Garmin 350, 400 Pilot's Guide

Cessna

350/400

This manual reﬂects the operation of System Software version 0545.00 or later for the Cessna 350 and 0530.04 or later for the Cessna 400. Some differences in operation may be observed when comparing the information in this manual to earlier or later software versions.

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

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

Garmin (Europe) Ltd., Liberty House, Bulls Copse Road, Hounsdown Business Park, Southampton, SO40 9RB, U.K Tel: 44/0870.8501241 Fax: 44/0870.8501251

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

Website Address: www.garmin.com

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

Garmin® and G1000® are registered trademarks of Garmin Ltd. or its subsidiaries. WATCH™, FliteCharts™, and SafeTaxi™ are trademarks of Garmin Ltd. or its subsidiaries. These trademarks may not be used without the express permission of Garmin.

Stormpscope® is a registered trademark of L-3 Communications; Ryan® is a registered trademark of Avidyne Corporation; NavData® is a registered trademark of Jeppesen, Inc.; and XM® is a registered trademark of XM Satellite Radio, Inc..

August 2007 Printed in the U.S.A.

Garmin G1000 Pilot’s Guide for the Cessna 350/400

190-00552-01 Rev. D

LIMITED WARRANTY

This Garmin product is warranted to be free from defects in materials or workmanship for three years from the date of purchase. Within this period, Garmin will, at its sole option, repair or replace any components that fail in normal use. Such repairs or replacement will be made at no charge to the customer for parts and labor, provided that the customer shall be responsible for any transportation cost. This warranty does not cover failures due to abuse, misuse, accident, or unauthorized alterations or repairs.

THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES EXPRESS OR IMPLIED OR STATUTORY, INCLUDING ANY LIABILITY ARISING UNDER ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE, STATUTORY OR OTHERWISE. THIS WARRANTY GIVES YOU SPECIFIC LEGAL RIGHTS, WHICH MAY VARY FROM STATE TO STATE.

IN NO EVENT SHALL GARMIN BE LIABLE FOR ANY INCIDENTAL, SPECIAL, INDIRECT OR CONSEQUENTIAL DAMAGES, WHETHER RESULTING FROM THE USE, MISUSE, OR INABILITY TO USE THIS PRODUCT OR FROM DEFECTS IN THE PRODUCT. Some states do not allow the exclusion of incidental or consequential damages, so the above limitations may not apply to you.

Garmin retains the exclusive right to repair or replace the unit or software, or to offer a full refund of the purchase price, at its sole discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF WARRANTY.

To obtain warranty service, contact your local Garmin Authorized Service Center. For assistance in locating a Service Center near you, visit the Garmin Website at “http://www.garmin.com” or contact Garmin Customer Service at 800-800-1020.

190-00552-01 Rev. D

Garmin G1000 Pilot’s Guide for the Cessna 350/400

WARNINGS, CAUTIONS, AND NOTES

WARNING:

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

WARNING:

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

WARNING:

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

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

WARNING:

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

WARNING:

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

WARNING:

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

WARNING:

Do not use outdated database information. Databases used in the G1000 System must be updated regularly in order to ensure that the information remains current. Pilots using any outdated database do so entirely at their own risk.

Garmin G1000 Pilot’s Guide for the Cessna 350/400

190-00552-01 Rev. Dii

WARNINGS, CAUTIONS, AND NOTES

WARNING:

Do not use basemap (land and water data) information for primary navigation. Basemap data is intended only to supplement other approved navigation data sources and should be considered as an aid to enhance situational awareness.

WARNING:

Trafﬁc information shown on the G1000 Multi Function Display is provided as an aid in visually acquiring trafﬁc. The aircraft should be maneuvered based only upon ATC guidance or positive visual acquisition of conﬂicting trafﬁc.

WARNING:

XM Weather should not be used for hazardous weather penetration. Weather information

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

WARNING:

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

WARNING:

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

WARNING

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

WARNING

This product, its packaging, and its components contain chemicals known to the State of California to cause cancer, birth defects, or reproductive harm. This notice is being provided in accordance with California’s Proposition 65. For additional information, refer to the website at www.garmin.com/ prop65.

