Garmin PA32 User Manual

Page 1

Piper

PA32

Page 2

This manual reﬂects the operation of System Software version 0648.05 or later for the Piper PA32. 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: 44/0870.851241 Fax: 44/0870.8501251

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

Website Address: www.garmin.com

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

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

NavData® is a registered trademark of Jeppesen, Inc.; Stormscope® and SkyWatch® are registered trademarks of L-3 Communications; and XM® is a registered trademark of XM Satellite Radio, Inc.

April 2007 Printed in the U.S.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 website at “http://www.garmin.com” or contact Garmin Customer Service at 800-800-1020.

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Garmin G1000 Pilot’s Guide for Piper PA32

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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 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:

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:

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

WARNING:

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

WARNING:

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

WARNING:

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

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

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Page 5

WARNINGS, CAUTIONS, AND NOTES

WARNING:

delays in data transmission and the relative age of the data, NEXRAD weather data should not be used for short-range weather avoidance.

NEXRAD weather data is to be used for long-range planning purposes only. Due to inherent

WARNING:

CAUTION:

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.

CAUTION:

To reduce the risk of unsafe operation, carefully review and understand all aspects of the G1000 Pilot’s Guide documentation and the Piper PA32 Pilot’s Operating Handbook (POH). 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 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”.

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 104X 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.

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WARNINGS, CAUTIONS, AND NOTES

NOTE:

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

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.

Garmin G1000 Pilot’s Guide for Piper PA32

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Record of Revisions

REVISION INFORMATION

Part Number

190-00692-00 190-00692-00 190-00692-00

Revision Date Page Range Description

1 A B

1/15/07 3/15/07

4/4/07

i – I-4

All All

Initial release Production release Editorial changes

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TABLE OF CONTENTS

SECTION 1 SYSTEM OVERVIEW

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

1.2 Line Replaceable Units (LRU) ..............................1-2

1.3 G1000 Controls .....................................................1-7

PFD/MFD Controls .....................................................1-7

Audio Panel Controls .................................................1-9

1.4 Secure Digital (SD) Cards .................................. 1-12

1.5 System Power-up ................................................ 1-13

1.6 System Operation ............................................... 1-14

Normal Display Operation ........................................1-14

Reversionary Display Operation ................................1-14

AHRS Operation ......................................................1-15

G1000 System Annunciations ...................................1-17

Softkey Function ...................................................... 1-17

1.7 Accessing G1000 Functionality ........................1-25

Menus .................................................................... 1-25

MFD Page Groups ....................................................1-25

MFD System Pages ..................................................1-29

1.8 Display Backlighting ..........................................1-38

Automatic Adjustment .............................................1-38

Manual Adjustment .................................................1-38

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, Glideslope, and Glidepath Indicators 2-9

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

Course Deviation Indicator .......................................2-14

2.2 Supplemental Flight Data .................................2-21

Generic Timer .......................................................... 2-21

System Time ............................................................2-22

Outside Air Temperature ...........................................2-23

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 .................................................2-26

