDI

ADF/DME

(optional)

Press the CDI Softkey to cycle through navigation sources:

- GPS

- NAV1 (VOR/LOC)

- NAV2 (VOR/LOC)

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

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

Large (Outer)

Knob

Small (Inner)

Knob

Figure 1-11 Dual Concentric Knob

SOFTKEY FUNCTION

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

In the following descriptions, top level softkeys are denoted with bullets.

Softkey

Bezel-Mounted Softkeys (Press)

Figure 1-12 Softkeys (Second-Level PFD Conﬁguration)

Softkey Selection

Box (Light Blue)

PFD SOFTKEYS

The

CDI, IDENT, TMR/REF, NRST,

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

The PFD softkeys provide control over ﬂight management functions, including GPS, NAV, terrain, trafﬁc, and lightning (optional). Each softkey sublevel has a previous level. The ALERTS Softkey is visible at all softkey levels (label changes if messages are issued).

and

ALERTS

softkeys undergo a momentary change to black text on

BACK Softkey which can be selected to return to the

Softkey Names

(Displayed)

Figure 1-13 Top-level PFD Softkeys

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

190-00595-00 Rev. A1-14

Page 25

SYSTEM OVERVIEW

BACK

Press the OFF or BACK Softkey to return to the top-level softkeys.

DCLTR

DCLTR-2

DCLTR-3

DCLTR-1

TOPO

ALERTS

NEXRAD

(optional)

TERRAIN

XM LTNG

(optional)

OFF

TRAFFIC

INSET

XPDR

IDENT

TMR/REF

NRST

ALERTS

OBS

PFD

CDI

ADF/DME

(optional)

Press the CDI Softkey to cycle through navigation sources:

- GPS

- NAV1 (VOR/LOC)

- NAV2 (VOR/LOC)

• INSET OFF DCLTR (3)

TRAFFIC TOPO TERRAIN NEXRAD XM LTNG

Displays Inset Map in PFD lower left corner Removes Inset Map Selects desired amount of map detail; cycles through declutter levels: DCLTR (No Declutter): All map features visible DCLTR-1: Removes land data DCLTR-2: Removes land and SUA data DCLTR-3: Removes everything except active ﬂight plan Displays/removes trafﬁc information on Inset Map Displays/removes topographical data (e.g., coastlines, terrain, rivers, lakes) on Inset Map Displays/removes terrain information on Inset Map Displays/removes NEXRAD weather and coverage information on Inset Map ( Displays/removes XM lightning information on Inset Map (

optional)

• PFD METRIC

DFLTS DME BRG1

360 HSI ARC HSI

190-00595-00 Rev. A

Figure 1-14 INSET Softkeys

Displays second-level softkeys for additional PFD conﬁguration Displays Selected and current altitudes additionally in meters and changes barometric

setting to hectopascals (hPa) from inches of mercury (in Hg) Resets PFD to default settings, including changing units to standard Displays/removes DME Information Window (

optional) Cycles the Bearing 1 Information Window through: NAV1: Waypoint frequency/identiﬁer and DME information GPS: Waypoint identiﬁer and GPS distance information ADF: Waypoint frequency Off: Removes window Displays the HSI as a 360° compass rose Displays the HSI as a 140° viewable arc (Bearing Information Windows unavailable)

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

1-15

Page 26

SYSTEM OVERVIEW

BACK

Press the OFF or BACK Softkey to return to the top-level softkeys.

DCLTR

DCLTR-2

DCLTR-3

DCLTR-1

TOPO

ALERTS

NEXRAD

(optional)

TERRAIN

XM LTNG

(optional)

OFF

TRAFFIC

INSET

XPDR

IDENT

TMR/REF

NRST

ALERTS

OBS

PFD

CDI

ADF/DME

(optional)

Press the CDI Softkey to cycle through navigation sources:

- GPS

- NAV1 (VOR/LOC)

- NAV2 (VOR/LOC)

ARC HSI

STD BARO

BACK

ALERTS

METRIC

DFLTS

360

HSI

PFD

BRG

DME

(optional)

Press the BRG1/BRG2 softkeys to display/ remove the Bearing Information windows and cycle through bearing sources:

- NAV1/NAV2

- GPS

- ADF

Press the STD BARO or BACK Softkey to return to the top-level softkeys.

BRG2

Cycles the Bearing 2 Information Window through: NAV2: Waypoint frequency/identiﬁer and DME information GPS: Waypoint identiﬁer and GPS distance information ADF: Waypoint frequency Off: Removes window

STD BARO Sets barometric pressure to 29.92 in Hg (1013 hPa if METRIC Softkey is selected)

• OBS

• CDI

Selects OBS Mode on the CDI when navigating by GPS (only available with active leg) Cycles CDI through GPS, NAV1 (VOR/LOC), and NAV2 (VOR/LOC) navigation sources

• ADF/DME Displays/removes ADF/DME Radio Tuning Window (optional; may appear as ADF, DME, or ADF/DME depending on installation)

• XPDR

STBY ON ALT

VFR CODE

0 — 7 BKSP

• IDENT

• TMR/REF

• NRST

• ALERTS

Figure 1-15 PFD Conﬁguration Softkeys

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

interrogations)

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

transponder return on the ATC screen

Displays/removes Timer/References Window Displays/removes Nearest Airports Window Displays/removes Alerts Window

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

190-00595-00 Rev. A1-16

Page 27

BACK

Press the OFF or BACK Softkey to return to the top-level softkeys.

DCLTR

DCLTR-2

DCLTR-3

DCLTR-1

TOPO

ALERTS

NEXRAD

(optional)

TERRAIN

XM LTNG

(optional)

OFF

TRAFFIC

INSET

XPDR

IDENT

TMR/REF

NRST

ALERTS

OBS

PFD

CDI

ADF/DME

(optional)

Press the CDI Softkey to cycle through navigation sources:

- GPS

- NAV1 (VOR/LOC)

- NAV2 (VOR/LOC)

ARC HSI

STD BARO

BACK

ALERTS

METRIC

DFLTS

360

HSI

PFD

BRG

DME

(optional)

Press the BRG1/BRG2 softkeys to display/ remove the Bearing Information windows and cycle through bearing sources:

- NAV1/NAV2

- GPS

- ADF

Press the STD BARO or BACK Softkey to return to the top-level softkeys.

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

Press the IDENT or BACK Softkey to return to the top-level softkeys.

XPDR

STBY

ALT

VFR

IDENT

BACK

ALERTS

CODE

IDENT

BACK

ALERTS

BKSP

MAP

ENGINE

CHKLIST

DCLTR

DCLTR-2

DCLTR-3

DCLTR-1

MFD SOFTKEYS

Figure 1-16 XPDR Softkeys

SYSTEM OVERVIEW

MFD softkeys vary depending on the page selected. EIS and Navigation Map Page (default MFD page)

softkeys are described here.

• ENGINE

LEAN SYSTEM

• MAP TRAFFIC TOPO

TERRAIN NEXRAD

XM LTNG BACK

Figure 1-17 Navigation Map Page Softkeys

Displays second-level engine softkeys (Figure 1-18; see the EIS Section for more

information) Displays the EIS Lean Display (softkeys for engine leaning assist are shown when selected) Displays the EIS System Display (softkeys for fuel calculations are shown when selected) Enables second-level Navigation Map Page softkeys Displays/removes trafﬁc information on Navigation Map Page Displays/removes topographical data (e.g., coastlines, terrain, rivers, lakes) on Navigation

Map Page Displays/removes terrain information on Navigation Map Page Displays/removes NEXRAD weather and coverage information on Navigation Map Page

(optional) Displays/removes XM lightning information on Navigation Map Page (optional) Returns to top-level softkeys

190-00595-00 Rev. A

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

1-17

Page 28

SYSTEM OVERVIEW

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

ENGINE

SYSTEM

ENGINE

LEAN

INC FUEL

RST FUEL

DEC FUEL

BACK

SYSTEM

ENGINE

LEAN

BACK

MAP

ENGINE

CHKLIST

DCLTR

DCLTR-2

DCLTR-3

DCLTR-1

ASSIST

CYL SLCT

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

ENGINE

SYSTEM

ENGINE

LEAN

INC FUEL

RST FUEL

DEC FUEL

BACK

SYSTEM

ENGINE

LEAN

BACK

(optional)

NEXRAD

TERRAIN

(optional)

XM LTNG

TOPO

MAP

TRAFFIC

MAP

ENGINE

CHKLIST

DCLTR

DCLTR-2

DCLTR-3

DCLTR-1

ASSIST

CYL SLCT

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

ENGINE

SYSTEM

ENGINE

LEAN

INC FUEL

RST FUEL

DEC FUEL

BACK

SYSTEM

ENGINE

LEAN

BACK

(optional)

NEXRAD

TERRAIN

(optional)

XM LTNG

TOPO

MAP

TRAFFIC

MAP

ENGINE

CHKLIST

The DONE Softkey label changes to UNDO when the checklist item is already checked.

EXIT

DONE

ENGINE

CHKLIST

EMERGCY

CHKLIST

DCLTR

DCLTR-2

DCLTR-3

DCLTR-1

ASSIST

CYL SLCT

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

• DCLTR (3)

Selects desired amount of map detail; cycles through declutter levels: DCLTR (No Declutter): All map features visible DCLTR-1: Removes land data DCLTR-2: Removes land and SUA data DCLTR-3: Removes everything except the active ﬂight plan

• CHKLIST Displays the Checklist Page; press the EXIT Softkey to return to the top-level softkeys

Figure 1-18 ENGINE Softkeys

Figure 1-19 MAP Softkeys

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

Figure 1-20 Checklist Softkeys

190-00595-00 Rev. A1-18

Page 29

1.7 ACCESSING G1000 FUNCTIONALITY

MENUS

SYSTEM OVERVIEW

NOTE:

No other window can be displayed on the PFD while the PFD Setup Menu is displayed. Pressing the

MENU Key while any other PFD window is displayed does not display the PFD Setup Menu.

The G1000 has a dedicated 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 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 additional features or settings for the window/page selected.

Navigating a menu:

1) Press the MENU Key to display the menu.

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

window/box when the option list is longer than the window/box).

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

4) Press the CLR Key or FMS Knob to remove the menu and cancel the operation.

No Options for

NRST Window

Options for FPL Window

DATA ENTRY

The FMS Knob can be used for directly entering alphanumeric data (e.g., Flight ID, waypoint identiﬁers, barometric minimum descent altitude) into the G1000 In some instances, such as when entering an identiﬁer, the G1000 will try to predict the desired identiﬁer based on the characters being entered. In this case, if the desired identiﬁer appears, use the ENT Key to conﬁrm the entry without entering the rest of the identiﬁer manually. This can save the pilot from having to enter all the characters of the identiﬁer.

Using the FMS Knob to enter data:

1) If needed, press the FMS Knob to activate the cursor.

2) Use the large FMS Knob to highlight the desired ﬁeld.

3) Begin entering data by turning the small FMS Knob to select a character for the ﬁrst placeholder.

190-00595-00 Rev. A

Figure 1-21 Page Menu Examples

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

1-19

Page 30

SYSTEM OVERVIEW

Turning the knob to the right scrolls through the alphabet (where appropriate) toward the letter Z, starting in

the middle at K, and the digits zero through nine. Turning the knob to the left scrolls in the opposite direction.

4) Use the large FMS Knob to move the cursor to the next placeholder in the ﬁeld.