WARNING

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

WARNING

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

190-00552-01 Rev. D

Garmin G1000 Pilot’s Guide for the Cessna 350/400

iii

WARNINGS, CAUTIONS, AND NOTES

CAUTION:

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

CAUTION:

The GDU 1040 PFD and GDU 1040/1044 MFD displays use a lens coated with a special antireﬂective 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:

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

NOTE:

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

NOTE:

The GDU 1040/1044 PFD/MFD may require a warm-up time of up to 30 minutes when exposed to

-40˚C for an extended period. A warm-up time of up to 15 minutes may be required when exposed to -30˚C for an extended period.

NOTE:

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

NOTE:

Interference from GPS repeaters operating inside nearby hangars can cause an intermittent loss of attitude and heading displays while the aircraft is on the ground. Moving the aircraft more than 100 feet away from the source of the interference should alleviate the condition.

NOTE:

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

Garmin G1000 Pilot’s Guide for the Cessna 350/400

190-00552-01 Rev. Div

Record of Revisions

REVISION INFORMATION

Part Number

190-00552-00 A 03/29/06 i – I-4 Initial release 190-00552-01 A 07/11/07 i – I-6 Added GDU 8.10 parameters, WAAS, VNAV, Airways and Charts

Revision Date Page Range Description

B 07/26/07 i – I-6 Clerical C 08/03/07 i – I-6 Clerical D 12/13/07 i-I-6 Changed aircraft designation to Cessna 350/400