2-25

TAWS Annunciations ................................................ 2-27

Altitude Alerting ......................................................2-27

Minimum Descent Altitude/Decision Height Alerting ...2-28

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

2-29

SECTION 3 ENGINE INDICATION SYSTEM

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

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

Engine Temperature Group .........................................3-6

Electrical Group .........................................................3-7

Fuel Calculations Group ............................................. 3-7

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

Lean Display .............................................................3-9

System Display ........................................................3-12

3-8

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

COM Transceiver Manual Tuning .................................4-7

Quick-Tuning and Activating 121.500 MHz ................... 4-8

Auto-Tuning the COM Frequency .................................4-9

Frequency Spacing ...................................................4-13

Automatic Squelch ...................................................4-14

Volume ................................................................... 4-14

4.3 NAV Operation ....................................................4-15

NAV Radio Selection and Activation ..........................4-15

NAV Receiver Manual Tuning ....................................4-16

Auto-Tuning the NAV Frequency ................................4-18

Marker Beacon Receiver ...........................................4-23

DME Tuning (Optional) .............................................4-24

4.4 GTX 33 Mode S Transponder .............................4-25

Transponder Controls ............................................... 4-25

Transponder Mode Selection .....................................4-26

Entering a Transponder Code .................................... 4-28

IDENT Function .......................................................4-30

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

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

Power-Up ................................................................4-32

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

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

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

Passenger Address (PA) System ................................. 4-35

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

Split COM ...............................................................4-36

Entertainment Inputs ...............................................4-37

4.6 Audio Panel Preﬂight Procedure ...................... 4-38

4.7 Abnormal Operation ..........................................4-39

Stuck Microphone .................................................... 4-39

COM Tuning Failure ..................................................4-39

Audio Panel Fail-Safe Operation ................................4-39

Reversionary Mode .................................................. 4-39

SECTION 5 GPS NAVIGATION

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

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

Dead Reckoning ........................................................5-2

Navigation Map Page .................................................5-4

5.3 PFD Inset Map and Windows ............................5-29

Inset Map ............................................................... 5-29

PFD Windows ..........................................................5-31

5.4 Direct-to-Navigation (MFD) ............................. 5-32

Selecting a Direct-to Waypoint .................................. 5-33

Clearing Vertical Constraints ....................................5-34

Specifying a Course to a Waypoint ............................5-35

Canceling Direct-to Navigation ................................5-36

Direct-to Navigation Shortcuts .................................5-37

5.5 Direct-to-Navigation (PFD) ..............................5-40

5.6 Airport Information (MFD) ................................ 5-43

Duplicate Waypoints ................................................5-45

Additional Airport Runway Information ......................5-45

5.7 Intersection Information (MFD) ........................5-47

5.8 NDB Information (MFD) .....................................5-48

5.9 VOR Information (MFD) .....................................5-49

5.10 User Waypoint Information (MFD) ...................5-50

5.11 Nearest Airports (MFD) ......................................5-54

5.12 Nearest Intersections (MFD) .............................5-56

5.13 Nearest NDB (MFD) ............................................ 5-57

5.14 Nearest VOR (MFD) ............................................5-58

5.15 Nearest User Waypoint (MFD) ..........................5-59

5.16 Nearest Airspaces ...............................................5-61

5.17 Nearest Airports (PFD) ....................................... 5-64

5.18 Flight Planning (MFD) .......................................5-66

Airways/Jetways ......................................................5-78

Display of Airways on the Flight Plan Page .................5-86

Vertical Navigation (VNV) .........................................5-91

Navigating an Example Flight Plan ............................5-98

Parallel Track (PTK) ................................................5-121

light Planning (PFD) ...................................... 5-124

5.19 F

Operations ............................................................5-124

5.20 Procedures

Leg Types Supported by the G1000 ..........................5-130

5.21 Procedures

Operations ............................................................5-142

(MFD) ............................................. 5-130

(PFD) .............................................. 5-142

SECTION 6 HAZARD AVOIDANCE

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

Activating Services .....................................................6-1

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

Weather Softkeys .......................................................6-5

Legend .....................................................................6-6

Setting Up the Weather Data Link Page .....................6-24

Setting Up XM Weather on the Navigation Map ......... 6-28

6.2 Stormscope WX-500 Series II Sensor ............... 6-30

Setting Up Stormscope on the Navigation Map ..........6-30

Selecting the Stormscope Page .................................6-34

Stormscope Operation with Loss of Heading Input ......6-36

6.3 Terrain Pro

Requirements ..........................................................6-37

GPS Position and GPS-MSL Altitude ........................... 6-37

Displaying Terrain Proximity Data .............................. 6-38

Terrain Proximity Page ..............................................6-40

Navigation Map Page ...............................................6-42

6.4 TAWS

Requirements ..........................................................6-44

Computing GPS Altitude for TAWS .............................6-44

Using TAWS ............................................................6-45

TAWS Symbols ........................................................6-49

TAWS Alerts ............................................................6-50

6.5 Trafﬁc ...................................................................

Trafﬁc Information Service (TIS) .................................6-58

L-3 SKYWATCH Trafﬁc Advisory System .....................6-66

6.6 Hazard Displays with Loss of GPS Pos

ximity ................................................6-37

..................................................................6-44

6-58

ition .....6-70

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TABLE OF CONTENTS

SECTION 7 AUTOMATIC FLIGHT CONTROL SYSTEM

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

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

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

Day/Night View .......................................................8-23

ChartView Cycle Number and Expiration Date ............8-25

8.3 FliteCharts ...........................................................8-29

FliteCharts Softkeys .................................................8-29

Terminal Procedures Charts ......................................8-30

Chart Options .......................................................... 8-38

Day/Night View .......................................................8-41

FliteCharts Cycle Number and Expiration Date ............8-43

8.4 XM Radio Entertainment (Optional) ................ 8-47

XM Satellite Radio Service ........................................8-47

XM Service Activation ..............................................8-48

Using XM Radio ......................................................8-49

8.5 Abnormal Operation ..........................................8-53

APPENDICES

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

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

Aircraft Alerts ............................................................A-3

TAWS Alerts ..............................................................A-4

TAWS System Status Annunciations .............................A-5

Other G1000 Aural Alerts ...........................................A-5

G1000 System Message Advisories ..............................A-5

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

Jeppesen Databases ...................................................B-1

Garmin Databases .....................................................B-2

B-1

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

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

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

Introduction .............................................................. E-1

TIS vs. TAS/TCAS ........................................................E-1

TIS Limitations ..........................................................E-1

Display Symbols ............................................................. F-1