5) Repeat, using the small FMS Knob to select a character and the large FMS Knob to move the cursor, until the

ﬁeld is complete.

6) Press the ENT Key to conﬁrm entry.

7) Press the FMS Knob or CLR Key to cancel data entry (the ﬁeld reverts back to its previous information).

PAGE GROUPS

NOTE:

Refer to other supporting sections in this Pilot’s Guide for details on speciﬁc pages.

Information on the MFD is presented on pages which are grouped according to function. The page group and active page title are displayed in the upper center of the screen in light blue. 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 by icons. For some of these pages (Airport/Procedure/Weather Information, XM, Procedure Loading), the title of the page changes while the page icon remains the same.

Page Group Active Page Title

Page Groups

MFD

Figure 1-22 Page Title and Page Group Icons

Pages in Current Group

Selected Page

There are four main page groups, navigated using the FMS Knob; 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

the

large FMS

small FMS

Knob until the desired page group is selected.

Knob until the desired page is selected.

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

190-00595-00 Rev. A1-20

Page 31

• Map Page Group (MAP)

Navigation Map

Trafﬁc Map

SYSTEM OVERVIEW

Weather Data Link (

optional)

Terrain Proximity

• Waypoint Page Group (WPT)

Airport/Procedures/Weather Information Pages

- Airport Information (INFO Softkey)

- Departure Information (DP Softkey)

Figure 1-23 Map Pages

- Arrival Information (STAR Softkey)

- Approach Information (APR Softkey)

- Weather Information (

optional)

(WX Softkey)

Intersection Information

NDB Information

VOR Information

User Waypoint Information

Airport/Procedures/

Weather Information

Pages

Figure 1-24 Waypoint Pages

190-00595-00 Rev. A

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

1-21

Page 32

SYSTEM OVERVIEW

• Auxiliary Page Group (AUX)

Trip Planning

Utility

GPS Status

System Setup

XM Satellite screens (

- XM Information

optional)

(INFO Softkey)

- XM Radio (RADIO Softkey)

System Status

• Nearest Page Group (NRST)

Nearest Airports

Nearest Intersections

Nearest NDB

Nearest VOR

Pages

Figure 1-25 Auxiliary Pages

Nearest User Waypoints

Nearest Frequencies

Nearest Airspaces

Figure 1-26 Nearest Pages

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

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

190-00595-00 Rev. A1-22

Page 33

SYSTEM OVERVIEW

In addition to the main page groups accessed exclusively using the FMS Knob, there are pages for ﬂight planning (FPL) and loading procedures (PROC) which are accessed by key. In some instances, softkeys may be used to access the Procedure Loading pages.

The Flight Plan pages are accessed using the

FPL Key on the MFD. Main pages within this group are selected

by turning the small FMS Knob.

• Flight Plan Page Group (FPL)

Active Flight Plan

Flight Plan Catalog

- Stored Flight Plan (NEW Softkey)

Vertical Navigation

Figure 1-27 Flight Plan Pages

The Procedure Loading pages may be accessed at any time on the MFD by pressing the

PROC Key. A menu is initialized, and when a departure, approach, or arrival is selected, the appropriate Procedure Loading page is opened. These pages can also be accessed from the Active and Stored Flight Plan pages using the LD softkeys. Turning the

FMS Knob does not scroll through the Procedure Loading pages (note the single page icon in the

lower right corner).

• Procedure Loading Page Group (PROC)

Departure Loading

Arrival Loading

Approach Loading

Figure 1-28 Procedure Loading Pages

Information on optional electronic checklist pages is offered later in this section. Checklist pages may be

accessed from any page on the MFD using the

CHKLIST Softkey.

190-00595-00 Rev. A

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

1-23

Page 34

SYSTEM OVERVIEW

SYSTEM SETUP AND STATUS

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

AUX - SYSTEM SETUP PAGE

The System Setup Page allows management of the following system parameters:

• Time display format (local or UTC )

• Displayed measurement units

• Map datum

• Airspace alerts

• Arrival alert

• Audio alert voice

• MFD Data Bar (Navigation Status Box) ﬁelds

• GPS Course Deviation Indicator (CDI) settings

• COM transceiver channel spacing

• Displayed nearest airports

Figure 1-29 System Setup Page

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

190-00595-00 Rev. A1-24

Page 35

SYSTEM OVERVIEW

PILOT PROFILES

System settings conﬁgured on the System Setup Page may be saved under a pilot proﬁle. 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.

Creating a proﬁle:

1) Use the FMS Knob to select the 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) 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.

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

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.

7) Press the ENT Key.

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

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) Use the FMS Knob to select the 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) Use the FMS Knob to select the 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.

6) Press the ENT Key.

190-00595-00 Rev. A

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

1-25

Page 36

SYSTEM OVERVIEW

7) 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) Use the FMS Knob to select the 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.

DATE/TIME

The System Setup page displays the current date and time and allows the pilot to set the time format (local 12-hr, local 24-hr, or UTC) and offset in the box labeled ‘Date/Time’. The time offset is used to deﬁne current local time. Universal Coordinated Time (UTC; also called Greenwich Mean Time (GMT) or Zulu) date and time are calculated directly from the GPS satellites signals and cannot be changed. When using a local time format, designate the offset by adding or subtracting the desired number of hours from UTC.

Setting the system time format:

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

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

3) Turn the large FMS Knob to highlight the time format ﬁeld in the Date/Time Box.

4) Turn the small FMS Knob to select the desired system time format (local 12hr, local 24hr, UTC).

5) Press the ENT Key.

Setting the current time offset:

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

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

3) Turn the large FMS Knob to highlight the time offset ﬁeld in the Date/Time Box.

4) Enter the time offset and press the ENT Key.

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

190-00595-00 Rev. A1-26

Page 37

SYSTEM OVERVIEW

DISPLAY UNITS

The Display Units Box on the System Setup Page allows conﬁguration of the measurement units used for

the following displayed data:

• Navigation angle (auto, true)

• Distance and speed (metric, nautical)

• Altitude and vertical speed (feet, meters)

• Barometric pressure (inches of mercury, hectopascals)

For the navigation angle, if ‘Auto’ is selected, all track, course, and heading information is corrected to the

computed magnetic variation (MAG VAR) shown in the Display Units Box . The ‘True’ setting references all information to true north.

Units of display for the ﬂight instruments are unaffected when the display units for distance, speed,

altitude, and vertical speed are changed. Displayed engine parameter temperatures and pressures also remain unaffected when display units for temperature or pressure are changed. Changing the fuel and fuel ﬂow units affects the display of parameters only on the AUX - Trip Planning Page.

Changing a display units setting:

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

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

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

4) Turn the small FMS Knob to select from a list of measurement units.

• Air temperature (Celsius, Fahrenheit)

• Fuel and fuel ﬂow (gallons, imperial gallons, kilograms, liters, pounds)

• Position (HDDD°MM.MM’, HDDD°MM’SS.S”, MGRS, UTM/UPS)

5) Press the ENT Key when the desired unit is highlighted.

6) To cancel the process without changing the units, press the CLR Key.

MAP DATUM

The Map Datum Box on the System Setup Page allows selection of the map datum to be used by the G1000 from a list of datums available in the current aviation database. The aviation database contains over 100 map datums to adjust position reading to conform to speciﬁc paper charts (see Appendix E for a list of available map datums.). The default datum setting is WSG 84. Per TSO C129a, the WSG 84 map datum should be used in the United States.

For use outside the U.S., select the geodetic datum required by that country. If charts based on another datum are being used, the G1000 should be set to use the same datum. Using a map datum that does not match the paper charts can result in signiﬁcant differences in position information. If paper charts are being used for reference only, the G1000 still provides correct navigation guidance to the waypoints contained in the database, regardless of the datum selected.

Changing the map datum:

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

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

190-00595-00 Rev. A

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

1-27

Page 38

SYSTEM OVERVIEW

3) Turn the large FMS Knob to highlight the datum in the Map Datum Box.

4) Turn the small FMS Knob to display and scroll through the list of available map datums.

5) Press the ENT Key when the desired datum is highlighted.

AIRSPACE ALERTS

The Airspace Alerts Box allows the pilot to turn the controlled/special-use airspace message alerts on or off. This does not affect the alerts listed on the Nearest Airspaces Page or the airspace boundaries depicted on the Navigation Map Page. It simply turns on/off the warning provided when the aircraft is approaching or near an airspace. Alerts for the following airspaces can be turned on/off in the Airspace Alerts Box:

• Class B/TMA

• Class C/TCA

• Class D

An altitude buffer is also provided which “expands” the vertical range above or below an airspace. For example, if the buffer is set at 500 feet, and the aircraft is more than 500 feet above/below an airspace, an alert message will not be generated, but if the aircraft is less than 500 feet above/below an airspace and projected to enter it, the pilot is notiﬁed with an alert message. The default setting for the altitude buffer is 200 feet.

Changing the altitude buffer distance setting:

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

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

3) Turn the large FMS Knob to highlight the altitude buffer ﬁeld in the Airspace Alerts Box.

4) Enter an altitude buffer value and press the ENT Key.

Turning an airspace alert on or off:

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

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

• Restricted

• MOA (Military)

• Other airspaces

3) Turn the large FMS Knob to highlight the desired ﬁeld in the Airspace Alerts Box.

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

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.

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

190-00595-00 Rev. A1-28

Page 39

SYSTEM OVERVIEW

Enabling/disabling an arrival alert:

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

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

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

4) Turn the small FMS Knob to display and highlight the desired voice.

5) Press the ENT Key.

MFD DATA BAR FIELDS

The MFD Data Bar Fields Box on the System Setup Page can be used to change the conﬁguration of the data ﬁelds in the Navigation Status Box on the MFD. By default, the Navigation Status Box is set to display ground speed (GS), distance to next waypoint (DIS), estimated time enroute (ETE), and enroute safe altitude (ESA). The Navigation Status Box on the PFD is not affected.

The following data may be selected for display in the four ﬁelds of the MFD Navigation Status Box.

• Bearing (BRG)

• Distance (DIS)

• Desired Track (DTK)

• Ground Speed (GS)

• Minimum Safe Altitude (MSA)

• Track Angle Error (TKE)

• Enroute Safe Altitude (ESA)

• Estimated Time of Arrival (ETA)

• Estimated Time Enroute (ETE)

190-00595-00 Rev. A

• Track (TRK)

• Vertical Speed Required (VSR)

• Crosstrack Error (XTK)

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

1-29

Page 40

SYSTEM OVERVIEW

Changing the information shown in an MFD Navigation Status Box ﬁeld:

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

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

3) Turn the large FMS Knob to highlight the desired ﬁeld number in the MFD Data Bar Fields Box.

4) Turn the small FMS Knob to highlight the desired selection from the data options list.

5) Press the ENT Key.

GPS CDI

The GPS CDI Box on the System Setup Page allows the pilot to deﬁne the range for the on-screen Course Deviation Indicator (CDI). The range values represent full range deﬂection for the CDI to either side. The default setting is ‘AUTO’. At this setting, leaving the departure airport the CDI range is set to 1.0 nm and gradually ramps up to 5 nm beyond 30 nm from the departure airport. The CDI range is set to 5.0 nautical miles during the enroute phase of ﬂight. Within 30 nm of the destination airport, the CDI range gradually ramps down to 1.0 nm (terminal area). During approach operations, the CDI range ramps down even further to 0.3 nm. This transition normally occurs within 2.0 nm of the ﬁnal approach ﬁx (FAF).