190-00552-01 Rev. D

Garmin G1000 Pilot’s Guide for the Cessna 350/400

TABLE OF CONTENTS

SECTION 1 SYSTEM OVERVIEW

1.1 Line Replaceable Units ........................................1-2

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

1.3 System Power-up ..................................................1-8

1.4 System Operation .................................................1-9

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

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

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

System Status ..........................................................1-11

AHRS Operation ......................................................1-13

GPS Receiver Operation ...........................................1-14

1.5 G1000

Controls ...................................................1-18

PFD/MFD Controls ...................................................1-18

MFD/PFD Control Unit .............................................. 1-20

Softkey Function ...................................................... 1-22

1.6 Accessing G1000 Functionality ........................1-28

Menus ....................................................................1-28

Data Entry ..............................................................1-28

Page Groups ...........................................................1-30

System Settings .......................................................1-34

Timers .................................................................... 1-39

Scheduler ................................................................1-41

Electronic Checklists (Optional) .................................1-43

1.7 Display Backlighting .......................................... 1-45

SECTION 2 FLIGHT INSTRUMENTS

2.1 Flight Instruments .................................................. 2-4

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

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

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

Vertical Speed Indicator (VSI) ......................................2-8

Vertical Deviation ......................................................2-9

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

Course Deviation Indicator (CDI) ............................... 2-15

2.2 Supplemental Flight Data .................................2-22

Temperature displays ...............................................2-22

Wind Data ..............................................................2-23

Vertical Navigation (VNV) Indications ........................2-24

2.3 PFD Annunciations and Alerting Functions .....

G1000 Alerting System .............................................2-25

Marker Beacon Annunciations .................................. 2-26

Trafﬁc Annunciation .................................................2-27

2-25

TAWS Annunciations (Optional) ................................2-27

Altitude Alerting ......................................................2-28

Low Altitude Annunciation .......................................2-28

Minimum Descent Altitude/Decision Height Alerting ...2-29

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

Abnormal GPS Conditions ........................................2-30

Unusual Attitudes ....................................................2-31

2-30

SECTION 3 ENGINE INDICATION SYSTEM

3.1 EIS Display .............................................................3-2

3.2 Engine Page ..........................................................3-4

Carbon Monoxide Detection .......................................3-6

Fuel Calculations Group .............................................3-6

Engine Temperature Group .........................................3-7

3.3 Engine Leaning Assist Mode ...............................3-8

Cessna 350 ............................................................... 3-8

Cessna 400 ............................................................. 3-10

SECTION 4 AUDIO PANEL AND CNS

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

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

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

MFD/PFD Control Unit ................................................ 4-6

4.2 COM Operation ..................................................... 4-8

COM Transceiver Selection and Activation .................... 4-8

COM Transceiver Manual Tuning .................................4-9

Quick-Tuning and Activating 121.500 MHz .................4-11

Auto-Tuning the COM Frequency ...............................4-12

Frequency Spacing ...................................................4-16

Automatic Squelch ...................................................4-17

Volume ................................................................... 4-17

4.3 NAV Operation ....................................................4-18

NAV Radio Selection and Activation ..........................4-18

NAV Receiver Manual Tuning ....................................4-19

Auto-Tuning a NAV Frequency from the MFD .............4-21

Marker Beacon Receiver ........................................... 4-26

4.4 GTX 33 Mode S Transponder .............................4-27

Transponder Controls ...............................................4-27

Transponder Mode Selection .....................................4-28

Entering a Transponder Code ....................................4-31

IDENT Function .......................................................4-32

Flight ID Reporting ..................................................4-33

Garmin G1000 Pilot’s Guide for the Cessna 350/400

190-00552-01 Rev. Dvi

TABLE OF CONTENTS

4.5 Additional Audio Panel Functions ....................4-34

Power-Up ................................................................ 4-34

Mono/Stereo Headsets .............................................4-34

Speaker ..................................................................4-34

Intercom .................................................................4-35

Passenger Address (PA) System .................................4-37

Clearance Recorder and Player ..................................4-37

Split COM ...............................................................4-38

Entertainment Inputs ...............................................4-39

4.6 Audio Panel Preﬂight Procedure ......................4-40

4.7 Abnormal Operation ..........................................4-41

Stuck Microphone ....................................................4-41

COM Tuning Failure ..................................................4-41

Audio Panel Fail-Safe Operation ................................ 4-41

Reversionary Mode ..................................................4-41

SECTION 5 GPS NAVIGATION

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

Navigation Status Box ................................................5-3

5.2 Using Map Displays .............................................. 5-4

Map Orientation ........................................................5-4

Map Range ...............................................................5-6

Map Panning .............................................................5-9

Measuring Bearing and Distance ............................... 5-13

Topography .............................................................5-14

Map Symbols ..........................................................5-17

Airways ..................................................................5-23

Track Vector ............................................................5-25

Wind Vector ............................................................5-26

Nav Range Ring ......................................................5-27

Fuel Range Ring ......................................................5-28

5.3 Waypoints ............................................................5-29

Airports ..................................................................5-30

Intersections ...........................................................5-36

NDBs ......................................................................5-38

VORs ......................................................................5-40

User Waypoints .......................................................5-42

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

5-46

5.5 Direct-to-Navigation ......................................... 5-50

5.6 Flight Planning ....................................................5-55

Flight Plan Creation ................................................. 5-56

Adding Waypoints to an Existing Flight Plan ...............5-59

Adding Airways to a Flight Plan ................................5-61

Adding Procedures to a Stored Flight Plan .................5-63

Flight Plan Storage ..................................................5-69

Flight Plan Editing ...................................................5-72

Along Track Offsets ..................................................5-75

Parallel Track ...........................................................5-77

Activating a Flight Plan Leg ......................................5-80

Inverting a Flight Plan ..............................................5-81

Flight Plan Views ..................................................... 5-82

Closest Point of FPL ................................................. 5-84

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

Altitude Constraints .................................................5-87

5-85

5.8 Procedures ..........................................................5-91

Departures ..............................................................5-91

Arrivals ..................................................................5-94

Approaches ............................................................5-96

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

Trip Planning .........................................................5-102

5-102

5.10 RAIM Prediction ...............................................5-106

5.11 Navigating a Flight Plan ..................................5-109

5.12 Abnormal Operation ........................................ 5-136

SECTION 6 HAZARD AVOIDANCE

6.1 XM Satellite Weather (Optional) ........................6-2

Activating XM Satellite Services ..................................6-2

Using XM SATELLITE Weather Products ........................6-4

Weather Softkeys on the Weather Data Link Page .........6-7

6.2 Terrain Awareness & Warning System (TAWS) 6-28

Displaying TAWS Data ..............................................6-29

TAWS Page .............................................................6-31

TAWS Alerts ............................................................6-33

System Status ..........................................................6-41

6.3 Trafﬁc Information Service (TIS) .......................6-42

Displaying TRAFFIC Data ..........................................6-44

Trafﬁc Map Page ......................................................6-46

TIS Alerts ................................................................6-47

System Status ..........................................................6-48

6.4 Ryan 9900BX Trafﬁc Advisory Systems (TAS)

(Optional) ......................................................................6-51