INDEX

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SYSTEM OVERVIEW

SECTION 1 SYSTEM OVERVIEW

1.1 SYSTEM DESCRIPTION

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

PA32 aircraft. This includes the PA32 R-301 (Saratoga II HP) and the PA32 R-301 T (Saratoga II TC), as well as the PA32-301 FT (Piper 6X) and the PA32-301 XTC (Piper 6XT).

The G1000 system is an integrated ﬂight control system that presents ﬂight instrumentation, position, navigation,

communication, and identiﬁcation information to the pilot through large-format displays. The system consists of the following Line Replaceable Units (LRUs):

•

GDU 1040

•

GDU 1040

•

GIA 63W

•

GDC 74A

•

GEA 71

Primary Flight Display (PFD)

Multi Function Display (MFD)

Integrated Avionics Unit (IAU)

Air Data Computer (ADC)

Engine/Airframe Unit

•

GMU 44

•

GMA 1347

Beacon Receiver

•

GTX 33

•

GDL 69/69A

Magnetometer

Audio System with Integrated Marker

Mode S Transponder

Data Link

•

GRS 77

(AHRS)

A top-level G1000 system block diagram is shown in Figure 1-1. The following equipment is also connected

to the G1000 system and interfaces with the GIA 63W:

• L-3 STORMSCOPE

• L-3 SKYWATCH

• S-TEC System Fifty Five X

• Honeywell

Attitude and Heading Reference System

WX-500 Series II Weather Mapping Sensor

Trafﬁc Advisory System

Autopilot

KN 63 DME Transceiver

KR 87 ADF Receiver

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SYSTEM OVERVIEW

1.2 LINE REPLACEABLE UNITS (LRU)

•

GDU 1040

is conﬁgured as a PFD and the right display is conﬁgured as an MFD. The GDU 1040 links and displays all functions of the G1000 system during ﬂight. The displays communicate with each other through a High-Speed Data Bus (HSDB) Ethernet connection. Each display is also paired via an Ethernet connection with a GIA 63W Integrated Avionics Unit.

•

GIA 63W

a GPS receiver, VHF COM/NAV/GS receivers, a ﬂight director (FD) and system integration microprocessors. The GIA 63W also contains a GPS WAAS receiver. Each GIA is paired with a respective GDU 1040 display through Ethernet. The GIAs are not paired together and do not communicate with each other directly.

– The GDU 1040 features a 10.4-inch LCD display with 1024 x 768 resolution. The left display

(2) – Functions as the main communication hub, linking all LRUs with the PFD. Each GIA 63W contains

•

GDC 74A

altitude, airspeed, vertical speed, and OAT information to the G1000 system, and it communicates with the GIA 63W, GDU 1040, and GRS 77 using an ARINC 429 digital interface. The GDC 74A also interfaces directly with the GTP 59. The GDC 74A is designed to operate in Reduced Vertical Separation Minimum (RVSM) airspace.

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

1-2

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SYSTEM OVERVIEW

•

GEA 71

with both GIA 63Ws using an RS-485 digital interface.

•

GRS 77

GIA 63W. The GRS 77 contains advanced sensors (including accelerometers and rate sensors) and interfaces with the on-side GMU 44 to obtain magnetic ﬁeld information, with the GDC 74A to obtain air data, and with both GIAs to obtain GPS information. AHRS modes of operation are discussed later in this document.

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

(1) – Provides aircraft attitude and heading information via ARINC 429 to both the GDU 1040 and the

•

GMU 44

magnetic heading. This unit receives power directly from the GRS 77 and communicates with the GRS 77 using an RS-485 digital interface.

•

GMA 1347

beacon controls. The GMA 1347 also controls manual display reversionary mode (red button) and is installed between the MFD and the PFD. The GMA 1347 communicates with both GIA 63Ws using an RS-232 digital interface.

(1) – Measures local magnetic ﬁeld. Data is sent to the GRS 77 for processing to determine aircraft

– The GMA 1347 Audio Panel integrates NAV/COM digital audio, intercom system, and marker

DISPLAY BACKUP

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SYSTEM OVERVIEW

•

GTX 33

The GTX 33 is controlled through the PFD and communicates with both GIA 63Ws through an RS-232 digital interface.