If a lower CDI range setting is selected (i.e., 1.0 or 0.3 nm), the higher range settings are not selected during any phase of ﬂight. For example, if 1.0 nm is selected, the G1000 uses this for enroute and terminal phases and ramps down to 0.3 nm during an approach. Note that the Receiver Autonomous Integrity Monitoring (RAIM) protection limits follow the selected CDI range and corresponding ﬂight phases.

The GPS CDI Box on the System Setup Page displays the following:

• Selected CDI range (AUTO, 5 nm, 1 nm, 0.3 nm)

• Current system CDI range (5 nm, 1 nm, 0.3 nm)

• ILS CDI capture mode setting (AUTO, MANUAL)

Changing the CDI range:

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

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

3) Turn the large FMS Knob to highlight the selected ﬁeld in the GPS CDI Box.

4) Turn the small FMS Knob to highlight the desired selection from the range list.

5) Press the ENT Key.

Changing the ILS CDI capture setting:

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

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

3) Turn the large FMS Knob to highlight the ILS CDI capture ﬁeld in the GPS CDI Box.

4) Turn the small FMS Knob to select the desired mode.

5) Press the ENT Key.

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

190-00595-00 Rev. A1-30

Page 41

SYSTEM OVERVIEW

COM CONFIGURATION

The COM Conﬁguration Box on the System Setup Page allows the pilot to select 8.33 kHz or 25.0 kHz

COM frequency channel spacing.

Changing COM channel spacing:

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

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

3) Turn the large FMS Knob to highlight the channel spacing ﬁeld in the COM Conﬁguration Box.

4) Turn the small FMS Knob to select the desired spacing.

5) Press the ENT Key.

NEAREST AIRPORTS

The Nearest Airports Box on the System Setup Page deﬁnes the minimum runway length and surface type used when determining the nine nearest airports to display on the MFD Nearest Airports Page. A minimum runway length and/or surface type can be entered to prevent airports with small runways or runways that are not of appropriate surface from being displayed. Default settings are 0 feet (or meters) for runway length and “any” for runway surface type.

Selecting nearest airport surface matching criteria (any, hard only, hard/soft, water):

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

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

3) Turn the large FMS Knob to highlight the runway surface ﬁeld in the Nearest Airports Box.

4) Turn the small FMS Knob to select the desired runway option (any, hard only, hard/soft, water).

5) Press the ENT Key.

Selecting nearest airport minimum runway length matching criteria:

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

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

3) Turn the large FMS Knob to highlight the minimum length ﬁeld in the Nearest Airport Box.

4) Enter the minimum runway length (zero to 99,999 feet) and press the ENT Key.

190-00595-00 Rev. A

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

1-31

Page 42

SYSTEM OVERVIEW

AUX - 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 Diamond service center or Garmin-authorized dealer informed.

Figure 1-30 Example System Status Page

The LRU, ARFRM, and DBASE softkeys on the System Status Page select the box (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 cursor can also be placed in the desired box using the System Status Page Menu.

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

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

190-00595-00 Rev. A1-32

Page 43

ELECTRONIC CHECKLISTS (OPTIONAL)

SYSTEM OVERVIEW

NOTE:

The checklists presented in this section are for example only and may not reﬂect checklists actually available for the Beechcraft A36/G36. The information described in this section is not intended to replace the checklist information described in the AFM or the Pilot Safety and Warning Supplements document.

NOTE:

Garmin is not responsible for the content of the checklists. User-deﬁned checklists are created by the aircraft manufacturer. Modiﬁcations or updates to the checklists are coordinated through the aircraft manufacturer. The user cannot edit the checklists.

The MFD is able to display electronic checklists customized for the Beechcraft A36/G36. The G1000 accesses the checklists from an SD card inserted into the bezel slot (see Figure 1-3). Selecting the CHKLIST Softkey allows access to all checklists. Selecting the EXIT Softkey or momentarily holding down the CLR Key exits the Checklist Page and returns to the page last viewed.

If the SD card contains a valid checklist ﬁle, the power-up splash screen displays both the aircraft make and model to which the checklist applies and copyright information. If the SD card contains an invalid checklist ﬁle or no checklist, the Checklist Page displays ‘INVALID CHECKLIST’ or ‘CHECKLIST NOT PRESENT’ and the CHKLIST Softkey is greyed out. Selecting the EMERGCY Softkey accesses the emergency procedures.

190-00595-00 Rev. A

Figure 1-31 Checklist Page Example

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

1-33

Page 44

SYSTEM OVERVIEW

The Checklist Page displays the following:

• Selected procedure group (number of procedure groups depends on airframe)

• Selected checklist title

Navigating a checklist:

1) From any page, select the CHKLIST Softkey.

2) Turn the large FMS Knob to select the ‘GROUP’ ﬁeld.

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

4) Press the ENT Key.

5) Turn the large FMS Knob to select the ‘Checklist’ ﬁeld.

6) Turn the FMS Knob to select the desired checklist.

7) Press the ENT Key.

• Selected checklist text:

– Plain text

– Notes, Cautions, and

Warnings

– Challenge/Response pairs

– Challenges with no responses

– Check state of items

– Checklist complete indicator

8) With the desired checklist displayed, turn the FMS Knob to move up and down the checklist and highlight an

item with a hollow white rectangle. The default color for non-selected checklist items is blue; once an item is highlighted, it turns white.

Press the CLR Key to remove a check mark from an item.

9) Once the last item in a checklist is selected, ‘GO TO THE NEXT CHECKLIST?’ is highlighted. Press the ENT Key

to advance to the next checklist displayed.

10) To select a checklist item that is highlighted, press the ENT Key or DONE Softkey. Selected items turn green and

checkmarks are placed in the boxes next to the item. After an item is selected, the next item is automatically highlighted for selection.

Figure 1-32 Sample Checklist

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

190-00595-00 Rev. A1-34

Page 45

SYSTEM OVERVIEW

1.8 DISPLAY BACKLIGHTING

The backlighting of the PFD and MFD displays and bezel and Audio Panel keys can be adjusted automatically or manually. The default setting (automatic backlighting adjustment) uses photocell technology to automatically adjust for ambient lighting conditions. Photocell calibration curves are pre-conﬁgured to optimize display appearance through a broad range of cockpit lighting conditions. Manual backlighting adjustment can be accomplished using the existing instrument panel dimmer bus or the following procedures. In normal operating mode, backlighting can only be adjusted from the PFD. In Reversionary Mode, it can be adjusted from the remaining display.

Adjusting display backlighting:

1) Press the PFD

2) Turn the

3) Press the

4) With the intensity value now highlighted, enter the desired backlighting then press the

5) Turn the

6) To remove the menu, press the

Adjusting key backlighting:

1) Press the PFD

2) Turn the

3) Turn the

4) Turn the

5) Turn the

6) Press the

7) With the intensity value now highlighted, enter the desired backlighting and press the

8) Turn the

small FMS

ENT

Key.

large FMS

small FMS

large FMS

small FMS

ENT

Key.

large FMS

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

Knob to select ‘MANUAL’.

ENT

Knob to highlight ‘AUTO’ next to ‘MFD DSPL’ and repeat steps 2-4.

CLR

Key.

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

Knob to highlight ‘PFD DSPL’.

Knob in the direction of the green arrowhead to display ‘PFD KEY’.

Knob to highlight ‘AUTO’.

Knob to select ‘MANUAL’.

ENT

Knob to highlight ‘MFD DSPL’.

Key.

9) Turn the

10) To remove the menu, press the

190-00595-00 Rev. A

small FMS

Knob in the direction of the green arrowhead to display ‘MFD KEY’ and repeat steps 4-7.

CLR

Key.

PFD

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

Figure 1-33 PFD Setup Menu

1-35

Page 46

SYSTEM OVERVIEW

BLANK PAGE

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

190-00595-00 Rev. A1-36

Page 47

SECTION 2 FLIGHT INSTRUMENTS

2.1 INTRODUCTION

FLIGHT INSTRUMENTS

WARNING:

to the backup instruments.

NOTE:

instruments. Refer to the AFCS Section for details on these bugs and readouts, as they appear on the display during certain AFCS modes.

The G1000 System controls were designed so that regardless of which seat the pilot is ﬂying from, the aircraft can be ﬂown with one hand and the controls manipulated with the other hand. Increased situational awareness is provided by replacing the traditional instrument “six-pack” on the instrument panel with an easy-to-scan display that provides a large horizon, airspeed, attitude, altitude, vertical speed, and course deviation information. In addition to the ﬂight instruments, navigation, communication, annunciations, 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

– Trend vector

– Reference ﬂags

• Attitude Indicator with slip/skid

indication

• Altimeter, showing

– Trend vector

– Barometric setting

– Selected Altitude

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

The Automatic Flight Control System (AFCS) provides additional readouts and bugs on selected ﬂight

• Vertical Deviation/Glideslope Indicator

• Vertical Speed Indicator (VSI)

• Horizontal Situation Indicator, showing

– Heading and course indications

– Turn Rate Indicator

– Navigation source

– Course Deviation Indicator

(CDI)

– Bearing pointers and

information windows

• Outside air temperature (OAT)

• System time

• Timer/References Window, showing

– Generic timer

– Vspeed values and ﬂags

– Barometric minimum descent

altitude (MDA, DH)

The PFD also displays various alerts and annunciations.

190-00595-00 Rev. A

– DME Information Window

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

2-1

Page 48

FLIGHT INSTRUMENTS

NAV Frequency Box

Airspeed Indicator

True Airspeed

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 Barometric Setting

Vertical Speed Indicator (VSI)

Selected Altitude Bug

Altimeter

Selected Altitude

COM Frequency Box

AFCS Status Box

Navigation Status Box

Slip/Skid Indicator

Attitude Indicator

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

190-00595-00 Rev. A2-2

Page 49

FLIGHT INSTRUMENTS

Trafﬁc Annunciation

Selected Heading

Inset Map

DME Information Window

Bearing Information Windows

Selected Course

Figure 2-2 Additional PFD Information

Alerts Window

Barometric Minimum Descent Altitude

Annunciation Window

Vertical Deviation/Glideslope Indicator

Marker Beacon Annunciation

AFCS Status Annunciation

190-00595-00 Rev. A

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

2-3

Page 50

FLIGHT INSTRUMENTS

2.2 FLIGHT INSTRUMENTS

AIRSPEED INDICATOR

NOTE:

Refer to the Aircraft Flight Manual (AFM) for speed criteria.

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

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 (V

VFE/V

Airspeed

Trend Vector

Actual

Airspeed

Speed

Ranges

Vspeed

References

True

Airspeed

Figure 2-3 Airspeed Indicator

), at which point it turns red.

Figure 2-4 Red Pointer at V

SPEED AWARENESS RANGES

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). A red range is also present for low speed awareness.

AIRSPEED TREND VECTOR

The Airspeed Trend Vector is a vertical, magenta line, extending up or down on the airspeed scale, shown to the right of the color-coded speed range strip. The end of the trend vector corresponds to the predicted airspeed in 6 seconds if the current rate of acceleration is maintained. If the trend vector crosses VNE, the text of the actual airspeed readout changes to yellow. 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.

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

190-00595-00 Rev. A2-4

Page 51

VSPEED REFERENCES

FLIGHT INSTRUMENTS

NOTE:

Refer to the AFM for Vspeed values.