TAS Symbology ........................................................6-51

Operation ...............................................................6-52

TAS Alerts ...............................................................6-56

System Status ..........................................................6-57

190-00552-01 Rev. D

Garmin G1000 Pilot’s Guide for the Cessna 350/400

vii

TABLE OF CONTENTS

SECTION 7 AUTOMATIC FLIGHT CONTROL SYSTEM

7.1 AFCS Controls .......................................................7-2

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

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

AFCS status box ........................................................7-5

Command Bars ..........................................................7-6

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

7.3 vertical Modes ......................................................7-7

Pitch Hold Mode (PIT) ................................................7-8

Selected Altitude capture Mode (ALTs) .........................7-9

Altitude hold mode (alt) ...........................................7-10

Vertical Speed Mode (VS) .........................................7-11

Flight Level Change Mode (FLC) ................................7-12

Vertical Navigation Modes (VPTH, ALTV) ....................7-14

Glidepath Mode (GP) (waas only) ..............................7-19

Glideslope Mode (GS) ..............................................7-20

Go Around (GA) Mode ............................................. 7-21

7.4 lateral Modes ......................................................7-22

Roll Hold Mode (ROL) ..............................................7-23

Heading Select Mode (HDG) .....................................7-24

Navigation mode (GPS, VOR, LOC, BC) .......................7-25

Approach mode (GPS, VAPP, LOC) ..............................7-27

7.5 Autopilot Operation ...........................................7-29

Engaging the Autopilot ............................................ 7-29

Control Wheel Steering ............................................7-30

Disengaging the Autopilot ........................................7-30

7.6 Example Procedures ...........................................7-31

Departure ...............................................................7-32

Intercepting a VOR Radial ......................................... 7-34

Flying a Flight Plan/GPS Course ................................7-35

Descent ..................................................................7-36

Approach ................................................................7-40

Go Around/Missed Approach ....................................7-42

7.7 AFCS Annunciations and Alerts ........................7-44

AFCS Status Alerts ...................................................7-44

Overspeed Protection ...............................................7-45

Terminal Procedures Charts ........................................8-8

Chart Options ..........................................................8-18

Day/Night View .......................................................8-24

ChartView Cycle Number and Expiration Date ............8-26

8.3 FliteCharts ...........................................................8-30

FliteCharts Softkeys .................................................8-30

Terminal Procedures Charts ......................................8-31

Chart Options ..........................................................8-39

Day/Night View .......................................................8-42

FliteCharts Cycle Number and Expiration Date ............8-44

8.4 XM Radio Entertainment (Optional) ................8-48

Activating XM Satellite Radio Services .......................8-48

Using XM Radio ......................................................8-50

8.5 Scheduler .............................................................8-54

8.6 Electronic Checklists (Optional) .......................8-56

8.7 Abnormal Operation ..........................................8-59

APPENDICES

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

SD Card Use and Databases ..........................................B-1

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

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

General TIS Information ................................................ E-1

Map Symbols .................................................................. F-1

INDEX

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

SECTION 8 ADDITIONAL FEATURES

8.1 SafeTaxi .................................................................8-1

SafeTaxi Cycle Number and Revision ...........................8-4

8.2 ChartView ..............................................................8-7

ChartView Softkeys ....................................................8-7

Garmin G1000 Pilot’s Guide for the Cessna 350/400

190-00552-01 Rev. Dviii

SECTION 1 SYSTEM OVERVIEW

SYSTEM OVERVIEW

NOTE:

This section is designed to provide an overview of the G1000 Integrated Flight Deck as installed in Cessna

350/400 aircraft. The G1000 is an integrated ﬂight deck system that presents ﬂight instrumentation, position, navigation, communication, and identiﬁcation information to the pilot using ﬂat-panel color displays. The system is distributed across the following Line Replaceable Units (LRUs):

•

GDU 1040

•

GDU 1042/1044

•

GMA 1347

Beacon Receiver

•

GCU 476

•

GIA 63/63W

•

GDC 74

•

GEA 71

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

The Cessna 350/400 is also equipped with a GFC 700 Automated Flight Control System (AFCS), providing the

ﬂight director (FD), autopilot (AP), and manual electric trim (MET) functions of the G1000 System.