Vspeeds (Glide, VR, VX, and VY) can be changed and their ﬂags turned on/off from the Timer/References Window. When active (on), the Vspeeds are displayed at their respective locations to the right of the airspeed scale. By default, all Vspeed values are reset and all ﬂags turned off when power is cycled.

Changing Vspeeds and turning Vspeed ﬂags on/off:

1) Press the

2) Turn the

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

TMR/REF

large FMS

Softkey.

Knob to highlight the ﬁeld of the desired Vspeed to be changed.

ENT

Key (when a speed has been changed from a

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

4) With the ﬂag ON/OFF ﬁeld highlighted, turn the

5) To remove the window, press the

CLR

Key or the

small FMS

TMR/REF

Knob clockwise to ON or counterclockwise to OFF.

Softkey.

Figure 2-6 Timer/References Menu

Figure 2-5 Timer/References Window

Turning all Vspeed ﬂags on/off:

1) Press the

2) Press the

TMR/REF

Key.

Softkey.

3) To activate all Vspeed ﬂags, press the ENT Key with ‘All References On’ highlighted.

4) To remove all Vspeed ﬂags, turn the FMS Knob to highlight ‘All References Off’ and press the

ENT

Restoring all Vspeed defaults:

1) Press the

2) Press the

3) Turn the

TMR/REF

FMS

Softkey.

Key.

Knob to highlight ‘Restore Defaults’ and press the

ENT

Key.

190-00595-00 Rev. A

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

2-5

Page 52

FLIGHT INSTRUMENTS

ATTITUDE INDICATOR

NOTE

Some supplemental PFD information disappears when pitch exceeds +30˚/-20˚ or bank exceeds 65˚.

Attitude information is displayed over a virtual blue sky and brown ground with a white horizon line. The

Attitude Indicator displays the pitch, roll, and slip/skid information.

Roll Pointer

Roll Scale

Horizon Line

Aircraft Symbol

Land Representation

Pitch Scale

Slip/Skid Indicator

Figure 2-7 Attitude Indicator

Sky Representation

Roll Scale Zero

PITCH INDICATION

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˚.

Red extreme pitch warning chevrons pointing toward the horizon are displayed, starting at 50˚ above and 30˚ below the horizon line.

Nose LowNose High

Figure 2-8 Pitch Attitude Warnings

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

190-00595-00 Rev. A2-6

Page 53

FLIGHT INSTRUMENTS

ROLL AND SLIP/SKID INDICATION

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.

Figure 2-9 Slip/Skid Indication

ALTIMETER

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.

Selected

Altitude

(Meters)

Current Altitude

(Meters)

Barometric

Setting

(Hectopascals)

Figure 2-11 Altimeter (Metric)

Selected

Altitude Bug

Altitude

Trend

Vector

Barometric

Setting

Figure 2-10 Altimeter

Selected Altitude

Current

Altitude

ALTITUDE TREND VECTOR

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.

190-00595-00 Rev. A

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

2-7

Page 54

FLIGHT INSTRUMENTS

ALTIMETER BAROMETRIC SETTING

The Altimeter barometric pressure setting is displayed below the Altimeter in inches of mercury (in Hg) or

hectopascals (hPa) when the METRIC Softkey is selected.

Selecting the barometric Altimeter setting:

Turn the BARO (outer) Knob to select the desired setting.

Selecting standard barometric pressure (29.92 in Hg):

1) Press the PFD Softkey.

2) Press the STD BARO Softkey.

SELECTED ALTITUDE

NOTE:

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. The metric value, when selected, is displayed in a separate box above the Selected Altitude.

See the AFCS Section for more information about how the G1000 uses the Selected Altitude.

The Selected Altitude is displayed above the Altimeter in the box indicated by a selection bug symbol. A

Setting the Selected Altitude:

Turn the ALT Knob to set the Selected Altitude (large knob for 1000-ft increments, small for 100-ft

increments).

METRIC DISPLAY

Selected and current altitudes can be displayed in meters (readouts displayed above the normal readouts in feet) and the Altimeter barometric setting in hectopascals (see Figure 2-11). Note that the altitude tape does not change scale.

Displaying altitude and the Altimeter barometric setting in metric units:

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

2) Press the METRIC Softkey to display altitudes in meters and the barometric pressure setting in hectopascals.

3) Press the

BACK

Softkey to return to the top-level softkeys.

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

190-00595-00 Rev. A2-8

Page 55

FLIGHT INSTRUMENTS

VERTICAL DEVIATION/GLIDESLOPE INDICATOR

The Vertical Deviation/Glideslope Indicator (Figure 2-12) appears to the left of the Altimeter when an ILS is tuned in the active NAV ﬁeld (and selected on the Audio Panel). A green diamond appears and acts as the Vertical Deviation Indicator, like a glideslope needle on a conventional indicator.

VERTICAL SPEED INDICATOR (VSI)

NOTE:

Digits appear in the pointer when the climb or descent rate is greater than 100 fpm.

The Vertical Speed Indicator (VSI; Figure 2-13) displays the aircraft’s vertical speed with numeric labels and tick marks at 1000 and 2000 fpm in each direction on the non-moving tape. Minor tick marks are at intervals of 500 fpm.

The current vertical speed is displayed in the pointer, which also points to that speed on the non-moving tape. 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.

Marker Beacon

Annunciation

Vertical

Deviation/

Glideslope

Indicator

Figure 2-12 Vertical Deviation/Glideslope Indicator

Vertical

Speed

Pointer

Figure 2-13 Vertical Speed Indicator

190-00595-00 Rev. A

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

2-9

Page 56

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. The HSI presents heading, 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:

1) Press the

2) Press the

PFD

Softkey

360 HSI

ARC HSI

Softkey.

The 360˚ HSI (Figure 2-14) 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.

Turn Rate Indicator

Lateral Deviation Scale

Navigation Source

Aircraft Symbol

Course Deviation Indicator (CDI)

Rotating Compass Card

OBS Mode Active

To/From Indicator

Heading Bug

Course Pointer

Flight Phase

Turn Rate and Heading Trend Vector

Current Heading

Lubber Line

Figure 2-14 Horizontal Situation Indicator (360˚ HSI)

The Arc HSI (Figure 2-15) is a 140˚ expanded section of the compass rose. The Arc HSI contains a Course Pointer, 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

Figure 2-15 Arc HSI

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

Flight Phase

Annunciation

Course Deviation and

To/From Indicator

190-00595-00 Rev. A2-10

Page 57

HEADING AND COURSE INDICATIONS

FLIGHT INSTRUMENTS

NOTE:

See the AFCS Section for more information on Selected Heading functions.

A digital reading of the current magnetic heading appears on top of the HSI. The heading displayed on the HSI is always magnetic, even if the Navigation Angle (NAV ANGLE) is set to ‘True’ on the AUX - System Setup Page on the MFD (see the System Overview for details).

When the pilot selects a course by rotating the

CRS Knob, a digital reading appears for 3 seconds in a box to the right of the lubber line, next to the HSI. While the HSI is displayed as an arc, the Selected Course is displayed whenever the Course Pointer is not within the 140˚ currently shown Pressing the CRS Knob displays the digital reading, re-centers the CDI, and returns the course pointer pointing to the bearing of the active waypoint or navigation station (see OBS Mode for information on adjusting a GPS course).

When the pilot selects a heading by rotating the

HDG Knob, a digital reading appears for 3 seconds in a box to the left of the lubber line, next to the HSI. A rotatable heading bug marks the desired heading on the HSI. 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 displayed. This Selected Heading Bug and the current aircraft heading can be synchronized by pressing the HDG Knob, which moves the bug to the current heading.

Selected Heading

Current

Heading

Selected

Heading Bug

Selected

Course

Figure 2-16 Heading and Course Indications

TURN RATE INDICATOR

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. 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 (Figure 2-17).

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 (Figure 2-18).

Half-std Turn Rate

Std Turn Rate

Figure 2-17 Turn Rate Indicator and Trend Vector

Arrow Shown for Turn Rate > 4 deg/sec

Figure 2-18 Standard-Rate Turn Indication

Turn Rate Trend Vector

190-00595-00 Rev. A

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

2-11

Page 58

FLIGHT INSTRUMENTS

NAVIGATION SOURCE

The HSI can display two sources of navigation: GPS or NAV (VOR, localizer, and glideslope). The CDI Softkey cycles through the navigation sources. Color indicates the current navigation source: magenta (for GPS) or green (for VOR and LOC).

GPS

Selected

Figure 2-19 Navigation Sources with Example HSI Annunciations

Changing navigation sources:

1) Press the CDI Softkey to change from GPS to VOR1 or LOC1. The light blue tuning box is placed 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. The light blue tuning box is placed

over the NAV2 standby frequency.

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

NAV2 Selected for Tuning

LOC1

Selected

NAV1 Selected for Tuning

VOR2

Selected

Pressing the

through Navigation Sources

CDI

Softkey Cycles

Figure 2-20 Selecting a Navigation Source

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

190-00595-00 Rev. A2-12

Page 59

FLIGHT INSTRUMENTS

The following annunciations appear in yellow on the HSI to indicate abnormal GPS conditions:

• ‘INTEG’: Loss of Integrity–GPS integrity is insufﬁcient for the current phase of ﬂight

• ‘WARN’: GPS position error

AUTOMATIC NAVIGATION SOURCE SWITCHING

On the AUX - System Setup Page, ‘ILS CDI Capture’ may be changed to ‘Manual’. In ‘Auto’ (default) setting, the system automatically switches from GPS to LOC navigation source and changes the CDI scaling accordingly when:

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

• The ﬁnal approach ﬁx (FAF) is the active leg, 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 HSI 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 Vector-to-Final (see the GPS Navigation Section) also causes the HSI to switch to LOC navigation source, although the change is not considered automatic to the system and GPS steering guidance is not provided after this switch.

Changing the ILS CDI Capture 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

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

large FMS

Knob to highlight the ‘ILS CDI Capture’ ﬁeld in the ‘GPS CDI’ Box (Figure 2-21).

Figure 2-21 System Setup Page,

ILS CDI Capture Setting

190-00595-00 Rev. A

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

2-13

Page 60

FLIGHT INSTRUMENTS

OBS MODE

Enabling Omni-bearing Selector (OBS) Mode (with the OBS Softkey) 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 2-22). When OBS is disabled (the OBS Softkey is pressed again), the GPS returns to normal operation, with automatic sequencing of waypoints. OBS mode also allows a desired course to/from a waypoint to be set (with a CRS Knob); pressing the CRS Knob re-centers the CDI and returns the course pointer to the waypoint bearing.

Enabling/disabling OBS Mode while navigating with GPS:

1) Press the OBS Softkey to select OBS Mode.

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

3) Press the OBS Softkey again to return to normal operation.

GPS

Selected

Extended

Course Line

Pressing the

Enables OBS Mode

OBS

Softkey

As the aircraft crosses the missed approach point (MAP), 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

waypoints.

OBS Mode

Enabled

Pressing the

Returns to Normal Operation

Figure 2-22 Omni-bearing Selector (OBS) Mode

OBS

Softkey Again

Softkey label changes to SUSP. Selecting the SUSP Softkey resumes automatic of approach

SUSP

Annunciation

Pressing the

Automatic Waypoint Sequencing

SUSP

Softkey Suspends

Figure 2-23 Suspending Automatic Waypoint Sequencing

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

190-00595-00 Rev. A2-14

Page 61

FLIGHT INSTRUMENTS

COURSE DEVIATION INDICATOR

NOTE

If the pilot makes a heading change greater than 105˚ with respect to the course, 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

scale to display aircraft position relative to the course.

360º HSI

Arc HSI

CDI

Figure 2-24 Course Deviation Indicator

The CDI has the same angular limits as a mechanical CDI when coupled to a VOR or LOC. When coupled to GPS, the full scale limits for the CDI are deﬁned by a GPS-derived distance (5.0, 1.0, or 0.3 nm). The current GPS CDI scale setting is displayed as ‘System CDI’ on the AUX - System Setup Page, and the scale setting may also be changed (5.0 nm, 1.0 nm, 0.3 nm, or Auto) from this page (Figure 2-25). When set to ‘Auto’ (default), the CDI scale automatically adjusts to the desired limits based upon the current phase of ﬂight:

• Leaving the departure airport the CDI scale is set to 1.0 nm and gradually ramps up to 5.0 nm beyond 30

nm from the departure airport

• The CDI scale is set to 5.0 nm during the enroute phase of ﬂight

• Within 30 nm of the destination airport, the CDI scale gradually ramps down to 1.0 nm (terminal area)

• During approach operations, the CDI scale ramps down even further to 0.3 nm. This transition normally

occurs within 2.0 nm of the ﬁnal approach ﬁx (FAF).

If a lower CDI scale setting is selected (1.0 or 0.3 nm), the higher scale settings are not selected during any phase of ﬂight and the selected setting is displayed instead of the ﬂight phase annunciation. For example, if

1.0 nm is selected, the G1000 uses this for enroute and terminal phases and ramps down to 0.3 nm during an approach. Receiver Autonomous Integrity Monitoring (RAIM) protection limits follow the selected CDI scale and corresponding ﬂight phases.

190-00595-00 Rev. A

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

2-15

Page 62

FLIGHT INSTRUMENTS

Changing the GPS CDI settings:

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

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

large FMS

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

Figure 2-25 System Setup Page,

GPS CDI Settings

BEARING POINTERS AND INFORMATION WINDOWS

NOTE:

GPS, and ADF sources. 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 even 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.

Refer to the Audio Panel and CNS Section for information on tuning the radios.

Two bearing pointers and associated information (Figure 2-22) can be displayed on the HSI for NAV,

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

Information windows (Figure 2-26) are displayed to the lower sides of the HSI and show:

• Bearing source (NAV, GPS, ADF)

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

• Frequency (NAV, ADF)

• Station/waypoint identiﬁer (NAV, GPS)

• GPS-derived great circle distance to bearing source

If the NAV radio is the selected bearing source and is tuned to an ILS frequency, the bearing pointer is removed from the HSI and the frequency is replaced with “ILS”. If the NAV radio is not receiving the tuned VOR station, the bearing pointer is removed from the HSI and the frequency displayed in the information window is replaced with “NO DATA”. When NAV1 or NAV2 is the selected bearing source, the frequency is replaced by the station identiﬁer when the station is within range.

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

190-00595-00 Rev. A2-16

Page 63

FLIGHT INSTRUMENTS

If GPS is the selected bearing source, the active waypoint identiﬁer is displayed in lieu of a frequency. If an active waypoint is not selected, the bearing pointer is removed from the HSI and “NO DATA” is displayed in the information window.

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) Press the BRG Softkey a third time to change the bearing source to ADF (note: ADF radio installation is

optional).

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

DME INFORMATION WINDOW

NOTE:

Refer to the Audio Panel and CNS Section for information on tuning the radios.

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 is replaced by “–.– – NM”.

Displaying the DME Information Window:

1) Press the PFD Softkey.

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.

DME

Information

Window

Bearing 1

Pointer

Bearing 2

Pointer

Waypoint

Selected

Tuning Mode

Distance to

Bearing Source

DME Label

Frequency

Distance

Station

Identiﬁer

Bearing

Source

190-00595-00 Rev. A

Pointer

Icon

Bearing 1

Information

Window

Figure 2-26 HSI with Bearing and DME Information

Bearing 2

Information

Window

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

Pointer

Icon

Bearing

Source

2-17

Page 64

FLIGHT INSTRUMENTS

2.3 SUPPLEMENTAL FLIGHT DATA

NOTE:

Some displayed information disappears when pitch exceeds +30˚/-20˚ or bank exceeds 65˚. The Altimeter and Airspeed, Attitude, Vertical Speed, and Horizontal Situation indicators remain on the display and the Bearing Information 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:

• Trafﬁc Annunciations

• AFCS Annunciations

• Flight director Command Bars

• Inset Map

• Outside Air Temperature

• DME Information Window

• Transponder Data Box

Pressing the DFLTS Softkey (a second-level PFD softkey) turns off metric Altimeter display and the

Inset Map. Pressing this softkey does not restore display units to the default settings.

• System Time

• PFD Setup Menu

• Windows displayed in the lower right corner

• Barometric Minimum Descent Altitude Box

• Vertical Deviation/Glideslope Indicator

• Altimeter Barometric Setting

• Selected Altitude

TIMER/REFERENCES WINDOW

NOTE:

The Timer/References Window is enabled/disabled in the lower right corner of the PFD by pressing the

REF

• Generic Timer

• Vspeed values and ﬂags

• Barometric minimum descent altitude (MDA, DH)

Refer to Section 2.2 under the Airspeed Indicator discussion for information on Vspeeds and Section

2.4 for information on the barometric minimum descent altitude.

Softkey. This window provides access to the following settings:

Figure 2-27 Timer/References Window

TMR/

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

190-00595-00 Rev. A2-18

Page 65

FLIGHT INSTRUMENTS

GENERIC TIMER

The PFD 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.

Setting the generic timer:

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

5) Press the

6) With ‘START?’ highlighted, press the

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

TMR/REF

large FMS

ENT

Key.

Softkey.

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

ENT

small FMS

ENT

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

Knob to select the timer counting direction.

Key.

digits are reset.

9) To remove the window, press the

CLR

Key or the

TMR/REF

Softkey.

OUTSIDE AIR TEMPERATURE

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 Reversionary Mode

Changing temperature display units:

1) Select the AUX - System Setup Page using the FMS Knob.

2) Press the FMS Knob to activate the cursor.

3) Turn the large FMS Knob to highlight the ‘Temp’ ﬁeld (Figure 2-30).

4) Turn the small FMS Knob to select the desired unit.

5) Press the ENT Key to conﬁrm selection.

190-00595-00 Rev. A

Figure 2-28 Outside Air Temperature

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

2-19

Page 66

FLIGHT INSTRUMENTS

SYSTEM TIME

The system time is displayed in the lower right corner of the PFD. Three display formats are available, local 12-hr, local 24-hr, and Coordinated Universal Time (UTC). Time and date are obtained from the GPS satellites and cannot be changed, although a time offset may be entered (±HH:MM) for local times.

Figure 2-29 System Time

Conﬁguring the system time:

1) Select the AUX - System Setup Page using the FMS Knob.

2) Press the FMS Knob to activate the cursor.

3) Turn the large FMS Knob to highlight the ‘Time Format’ ﬁeld (Figure 2-31).

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 2-31 System Setup Page,

Figure 2-30 System Setup Page,

Display Units Settings

Date/Time Settings

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

190-00595-00 Rev. A2-20

Page 67

FLIGHT INSTRUMENTS

2.4 PFD ANNUNCIATIONS AND ALERTING FUNCTIONS

NOTE:

For a detailed description of annunciations and alerts, refer to Appendix A.

SOFTKEY ANNUNCIATIONS

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 label, and when pressed again opens the Alerts Window to display a descriptive message of the alert.

Warnings are time-critical and require immediate pilot attention. A ﬂashing WARNING Softkey annunciation and aural tone (single chime every two seconds) are used to alert the pilot of any warnings. The aural tone and ﬂashing WARNING annunciator continue until acknowledged by the pilot (by pressing the Softkey).

Caution indicates the existence of abnormal conditions on the aircraft that may require pilot intervention. A ﬂashing cautions. The ﬂashing CAUTION annunciator continues to ﬂash until acknowledged by the pilot (by pressing the

CAUTION Softkey annunciation and single aural tone (one chime) are used to alert the pilot of any

CAUTION

Softkey).

WARNING

An advisory provides general information to the pilot that may not need immediate attention. A ﬂashing ADVISORY Softkey annunciation (no aural tone) is used to alert the pilot of any message advisories. The ﬂashing ADVISORY annunciator continues to ﬂash until acknowledged by the pilot (by pressing the Softkey).

Figure 2-32 Softkey Annunciation (ALERTS Softkey labels)

ADVISORY

190-00595-00 Rev. A

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

2-21

Page 68

FLIGHT INSTRUMENTS

ALERTS WINDOW

Messages appear in the Alerts Window (in the lower right corner of the PFD; Figure 2-33) when a warning, caution, advisory alert, or G1000 message advisory occurs. System alert messages are provided to make the pilot aware 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 pressing the

ALERTS

Softkey. If the window is already open when a

new message is generated, pressing the ALERTS Softkey to acknowledge the message causes it to turn gray.

ANNUNCIATION WINDOW

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. 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.

Figure 2-33 G1000 Alerting System

Annunciation

Window

Alerts

Window

Softkey

Annunciation

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

190-00595-00 Rev. A2-22

Page 69

FLIGHT INSTRUMENTS

ALTITUDE ALERTING

The Altitude Alerting function provides the pilot with a visual alert 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. The following occurs when approach 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 and ﬂashes for ﬁve seconds.

• When the aircraft passes within 200 feet of the Selected Altitude, the Selected Altitude changes to light blue

text on a black background, ﬂashes for ﬁve seconds, and an aural tone is generated.

• 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 ﬁve seconds, and an

aural tone is generated.

Within 1000 ft Within 200 ft Deviation of ±200 ft

Figure 2-34 Altitude Alerting Visual Annunciations

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.

Outer Marker Middle Marker Inner Marker

Altimeter

Figure 2-35 Marker Beacon Annunciations

190-00595-00 Rev. A

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

2-23

Page 70

FLIGHT INSTRUMENTS

TRAFFIC ANNUNCIATION

The G1000 System displays trafﬁc symbolically on the Inset Map (PFD), 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 occurs:

• 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

(refer to the applicable TAS documentation for alerts generated by TAS equipment)

If additional TAs appear, new aural and visual alerts are generated.

“TRAFFIC” aural alert is generated, unless an optional Trafﬁc Advisory System (TAS) is installed

TAWS ANNUNCIATIONS

Terrain Awareness and Warning System (TAWS) annunciations appear on the PFD to the upper left of the Altimeter (also where the Marker Beacon Annunciations appear). Refer to the Hazard Avoidance Section and Appendix A for information on TAWS alerts and annunciations.

Figure 2-36 Trafﬁc and Example TAWS Annunciations

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

190-00595-00 Rev. A2-24

Page 71

FLIGHT INSTRUMENTS

BAROMETRIC MINIMUM DESCENT ALTITUDE

For altitude awareness, a barometric minimum descent altitude (MDA, or decision height, DH) can be set in the Timer/References Window. When active, the MDA is displayed in a window labeled ‘BARO MIN’ to the lower left of the Altimeter and on the altitude tape with a bug (once the altitude is within the range of the tape). This altitude can be adjusted in the ‘Baro Min’ ﬁeld in the Timer/References Window (Figure 2-37) from zero to 16,000 feet (in 10-ft increments with the small FMS Knob). The MDA is reset any time the power is cycled.