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

Primary Flight Display (PFD)

Multi Function Display (MFD)

Audio Panel with Integrated Marker

MFD/PFD Control Unit

Integrated Avionics Units (IAU)

Air Data Computer (ADC)

Engine/Airframe Unit

•

GTX 33

•

GRS 77

(AHRS)

•

GMU 44

•

GDL 69A

•

GSA 81

•

GTA 82

•

GSM 85

Mode S Transponder

Attitude and Heading Reference System

Magnetometer

Data Link Receiver

AFCS Servos

Pitch Trim Adapter

Servo Mounts

190-00552-01 Rev. D

Garmin G1000 Pilot’s Guide for the Cessna 350/400

1-1

SYSTEM OVERVIEW

1.1 LINE REPLACEABLE UNITS

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

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

DISPLAY BACKUP

button; see Section 1.4, System Operation) and communicates

•

GCU 476

– The Control Unit provides MFD/PFD and radio tuning control through an RS-232 digital interface

Garmin G1000 Pilot’s Guide for the Cessna 350/400

190-00552-01 Rev. D1-2

SYSTEM OVERVIEW

•

GIA 63/63W

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

•

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.

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

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

•

GEA 71

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

•

GTX 33

through an RS-232 digital interface.

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

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

190-00552-01 Rev. D

Garmin G1000 Pilot’s Guide for the Cessna 350/400

1-3

SYSTEM OVERVIEW

•

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 1.4, System Operation.

•

GMU 44

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

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

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

•

GDL 69A

– The Data Link Satellite Radio Receiver provides real-time weather information to the G1000 MFD and PFD Inset Map, as well as digital audio entertainment. The Data Link Receiver communicates with the MFD via a HSDB connection. A subscription to XM Satellite Radio Service is required to enable the GDL 69A capability.

•

GSA 81, GTA 82,

and

GSM 85

– The GSA 81 servos are used for automatic control of pitch and roll. The GTA 82 Pitch Trim Adapter works with the existing motor to provide automatic pitch trim. These units interface with each IAU.

The GSM 85 servo mounts are responsible for transferring the output torque of the GSA 81 servo actuators to

the mechanical ﬂight-control surface linkages.

Garmin G1000 Pilot’s Guide for the Cessna 350/400

190-00552-01 Rev. D1-4

GTX 33

Transponder

High-Speed Data Bus (Ethernet)

Reversionary

Control

GEA 71

Engine/Airframe

Unit

GDC 74

Air Data

Computer

OAT

Airspeed

Altitude

rtical Speed

GRS 77

AHRS

Attitude

Rate of Turn

Slip/Skid

GMU 44

Magnetometer

Heading

Reversionary

Control

GMA 1347

Audio Panel

GDU 1040 (PFD)

GDU 1042 (MFD)

GCU 476

Control Unit

GTA 82

Pitch Trim

Adapter

Autopilot Calculations

GSA 81

Pitch Servo

Autopilot Calculations

GSA 81

Roll Servo

Autopilot Calculations

No. 2 GIA 63/63W

Integrated Avionics Unit

System Integration Processors

I/O Processor

VHF COM

VHF NAV/LOC

GPS/WAAS

Glideslope

GPS Output

No. 1 GIA 63/63W

Integrated Avionics Unit

System Inegration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS/W

AAS

Glideslope

GPS Output

SYSTEM OVERVIEW

190-00552-01 Rev. D

Figure 1-1 Basic G1000 System Block Diagram

Garmin G1000 Pilot’s Guide for the Cessna 350/400

1-5

SYSTEM OVERVIEW

High-Speed Data Bus (Ethernet)

No. 2 GIA 63/63W

Integrated Avionics Unit

System Integration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS/W

AAS

Glideslope

GDL 69A

Data Link

Real-time Weather and

Digital Audio Entertainment

(subscription-based service)

Stormscope

Lightning Strike and

Thunderstorm Detection

(optional)

Ryan 9900BX

Provides TAS Information

(optional)

CO Guardian

Carbon Monoxide

Detection

Figure 1-2 G1000 With Optional/Additional Interfaces

NOTE:

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

Garmin G1000 Pilot’s Guide for the Cessna 350/400

190-00552-01 Rev. D1-6

SYSTEM OVERVIEW

1.2 SECURE DIGITAL (SD) CARDS

NOTE:

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

NOTE:

Refer to Appendix B for instructions on updating 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

190-00552-01 Rev. D

Garmin G1000 Pilot’s Guide for the Cessna 350/400

1-7

SYSTEM OVERVIEW

1.3 SYSTEM POWER-UP

NOTE:

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

and emergency power supply operation.