Setting the barometric minimum descent altitude and bug:

1) Press the

2) Turn the large FMS Knob to highlight the ‘Baro Min’ ﬁeld (Figure 2-37).

3) Use the small FMS Knob to enter the desired altitude (in 10-ft increments from zero to 16,000 feet) and press

TMR/REF

Softkey.

the ENT Key.

4) In the highlighted ON/OFF ﬁeld, turn the small FMS Knob clockwise to ON or counterclockwise to OFF.

5) To remove the window, press the

Figure 2-37 Barometric Minimum Descent Altitude

CLR

Key or the

TMR/REF

Softkey.

Visual annunciations alert the pilot when approaching the MDA (Figure 2-38):

• When the aircraft altitude descends to within 2500 feet of the MDA setting, the ‘BARO MIN’ Window appears

with the altitude in light blue text. Once in range, the bug appears on the tape in light blue.

• When the aircraft passes through 100 feet of the MDA, the bug and text turn white.

• Once the aircraft descends past the MDA, the bug and text turn yellow and the aural alert, “Minimums

Minimums”, is generated.

Alerting is inhibited while the aircraft is on the ground and until the aircraft reaches 150 feet above the MDA. If the aircraft proceeds to climb after having reached the MDA, once it reaches 50 feet above the MDA, alerting is disabled.

190-00595-00 Rev. A

Barometric

Minimum Bug

Barometric

Minimum Box

Figure 2-38 Barometric Minimum Descent Altitude Alerting Visual Annunciations

Within 2500 ft

Within 100 ft Altitude Reached

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

2-25

Page 72

FLIGHT INSTRUMENTS

BLANK PAGE

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

190-00595-00 Rev. A2-26

Page 73

SECTION 3 ENGINE INDICATION SYSTEM (EIS)

3.1 INTRODUCTION

EIS

NOTE:

The G1000 Engine Indication System (EIS) for the Beechcraft A36/G36 displays critical engine, electrical, fuel,

and other system parameters on the left side of the Multi Function Display (MFD) during normal operations. In Reversionary Mode, the display unit is re-conﬁgured to present Primary Flight Display (PFD) symbology together with the EIS (refer to the System Overview for information about Reversionary Mode).

Refer to the Pilot’s Operating Handbook (POH) for limitations.

EIS

EIS information is presented in three displays, accessed using the

• Engine Display – Default display, shows all critical engine, fuel, and electrical indicators

• Lean Display – Provides engine leaning information

• System Display – Shows numeric readouts of critical engine, fuel, and electrical indications

The Engine Manifold Pressure Gauge and Tachometer are present at the top of all three displays.

The EIS instrument types include gauges, horizontal bar indicators, bar graphs, and numeric readouts. Green

bands indicate normal ranges of operation; yellow and red bands indicate caution and warning, respectively. Pointers, bars, and readouts appear in white to indicate normal operation and change to yellow or red when parameters are in caution or warning ranges. If sensory data to an instrument becomes invalid or unavailable, a red “X” is shown across the instrument. The EIS automatically switches to the default Engine Display when certain parameters are exceeded while showing one of the other EIS displays.

190-00595-00 Rev. A

Figure 3-1 Multi Function Display

ENGINE

Garmin G1000 Pilot’s Guide for Beechcraft A36/G36

Softkey on the MFD:

3-1

Page 74

EIS

3.2 ENGINE DISPLAY

NOTE:

Refer to the POH for limitations regarding fuel quantity.

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 horizontal bar indicators for fuel ﬂow, cylinder head temperature, oil temperature and pressure, alternator load, bus voltage, and fuel quantity.

Fuel Flow Leaning Pointer

Figure 3-2 Engine Display

Garmin G1000 Pilot’s Guide for Beechcraft A36/G36

190-00595-00 Rev. A3-2

Page 75

EIS

Engine Manifold Pressure

Gauge (MAN IN HG)

Tachometer

(RPM)

Fuel Flow Indicator

(FFLOW GPH)

Cylinder Head Temperature

Indicator (CHT)

Oil Temperature Indicator

(OIL TEMP)

Oil Pressure Indicator

(OIL PRES)

Ammeter

(ALT LOAD)

Voltmeter

(BUS VOLTS)

Fuel Quantity Indicator

(FUEL QTY GAL)

Displays engine power in inches of Mercury (in Hg)

Shows propeller speed in revolutions per minute (rpm); the red area

indicates propeller overspeed

Displays current fuel ﬂow in gallons per hour (gph)

Normally-aspirated aircraft only: A Fuel Flow Leaning Pointer provides

a leaning reference for the pilot 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 climb or MPC.

The pointer, displaying the cylinder number, shows the highest Cylinder

Head Temperature (CHT) along a horizontal bar indicator

Oil temperature is shown along a horizontal bar indicator

Oil pressure is displayed along a horizontal bar indicator

Displays current loads for alternators 1 and 2

Displays the primary bus voltages for buses 1 and 2

Displays the amount of fuel in gallons (gal) for each tank (L and R)

190-00595-00 Rev. A

Garmin G1000 Pilot’s Guide for Beechcraft A36/G36

3-3

Page 76

EIS

3.3 LEAN DISPLAY

NOTE

The pilot should follow the engine manufacturer’s recommended leaning procedures in the POH.

The Lean Display is accessed by pressing the ENGINE Softkey followed by the LEAN Softkey. Engine temperature parameters are shown to provide assistance during engine leaning.

Bars for cylinders whose exhaust gas and head temperatures are within the normal range are shown in white. On the CHT Bar Graph, caution or 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 cylinder.

LEAN Softkey is pressed. The readouts below the bar graphs correspond to the selected

Figure 3-3 Lean Display

Garmin G1000 Pilot’s Guide for Beechcraft A36/G36

190-00595-00 Rev. A3-4

Page 77

EIS

Engine Manifold Pressure

Displays engine power in inches of Mercury (in Hg)

Gauge (MAN IN HG)

Tachometer

Fuel Flow

(RPM)

Shows propeller speed in revolutions per minute (rpm); the red area

indicates propeller overspeed

Displays current fuel ﬂow in gallons per hour (gph)

(FFLOW GPH)

Exhaust Gas Temperature Bar

Graph (EGT °F)

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 mark appears to represent the peak EGT for the selected

cylinder when the ASSIST Softkey is pressed

Cylinder Head Temperature

Bar Graph (CHT °F)

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.

While the EIS Lean Display is selected, the CYL SLCT Softkey can be pressed to obtain information about a

particular cylinder on both the EGT and CHT graphs. The selected cylinder is highlighted in light blue. The

SLCT Softkey is disabled during warning or caution conditions or when the ASSIST Softkey is pressed.

CYL

The ASSIST Softkey may be used to assist in the leaning process by identifying the EGT peak (shown as a light blue bar) of the selected cylinder. Pressing this softkey causes the EGT deviation from peak (∆ PEAK) to be displayed under the fuel ﬂow readout. The system automatically switches to the ﬁrst peak obtained.

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.

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 selected cylinder is shown in light blue.

Selecting the Engine Leaning Assist function:

From the Lean Display, press the ASSIST Softkey to identify the peak. The peak temperature for the selected

cylinder is indicated with a hollow block on the EGT Bar Graph and the temperature deviation from peak is shown underneath the EGT Bar Graph.

190-00595-00 Rev. A

Garmin G1000 Pilot’s Guide for Beechcraft A36/G36

3-5

Page 78

EIS

3.4 SYSTEM DISPLAY

NOTE:

Fuel calculations do not use the aircraft Fuel Quantity Indicator and are calculated from the last time

the fuel was reset.

NOTE:

Refer to the POH for limitations.

The System Display is accessed by pressing the ENGINE Softkey followed by the

SYSTEM

Softkey. Readouts below the Engine Manifold Pressure Gauge and Tachometer are grouped into three categories: System (Oil), Fuel Calculations, and Electrical.

Figure 3-4 System Display

Garmin G1000 Pilot’s Guide for Beechcraft A36/G36

190-00595-00 Rev. A3-6

Page 79

EIS

Engine Manifold Pressure

Gauge (MAN IN)

Tachometer

(RPM)

Oil Temperature

(OIL °C)

Oil Pressure

(OIL PSI)

Fuel Flow

(FFLOW GPH)

Calculated Fuel Remaining

(GAL REM)

Calculated Fuel Used

(GAL USED)

Calculated Endurance

(ENDUR)

Calculated Range

(RANGE NM)

Ammeter

(ALT LOAD)

Voltmeter

(BUS VOLTS)

Displays engine power in inches of Mercury (in Hg)

Shows propeller speed in revolutions per minute (rpm); the red area

indicates propeller overspeed

Oil temperature is shown in degrees Celsius (°C)

Oil pressure is displayed in pounds per square inch (psi)

Displays fuel ﬂow in gallons per hour (gph)

Shows the totalizer-based fuel remaining in gallons, adjusted by the

pilot using the FUEL softkeys

Shows the fuel used in gallons, based on fuel ﬂow

Shows the calculated endurance in hours:minutes (HH:MM)

Shows the calculated range in nautical miles (nm)

Displays loads for alternators 1 and 2 in amperes

Displays the primary bus voltages for buses 1 and 2

Fuel calculations are based on the fuel ﬂow totalizer and the displayed fuel remaining (GAL REM), adjusted by

the pilot 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

• 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

DEC FUEL or INC FUEL

Softkey to obtain the desired number of gallons

remaining (GAL REM).

Resetting the fuel totalizer:

From the System Display, press the

RST FUEL

Softkey. This also resets the displayed fuel remaining (GAL REM)

to zero.

190-00595-00 Rev. A

Garmin G1000 Pilot’s Guide for Beechcraft A36/G36

3-7

Page 80

EIS

BLANK PAGE

Garmin G1000 Pilot’s Guide for Beechcraft A36/G36

190-00595-00 Rev. A3-8

Page 81

AUDIO PANEL AND CNS

SECTION 4 AUDIO PANEL AND CNS

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):

• GDU 1040 Primary Flight Display (PFD) and

GDU 1042 Multi Function Display (MFD)

• GIA 63 Integrated Avionics Units (2)

The PFD/MFD 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.

• GMA 1347 Audio Panel

• GTX 33 Mode S Transponder

The Mode S transponder is controlled with softkeys located on the Primary Flight Display (PFD) at the lower portion of the screen. The Transponder Data Box is located to the left of the System Time Box. The data box displays a four-digit code ﬁeld, a mode ﬁeld, and a reply status indicator (Figure 4-1).

190-00595-00 Rev A

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

4-1

Page 82

AUDIO PANEL AND CNS

PFD/MFD CONTROLS AND FREQUENCY DISPLAY

3 4 5

7 861 2

Figure 4-1 PFD/MFD Controls, COM/NAV Frequency Tuning Boxes, and DME Tuning Window (PFD Shown)

4-2

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

190-00595-00 Rev. A

Page 83

AUDIO PANEL AND CNS

NAV VOL/ID Knob

and off. Volume level is shown in the NAV frequency ﬁeld as a percentage.

NAV Frequency Transfer Key

NAV Knob

– Tunes the standby frequencies for the NAV receiver (large knob for MHz; small knob for kHz).

Press to move the tuning box (light blue box) and Frequency Transfer Arrow between NAV1 and NAV2.

NAV Frequency Box

frequency of the NAV radio selected for navigation is displayed in green.

COM Frequency Box

transceiver frequency is displayed in green.

COM Knob

– Tunes the standby frequencies for the COM transceiver (large knob for MHz; small knob for kHz). Press to move the tuning box (light blue box) and Frequency Transfer Arrow between COM1 and COM2.

COM Frequency Transfer Key

for two seconds to tune the emergency frequency (121.500 MHz) automatically into the active frequency ﬁeld.

– Controls NAV audio volume level. Press to turn the Morse code identiﬁer audio on

– Transfers the standby and active NAV frequencies.

– Displays NAV standby and active frequency ﬁelds, volume, and station ID. The

– Displays COM standby and active frequency ﬁelds and volume. The selected COM

– Transfers the standby and active COM frequencies. Press and hold this key

COM

VOL/SQ Knob

– Controls COM audio volume level. Press to turn the COM automatic squelch on

and off. Volume level is shown in the COM frequency ﬁeld as a percentage.

DME Tuning Window

ENT Key

FMS Knob

– Validates or conﬁrms DME pairing mode and Auto-tune selection.

– Flight Management System Knob, used to select DME modes and Auto-tune entries when

– Displays DME frequency pairing mode. Display by pressing DME Softkey.

DME Tuning Window or NRST Window is present. Press the FMS Knob to turn the selection cursor on and off. The large knob moves the cursor in the window. The small knob selects individual characters for the highlighted cursor location.

Transponder Data Box

– Indicates the selected transponder code, operating mode, reply, and ident status

for the transponder.

190-00595-00 Rev A

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

4-3

Page 84

AUDIO PANEL AND CNS

AUDIO PANEL CONTROLS

Figure 4-2 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 A36/G36 aircraft.

4-4

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

190-00595-00 Rev. A

Page 85

AUDIO PANEL AND CNS

COM3

COM 1/2

TEL

SPKR

MKR/MUTE

HI SENS

DME

– Not used in A36/G36 aircraft.

–

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

– Not used in A36/G36 aircraft.

– Selects the passenger address system. The selected COM transmitter is deselected when the PA Key

is pressed.

– Pressing this key selects and deselects the cabin speaker. COM and NAV receiver audio can be

heard on the speaker.

– Selects Marker Beacon Receiver audio. Mutes the currently received Marker Beacon Receiver audio. Un-mutes automatically when new marker beacon audio is received. Also, stops play of recorded COM audio.

– Press to increase Marker Beacon Receiver sensitivity. Press again to return to low sensitivity.

– Pressing turns the optional DME audio on or off.

NAV1

ADF

NAV2

AUX

MAN SQ

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

– Not used in A36/G36 aircraft.

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

– Not used in A36/G36 aircraft.

– Press to enable manual squelch for the intercom. When active, press the PILOT Knob to

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

PLAY

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

PILOT

COPLT

PILOT Knob

– Pressing selects the pilot intercom isolation. Press again to deselect pilot isolation.

– Pressing selects the copilot intercom isolation. Press again to deselect copilot isolation.

– Press to switch between volume and squelch control as indicated by the ‘VOL’ or ‘SQ’ being

MKR/MUTE

Key during play of a memory block stops play.

illuminated. 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.

Reversionary Mode Button

190-00595-00 Rev A

– Pressing manually selects Reversionary Mode.

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

4-5

Page 86

AUDIO PANEL AND CNS

4.2 COM OPERATION

COM TRANSCEIVER SELECTION AND ACTIVATION

NOTE:

During PA Mode, the COM MIC annunciator is extinguished and the COM active frequency color is

white, indicating that the COM transmitter is inactive.

NOTE:

When turning on the G1000 for use, the system remembers the last frequencies used and the active

COM transceiver state prior to shutdown.

The COM Frequency Box is composed of four ﬁelds; the two active frequencies are on the left side and the

two standby frequencies are on the right.

The COM transceiver is selected for transmitting by pressing the

COM MIC

Keys on the Audio Panel. A selected COM frequency displayed in green indicates that the COM transceiver is selected on the Audio Panel (

COM1 MIC

COM2 MIC

Keys). Both active COM Frequencies appearing in white indicate that no COM

radio is selected for transmitting (PA Key is selected on the Audio Panel).

Frequencies in the standby ﬁeld are displayed in either white or gray. The standby frequency in the tuning

box is white. The other standby frequency is gray.

During reception of audio from the COM radio selected for transmission, audio from the other COM radio

is muted.

Active

Fields

Standby

Fields

Top Section of

the Audio Panel

Tuning Box

COM2 Radio is Selected

on the Audio Panel

Figure 4-3 Selecting a COM Radio for Transmit

4-6

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

190-00595-00 Rev. A

Page 87

AUDIO PANEL AND CNS

TRANSMIT/RECEIVE INDICATIONS

During COM transmission, a white ‘TX’ appears by the active COM frequency replacing the Frequency

Transfer Arrow. On the Audio Panel, when the active COM is transmitting, the active transceiver

COM MIC

Key Annunciator ﬂashes approximately once per second.

During COM signal reception, a white ‘RX’ appears by the active COM frequency replacing the Frequency

Transfer Arrow.

Annunciator

Flashes During

Transmit and

Receive Indicators

Figure 4-4 COM Radio Transmit and Receive Indications

Transmission

STUCK MICROPHONE

If the push-to-talk (PTT) Key becomes stuck, the COM transmitter stops transmitting after 35 seconds of

continuous operation. An alert appears on the PFD to advise the crew of a stuck microphone.

The

COM1 MIC

COM2 MIC

Key Annunciator on the Audio Panel continues to ﬂash as long as the PTT

Key remains stuck.

Figure 4-5 Stuck Microphone Alert

190-00595-00 Rev A

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

4-7

Page 88

AUDIO PANEL AND CNS

COM TRANSCEIVER MANUAL TUNING

The COM frequency controls and frequency boxes are on the right side of the PFD and MFD.

Manually tuning a COM frequency:

1) Turn the

2) Press the

COM

Knob to tune the desired frequency in the COM Tuning Box.

Frequency Transfer

Key to transfer the frequency to the active ﬁeld.

3) Adjust the volume level with the COM VOL/SQ Knob.

4) Press the COM VOL/SQ Knob to turn automatic squelch on and off.

VOL/SQ

Turn

volume. Press Knob to Turn

Automatic Squelch On or Off

Knob to adjust

Figure 4-6 COM Frequency Tuning

Press the

Frequencies Between Active

and Standby Frequency Boxes

Frequency Transfer

Key to Transfer COM

COM

Turn the Tune the Frequency in

the Tuning Box

Knob to

SELECTING THE RADIO TO BE TUNED

Pressing the small COM Knob transfers the frequency tuning box and the Frequency Transfer Arrow

between the upper and lower radio frequency ﬁelds.

4-8

Press the

Switch the Tuning Box From

One COM Radio to the Other

Figure 4-7 Switching COM Tuning Boxes

COM

Knob to

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

190-00595-00 Rev. A

Page 89

AUDIO PANEL AND CNS

COM TUNING FAILURE

In case of a COM system tuning failure, the emergency frequency (121.500 MHz) is automatically tuned in

the radio in which the tuning failure occurred.

Emergency Channel

Loaded Automatically

Figure 4-8 COM Tuning Failure

QUICK-TUNING AND ACTIVATING 121.500 MHZ

Pressing and holding the COM

Frequency Transfer

Key for two seconds automatically loads the emergency COM frequency (121.500 MHz) in the active ﬁeld of the COM radio selected for tuning (the one with the transfer arrow). In the example shown, pressing the Audio Panel COM2 MIC Key activates the transceiver.

Press for Two Seconds to Load 121.500 MHz

Figure 4-9 Quickly Tuning 121.500 MHz

190-00595-00 Rev A

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

4-9

Page 90

AUDIO PANEL AND CNS

AUTO-TUNING THE COM FREQUENCY

COM frequencies can be automatically tuned from the following:

• Nearest Airports Window (PFD)

• WPT – Airport Information Page

• NRST – Nearest Airports Page

AUTO-TUNING FROM THE PFD

COM frequencies for the nearest airports can be automatically tuned from the Nearest Airports Window on

the PFD. When the desired frequency is entered, it becomes a standby frequency. Pressing the

Transfer

Key places this frequency into the COM Active Frequency Field.

Auto-tuning a COM frequency for a nearby airport from the PFD:

• NRST – Nearest (ARTCC, FSS, WX) Frequencies Page

• NRST – Nearest Airspaces Page

Frequency

1) Press the

NRST

Softkey on the PFD to open the Nearest Airports Window. A list of 25 nearest airport identiﬁers

and COM frequencies is displayed.

2) Turn the

3) Press the

4) Press the Frequency Transfer Key to transfer the frequency to the COM Active Frequency Field.

FMS

Knob to scroll through the list and highlight the desired COM frequency.

ENT

Key to load the COM frequency into the COM Standby Tuning Box.

4-10

Figure 4-10 Nearest Airports Window (PFD)

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

Press the

Softkey to Open

the Nearest

Airports Window

NRST

190-00595-00 Rev. A

Page 91

AUDIO PANEL AND CNS

AUTO-TUNING FROM THE MFD

Frequencies can be automatically loaded into the COM Frequency Box from pages in the NRST or WPT

page group by highlighting the frequency and pressing the ENT Key (Figures 4-11, 4-12, and 4-13).

Auto-tuning a COM frequency from the MFD:

1) From any page that the COM frequency can be auto-tuned, activate the cursor by pressing the FMS Knob or the

appropriate softkey.

2) Turn the FMS Knob to place the cursor on the desired COM frequency (Figure 4-13).

3) Press the ENT Key to load the COM frequency into the standby ﬁeld of the selected COM radio.

4) Press the Frequency Transfer Key to transfer the frequency to the COM Active Frequency Field.

Turn the Knob to Scroll Through a List

of Frequencies

FMS

Press the

Load a Highlighted

the COM Standby

Figure 4-11 Frequency Auto-Tuning from the MFD

ENT

Key to

Frequency into

Frequency Box

OR:

5) Press the MENU Key to display the PAGE MENU (Figure 4-12).

6) Turn the large FMS Knob to scroll through the OPTIONS Menu.

7) Press the ENT Key to place the cursor on the desired selection.

8) Scroll through the frequency selections with the FMS Knob or the ENT Key.

9) Press the ENT Key to load the COM frequency into the standby ﬁeld of the selected COM radio.

10) Press the Frequency Transfer Key to transfer the frequency to the COM Active Frequency Field.

190-00595-00 Rev A

Figure 4-12 Nearest Pages PAGE MENU

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

4-11

Page 92

AUDIO PANEL AND CNS

On the WPT - Airport Information page, the cursor can be placed on the frequency ﬁeld from the PAGE MENU or by pressing the FMS Knob. The FMS Knob is used to scroll through the list. The frequency is transferred to the COM Standby Field with the ENT Key.

Press

Transfer

Frequency into COM

Frequency

Key to Load

Active Tuning Box

Selected Airport

Identiﬁer and

Information

Runway

Information

Figure 4-13 WPT – Airport Information Page

Press

ENT

Key to Load

Frequency into COM

Standby Field. Cursor

then Advances to

Next Frequency.

Press

INFO

AIRPORT, RUNWAYS,

and FREQUENCIES

Softkey for

Windows

4-12

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

190-00595-00 Rev. A

Page 93

AUDIO PANEL AND CNS

COM frequencies can also be auto-tuned from the NRST – Nearest Airspaces, NRST – Nearest Frequencies, and NRST – Nearest Airports Pages on the MFD in a similar manner using the appropriate softkeys or MENU Key and the FMS Knob.