NOTE:

The G1000 System is integrated with the aircraft electrical system and receives power directly from electrical busses. The G1000 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, the MFD/PFD Control Unit, 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 Cessna 350/400

190-00552-01 Rev. D1-8

SYSTEM OVERVIEW

1.4 SYSTEM OPERATION

NOTE:

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

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

The displays are connected together via a single Ethernet bus for high-speed communication. As shown in Figure 1-1, each IAU is connected to the on-side display. This allows the units to share information, enabling true system integration.

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

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

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

190-00552-01 Rev. D

Garmin G1000 Pilot’s Guide for the Cessna 350/400

1-9

SYSTEM OVERVIEW

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

Audio Panel’s red

The

DISPLAY BACKUP B

Reversionary Mode on Both Displays

DISPLAY BACKUP

Button. Pressing this button again deactivates Reversionary Mode.

NAV1 and COM1 (provided by the failed PFD)

Flagged Invalid

utton Activates/Deactivates

Figure 1-7 G1000 Reversionary Mode (Failed PFD)

G1000 SYSTEM ANNUNCIATIONS

When an LRU or an LRU function fails, a large red ‘X’ is typically displayed over the instrument experiencing failed data (Figure 1-8 displays all possible ﬂags and responsible LRUs). The G1000 System alerts the pilot when backup paths are utilized by the LRUs. Upon G1000 power-up, certain instruments remain invalid as equipment begins to initialize. All instruments should be operational within one minute of power-up. If any instrument remains ﬂagged, the G1000 should be serviced by a Garmin-authorized repair facility.

GIA 63/63W

Integrated

Avionics Unit

GEA 71 Engine

Airframe Unit

GIA 63/63W

Integrated

Avionics Unit

GIA 63/63W

Integrated

Avionics Unit

GRS 77 AHRS

GMU 44

Magnetometer

GDC 74 Air

Data Computer

GIA 63/63W

Integrated

Avionics Unit

GDC 74 Air

Data Computer

Figure 1-8 G1000 System Failure Annunciations

Garmin G1000 Pilot’s Guide for the Cessna 350/400

GTX 33 Transponder

GIA 63/63W

Integrated

Avionics Unit

190-00552-01 Rev. D1-10

SYSTEM OVERVIEW

SYSTEM STATUS

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

Viewing LRU information:

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

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

a) Select the LRU Softkey.

Or:

a) Press the MENU Key.

b) With ‘Select LRU Window’ highlighted, press the ENT Key.

3) Use the FMS Knob to scroll through the box to view LRU status information.

190-00552-01 Rev. D

Figure 1-9 Example System Status Page

Garmin G1000 Pilot’s Guide for the Cessna 350/400

1-11

SYSTEM OVERVIEW

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

Additional Features sections for more information about databases.

Viewing database information:

1) Select the AUX - System Status Page.

2) To place the cursor in the ‘Database’ Box, select the DBASE Softkey.

Or:

a) Press the MENU Key.

b) Highlight ‘Select Dbase Window’ and press the ENT Key.

3) Use the FMS Knob to scroll through the box to view database status information.

The G1000 uses aural tones to convey the priority of airframe-speciﬁc alerts. The alerting system’s annunciation

tone may be tested from the System Status Page. Refer to the Appendices for airframe-speciﬁc alerts.

Testing the system annunciation tone:

1) Select the AUX - System Status Page.

2) Select the ANN TEST Softkey.

Or:

a) Press the MENU Key.

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

Garmin G1000 Pilot’s Guide for the Cessna 350/400

190-00552-01 Rev. D1-12

AHRS OPERATION

Attitude/Heading Invalid

available

unavailable

available

unavailable

available

Airspeed Data

Magnetometer

unavailable

available

GPS

AHRS Normal

Operation

AHRS no-

Mag Mode

AHRS no-Mag/

no-Air Mode

Heading Invalid

AHRS

no-GPS

Mode

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.