190-00595-00 Rev A

Figure 4-14 NRST – Nearest Airspaces, NRST – Nearest Airports, and NRST – Nearest Frequencies Pages

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

4-13

Page 94

AUDIO PANEL AND CNS

FREQUENCY SPACING

The G1000 COM radios can tune either 25 kHz spacing (118.000 to 136.975 MHz) or 8.33 kHz spacing (118.000 to 136.990 MHz) for 760-channel or 3040-channel conﬁguration. When 8.33 kHz channel spacing is selected, all of the 25 kHz channel spacing frequencies are also available in the complete 3040 channel list.

COM channel spacing is set from the MFD on the System Setup Page of the AUX Page Group.

8.33 kHz Channel Spacing

Figure 4-15 COM Channel Spacing

25 kHz Channel

Spacing

Changing COM frequency channel spacing:

1) Select the AUX – System Setup Page.

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

3) Turn the large FMS Knob to highlight the Channel Spacing Field in the COM Conﬁguration Box.

4) Turn the small FMS Knob to select the desired channel spacing.

5) Press the ENT Key to complete the channel spacing selection.

4-14

Figure 4-16 AUX – System Setup Page

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

Select 8.33 kHz

or 25.0 kHz

COM Frequency

Channel Spacing

190-00595-00 Rev. A

Page 95

AUDIO PANEL AND CNS

AUTOMATIC SQUELCH

Automatic Squelch quiets unwanted static noise when no audio signal is received, while still providing good

sensitivity to weak COM signals. To disable Automatic Squelch, press the

VOL/SQ

Squelch is disabled, COM audio reception is always on. Continuous static noise is heard over the headsets and speaker, if selected. Pressing the

VOL/SQ

Knob again enables Automatic Squelch.

Knob. When Automatic

Press the COM

Knob to turn off

Automatic Squelch.

Press again to restore

Automatic Squelch.

Figure 4-17 Overriding Automatic Squelch

VOL/

VOLUME

COM radio volume level can be adjusted from 0 to 100% using the clockwise increases volume, turning the knob counterclockwise decreases volume. When adjusting volume, the level is displayed in place of the standby frequencies. Volume level indication remains for two seconds after the change.

Figure 4-18 COM Volume Level

VOL/SQ

COM Volume

Level Remains for

Two Seconds

Knob. Turning the knob

190-00595-00 Rev A

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

4-15

Page 96

AUDIO PANEL AND CNS

4.3 NAV OPERATION

NAV RADIO SELECTION AND ACTIVATION

The NAV Frequency Box is composed of four ﬁelds consisting of two standby ﬁelds and two active ﬁelds. In the NAV Frequency Box, the active frequencies are on the right side and the standby frequencies are on the left.

A NAV radio is selected for navigation by pressing the frequency selected for navigation is displayed in green. Pressing the

CDI

navigation radio. Pressing the

Softkey twice selects NAV2 as the navigation radio. Pressing the

Softkey a third time activates GPS mode. Pressing the

While cycling through the

CDI

Softkey selections, the NAV Tuning Box and the Frequency Transfer Arrow are

CDI

Softkey located on the PFD The active NAV

CDI

Softkey once selects NAV1 as the

CDI

Softkey again cycles back to NAV1.

CDI

placed in the active NAV Frequency Field and the active NAV frequency color changes to green.

The three navigation modes that can be cycled through are:

• VOR1 (or LOC1) – If NAV1 is selected, a green single line arrow (not shown) labeled either ‘VOR1’ or ‘LOC1’

is displayed on the HSI and the active NAV1 frequency is displayed in green.

• VOR2 (or LOC2) – If NAV2 is selected, a green double line arrow (shown) labeled either ‘VOR2’ or ‘LOC2’

is displayed on the HSI and the active NAV2 frequency is displayed in green.

• GPS – If GPS Mode is selected, a magenta single line arrow (not shown) appears on the HSI and neither NAV

radio is selected. Both active NAV frequencies are then displayed in white.

Standby

Fields

Active

Fields

Tuning Box

See the Flight Instruments Section for selecting the bearing information windows (VOR) and using VOR as the source for the bearing pointer.

4-16

The NAV Radio is

Selected by Pressing

the

CDI

Softkey

Figure 4-19 Selecting a NAV Radio for Navigation

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

190-00595-00 Rev. A

Page 97

AUDIO PANEL AND CNS

The NAV radio is selected for listening by pressing the corresponding key on the Audio Panel.

Pressing the NAV1, NAV2, or DME Key selects and deselects the navigation radio source. Selected audio can be heard over the headset and the speakers (if selected). All radios can be selected individually or simultaneously.

Figure 4-20 Selecting a NAV Radio Receiver

NAV RECEIVER MANUAL TUNING

The NAV frequency controls and frequency boxes are on the left side of the PFD and MFD.

Manually tuning a NAV frequency:

1) Turn the

2) Press the

NAV

Knob to tune the desired frequency in the NAV Tuning Box.

Frequency Transfer

Key to transfer the frequency to the NAV Active Frequency Field.

3) Adjust the volume level with the NAV VOL/ID Knob.

4) Press the NAV VOL/ID Knob to turn the Morse code identiﬁer audio on and off.

VOL/ID

Turn

volume. Press Knob to Turn

Morse Code On or Off

Press the

Transfer NAV Frequencies Between

Active and Standby Frequency Fields

Turn the

Tune the Frequency in

Knob to adjust

Frequency Transfer

NAV

Knob to

the Tuning Box

Key to

Figure 4-21 NAV Frequency Tuning

190-00595-00 Rev A

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

4-17

Page 98

AUDIO PANEL AND CNS

SELECTING THE RADIO TO BE TUNED

Pressing the small NAV Knob transfers the frequency tuning box and the Frequency Transfer Arrow between

the upper and lower radio frequency ﬁelds.

Press the

Figure 4-22 Switching NAV Tuning Boxes

NAV

the Tuning Box From One

NAV Radio to the Other

Knob to Switch

VOR/LOC ID

When the Morse code Identiﬁer audio is on for a NAV radio, a white ‘ID’ appears to the left of the active

NAV frequency.

In the example shown, in order to listen to either station identiﬁer, press the NAV1 or NAV2 Key on the

Audio Panel. Pressing the Tuning Box. To turn off both NAV IDs, transfer the NAV Tuning Box between NAV1 and NAV2 with the small NAV Knob and press the

The Morse Code Identiﬁer

for the GHM VOR is On

VOL/ID Knob turns off the Morse code audio only in the radio with the NAV

VOL/ID Knob again to turn the Morse code off in the other radio.

Station

Identiﬁer

Figure 4-23 NAV Radio ID Indication

VOLUME

NAV Radio volume level can be adjusted from 0 to 100% using the

clockwise increases volume, counterclockwise decreases volume.

When adjusting, the level is displayed in place of the standby frequencies. Volume level indication remains

for two seconds after the change.

NAV Volume

Level Remains for

Two Seconds

Figure 4-24 NAV Volume Levels

VOL/ID

Knob. Turning the knob

4-18

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

190-00595-00 Rev. A

Page 99

AUTO-TUNING THE NAV FREQUENCY

NAV frequencies can be selected and loaded from the following MFD pages:

• WPT – Airport Information

• NRST – Nearest VOR

AUDIO PANEL AND CNS

• WPT – VOR Information

• NRST – Nearest Airports

• NRST – Nearest (WX, VOR) Frequencies

• NRST – Nearest Airspaces

The MFD provides auto-tuning of NAV frequencies from waypoint and nearest pages. During enroute navigation, the NAV frequency is entered automatically into the NAV standby frequency ﬁeld. During approach activation the NAV frequency is entered automatically into the NAV active frequency ﬁeld.

Frequencies can be automatically loaded into the NAV Frequency Boxes by highlighting the frequency and pressing the

ENT

Key (Figures 4-25, 4-26, and 4-27).

Auto-tuning from the MFD:

1) From any page that the NAV frequency can be auto-tuned, activate the cursor by pressing the FMS Knob or the

appropriate softkey.

2) Turn the FMS Knob to place the cursor on the desired NAV identiﬁer.

3) Press the FREQ Softkey to place the cursor on the NAV frequency (Figure 4-27).

4) Press the ENT Key to load the NAV frequency into the standby ﬁeld of the selected NAV radio.

5) Press the Frequency Transfer Key to transfer the frequency to the NAV Active Frequency Field.

FMS

Turn the

Knob to Scroll Through a List of Frequencies

Press the

Key to Load

a Highlighted

Frequency into

the NAV Standby

Frequency Box

ENT

190-00595-00 Rev A

Figure 4-25 NAV Frequency Auto-Tuning from the MFD

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

4-19

Page 100

AUDIO PANEL AND CNS

OR:

6) Press the MENU Key to display the PAGE MENU (Figure 4-26).

7) Turn the large FMS Knob to scroll through the OPTIONS Menu.

8) Press the ENT Key to place the cursor on the desired selection.

9) Scroll through the frequency selections with the FMS Knob or the ENT Key.

10) Press the ENT Key to load the COM frequency into the standby ﬁeld of the selected COM radio.

11) Press the Frequency Transfer Key to transfer the frequency to the COM Active Frequency Field.

Figure 4-26 Nearest Pages PAGE MENU

4-20

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

190-00595-00 Rev. A

Garmin A36, G36 Pilot's Guide

Specifications and Main Features

Frequently Asked Questions

User Manual

SECTION 1 SYSTEM OVERVIEW

1.1 SYSTEM DESCRIPTION

1.2 LINE REPLACEABLE UNITS

1.3 SECURE DIGITAL (SD) CARDS

1.4 SYSTEM POWER-UP

1.5 SYSTEM OPERATION

NORMAL DISPLAY OPERATION

REVERSIONARY DISPLAY OPERATION

G1000 SYSTEM ANNUNCIATIONS

AHRS OPERATION

1.6 G1000 CONTROLS

PFD/MFD CONTROLS

SOFTKEY FUNCTION

1.7 ACCESSING G1000 FUNCTIONALITY

MENUS

DATA ENTRY

PAGE GROUPS

SYSTEM SETUP AND STATUS

ELECTRONIC CHECKLISTS (OPTIONAL)

1.8 DISPLAY BACKLIGHTING

SECTION 2 FLIGHT INSTRUMENTS

2.1 INTRODUCTION

2.2 FLIGHT INSTRUMENTS

AIRSPEED INDICATOR

ATTITUDE INDICATOR

ALTIMETER

VERTICAL DEVIATION/GLIDESLOPE INDICATOR

VERTICAL SPEED INDICATOR (VSI)

HORIZONTAL SITUATION INDICATOR (HSI)

2.3 SUPPLEMENTAL FLIGHT DATA

TIMER/REFERENCES WINDOW

OUTSIDE AIR TEMPERATURE

SYSTEM TIME

2.4 PFD ANNUNCIATIONS AND ALERTING FUNCTIONS

SOFTKEY ANNUNCIATIONS

ALERTS WINDOW

ANNUNCIATION WINDOW

ALTITUDE ALERTING

MARKER BEACON ANNUNCIATIONS

TRAFFIC ANNUNCIATION

TAWS ANNUNCIATIONS

BAROMETRIC MINIMUM DESCENT ALTITUDE

SECTION 3 ENGINE INDICATION SYSTEM (EIS)

3.1 INTRODUCTION

3.2 ENGINE DISPLAY

3.3 LEAN DISPLAY

3.4 SYSTEM DISPLAY