Figure 1-10 AHRS Operation

Loss of GPS, magnetometer, or air data inputs is communicated to the pilot by message advisory alerts (refer

to Appendix A for speciﬁc AHRS alert information). Any failure of the internal AHRS inertial sensors results in loss of attitude and heading information (indicated by red ‘X’ ﬂags over the corresponding ﬂight instruments).

Two GPS inputs are provided to the AHRS. If GPS information from one of the inputs fails, the AHRS uses

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

If the magnetometer input fails, the AHRS continues to output valid attitude information; however, the

heading output on the PFD is ﬂagged as invalid with a red ‘X’.

Failure of the air data input has no effect on the AHRS output while AHRS is receiving valid GPS information.

Invalid/unavailable airspeed data in addition to GPS failure results in loss of all attitude and heading information.

190-00552-01 Rev. D

Garmin G1000 Pilot’s Guide for the Cessna 350/400

1-13

SYSTEM OVERVIEW

GPS RECEIVER OPERATION

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

Viewing GPS receiver status information:

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

navigating MFD page groups).

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

3) To change the selected GPS receiver:

Select the desired

GPS

Softkey.

Or:

a) Press the MENU Key.

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

Satellite Constellation

Diagram

Satellite Signal

Information

GPS

Receiver

Status

RAIM

Availability

Prediction

Satellite Signal Strength Bars

Figure 1-11 GPS Status Page

Garmin G1000 Pilot’s Guide for the Cessna 350/400

190-00552-01 Rev. D1-14

SYSTEM OVERVIEW

For WAAS-enabled systems, GPS sensor annunciations are most often seen after system power-up when one GPS receiver has acquired satellites before the other or one of the GPS receivers has not yet acquired a WAAS signal. While the aircraft is on the ground, the WAAS signal may be blocked by obstructions causing one GPS receiver to have difﬁculty acquiring a good signal. Also, while airborne, turning the aircraft may result in one of the GPS receivers temporarily losing the WAAS signal. If no failure message exists, check the GPS Status Page and compare the information for GPS1 and GPS2. Discrepancies may indicate a problem.

GPS RECEIVER STATUS

The GPS solution type (ACQUIRING, 2D NAV, 2D DIFF NAV, 3D NAV, 3D DIFF NAV) for the active GPS receiver (GPS1 or GPS2) is shown in the upper right of the GPS Status Page. When the receiver is in the process of acquiring enough satellite signals for navigation, the receiver uses satellite orbital data (collected continuously from the satellites) and last known position to determine the satellites that should be in view. ACQUIRING is indicated as the solution until a sufﬁcient number of satellites have been acquired for computing a solution.

When the receiver is in the process of acquiring a 3D navigational GPS solution, 3D NAV is indicated as the solution until the 3D differential ﬁx has ﬁnished acquisition. Satellite-Based Augmentation System (SBAS) status should be indicated as INACTIVE at this point. When acquisition is complete, the solution status changes to 3D DIFF NAV and SBAS becomes active.

In certain situations, such as when the aircraft is outside or on the fringe of the WAAS coverage area, it may be desirable to disable WAAS (although it is not recommended). When disabled, the SBAS ﬁeld in the GPS Status box indicates DISABLED.

Disabling WAAS (for WAAS-enabled systems):

1) Select the GPS Status Page.

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

3) Press the

4) Press the ENT Key to uncheck the box.

5) Press the FMS Knob to remove the cursor.

FMS

Knob

. ‘WAAS’ is highlighted.

Figure 1-12 Enable/Disable WAAS

190-00552-01 Rev. D

Garmin G1000 Pilot’s Guide for the Cessna 350/400

1-15

SYSTEM OVERVIEW

RAIM PREDICTION

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

The RAIM prediction function also indicates whether RAIM is available at a speciﬁed date and time. RAIM computations predict satellite coverage within ±15 min of the speciﬁed arrival date and time. In most cases performing RAIM prediction is not necessary. However, in some cases, the selected approach may be outside the WAAS coverage area and it may be necessary to perform a RAIM prediction for the intended approach.

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

Predicting RAIM availability:

1) Select the GPS Status Page.

2) Select the RAIM Softkey.

2) Press the

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

4) Enter the desired waypoint and press the ENT Key (refer to Section 1.6 for instructions on data entry).

Or:

a) To use the present position, press the MENU Key.

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

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

5) Enter an arrival time and press the ENT Key.

6) Enter an arrival date and press the ENT Key.

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

FMS

Knob

. The ‘WAYPOINT’ ﬁeld is highlighted.

of the following is displayed:

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

• ‘COMPUTING AVAILABILITY’—RAIM calculation in progress

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

• ‘RAIM NOT AVAILABLE’—RAIM is predicted to be unavailable for the speciﬁed waypoint, time, and date

Garmin G1000 Pilot’s Guide for the Cessna 350/400

190-00552-01 Rev. D1-16

SYSTEM OVERVIEW

SATELLITE INFORMATION

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

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

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

• Hollow signal strength bar—Receiver has found the satellite and is collecting data. Each satellite has a 30-

second data transmission that must be collected (signal strength bar is hollow) before the satellite may be

used for navigation (signal strength bar becomes solid).

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

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

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

Using the current satellite signal information, they system calculates the aircraft’s GPS position, time, altitude, ground speed, and track for the aircraft (displayed below the satellite signal accuracy measurements for reference). The following quantities denote the accuracy of the aircraft’s GPS ﬁx:

• Estimated Position Uncertainty (EPU)—A statistical error indication; the radius of a circle centered on an

estimated horizontal position in which actual position has 95% probability of lying

• Horizontal Dilution of Precision (HDOP)—Measures satellite geometry quality (i.e., number of satellites

received and where they are relative to each other) on a range from 0.0 to 9.9, with lower numbers denoting

better accuracy

• Horizontal and Vertical Figures of Merit (HFOM and VFOM)—Measures of horizontal and vertical position

uncertainty; the current 95% confidence horizontal and vertical accuracy values reported by the GPS

receiver

190-00552-01 Rev. D

Garmin G1000 Pilot’s Guide for the Cessna 350/400

1-17

SYSTEM OVERVIEW

1.5 G1000 CONTROLS

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

PFD/MFD CONTROLS

Figure 1-13 PFD/MFD Controls

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

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

Large (Outer)

Knob

Small (Inner)

Knob

Figure 1-14 Dual Concentric Knob

Garmin G1000 Pilot’s Guide for the Cessna 350/400

190-00552-01 Rev. D1-18

SYSTEM OVERVIEW

NAV VOL/ID Knob

NAV Frequency Transfer Key

NAV Knob

Heading Knob

Joystick

CRS/BARO Knob

COM Knob

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 HSI and synchronize

the Selected Heading to the and current heading

Turn to change map range

Press to activate Map Pointer for map panning

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)

COM Frequency Transfer Key (EMERG)

COM VOL/SQ Knob

Direct-to Key ( )

FPL Key

CLR Key (DFLT MAP)

MENU Key

PROC Key

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

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

190-00552-01 Rev. D

Garmin G1000 Pilot’s Guide for the Cessna 350/400

1-19

SYSTEM OVERVIEW

ENT Key

FMS Knob

(Flight Management System Knob)

Validates/conﬁrms menu 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)

Softkey Selection

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

Keys

ALT Knob

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

thousands, the small knob selects the hundreds)

MFD/PFD CONTROL UNIT

The MFD/PFD Control Unit is a pedestal-mounted user interface allowing for ease of data entry, PFD/MFD operation, and NAV/COM tuning. Many procedures in this Pilot’s Guide can be performed using the MFD/PFD Control Unit rather than the display bezel controls. Indicators above the PFD, MFD, NAV, and COM keys are illuminated when their respective control mode(s) are selected. The unit is in MFD control mode by default on system power-up.

NAV/COM radio tuning can be accomplished in either PFD or MFD control mode. The appropriate frequency box (refer to Figure 2-1) on the selected display is outlined by a light blue selection box, which ﬂashes for a few seconds to indicate Control Unit activity (refer to the Audio Panel and CNS Section for more information about NAV/COM tuning). Selection of a different display control or radio tuning mode results in cancelation of the previous radio tuning mode.

Figure 1-15 G1000 Control Unit Layout

Garmin G1000 Pilot’s Guide for the Cessna 350/400

190-00552-01 Rev. D1-20

+ 458 hidden pages