•

GDL 69/69A

(and indirectly, to the inset map of the PFD) as well as optional digital audio entertainment. The GDL 69/69A communicates with the MFD via HSDB connection. A subscription to the XM Satellite Radio service is required to enable the GDL 69/69A capability.

(1) – The GTX 33 is a solid-state, Mode-S transponder that provides Modes A, C, and S operation.

(1) – A satellite radio receiver that provides real-time weather information to the G1000 MFD

•

GSA 81

trim. These units interface with each GIA 63W.

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

mechanical ﬂight-control surface linkage.

(3), and

GSM 85A

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

1-4

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No. 1 GIA 63W

Integrated Avionics Unit

System Inegration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS/WAAS

Glideslope

No. 2 GIA 63W

Integrated Avionics Unit

System Integration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS/WAAS

Glideslope

GTX 33

Transponder

High-Speed Data Bus (Ethernet)

Reversionary

Control

GEA 71

Engine/Airframe

Unit

GDC 74A

Air Data

Computer

OAT

Airspeed

Altitude

rtical Speed

GRS 77

AHRS

Attitude

Rate of Turn

Slip/Skid

GMU 44

Magnetometer

Heading

GPS Output

Reversionary

Control

GMA 1347

Audio Panel

PFD

GDU 1040

S-TEC System

Fifty-Five

Autopilot

MFD

GDU 1040

SYSTEM OVERVIEW

Figure 1-1 Basic G1000 System

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SYSTEM OVERVIEW

High-Speed Data Bus (Ethernet)

No. 2 GIA 63W

Integrated Avionics Unit

System Integration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS

Glideslope

Stormscope

Lightning Strike and

Thunderstorm Detection

(optional)

Honeywell

KR 87

ADF Receiver

(optional)

Honeywell

KN 63

DME Transceiver

(optional)

GDL 69/69A

Data Link

Real-time Weather

Digital Audio Entertainment

S-TEC System

Fifty Five X

Autopilot

L-3

Skywatc

Traffic Avoidance

System

(Optional)

No. 1 GIA 63W

Integrated Avionics Unit

System Integration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS

Glideslope

Figure 1-2 Additional G1000 Interfaces

1-6

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1.3 G1000 CONTROLS

SYSTEM OVERVIEW

NOTE:

The Audio Panel (GMA 1347) is described in the CNS & Audio Panel section. The autopilot controls

are described in the S-TEC System Fifty Five X Autopilot manufacturer’s documentation.

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

and MFD are discussed in the following pages of this section.

PFD/MFD CONTROLS

1 2 4 6

NAV VOL / ID Control

NAV Frequency Transfer Key

Dual NAV Knob

Heading Knob

Joystick

CRS/BARO Knob

Dual COM Knob

COM Frequency Transfer Key

COM VOL/SQ Knob

190-00692-00 Rev. B

Figure 1-3 PFD/MFD Controls

Direct-to Key

FPL Key

CLR Key (DFLT MAP)

Dual FMS Knob

MENU Key

PROC Key

ENTKey

Dual ALT Knob

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SYSTEM OVERVIEW

PFD and MFD controls function the same way, except where indicated.

NAV VOL/ID Knob

Volume level is shown in the ﬁeld as a percentage.

NAV Frequency Transfer Key

Dual

Heading Knob

Joystick

CRS/BARO Knob

NAV Knob

receiver. Press to toggle the tuning cursor (light blue box) between the NAV1 and NAV2 ﬁelds.

– Turn to manually select a heading on the HSI. When pressed, it synchronizes the heading bug with the compass lubber line. Selected heading provides the heading reference to the Flight Director while operating in Heading Select mode.

– Changes the map range (distance top to bottom of map display) when rotated. Activates the map

pointer when pressed.

course. The course is only adjustable when the HSI is in VOR1, VOR2, or OBS/SUSP mode. Pressing this knob centers the CDI on the currently selected VOR. Selected course provides course reference to the Flight Director when operating in Navigation and Approach modes.

– Controls the NAV audio level. Press to toggle the Morse code identiﬁer ON and OFF.

– Transfers the standby and active NAV frequencies.

– Tunes the MHz (large knob) and kHz (small knob) standby frequencies for the NAV

– The large knob sets the altimeter barometric pressure and the small knob adjusts the

Dual COM Knob

– Tunes the MHz (large knob) and kHz (small knob) standby frequencies for the COM transceiver. Pressing this knob toggles the tuning cursor (light blue box) between the COM1 and COM2 ﬁelds.

COM Frequency Transfer Key

– Transfers the standby and active COM frequencies. Pressing and holding this key for two seconds automatically tunes the emergency frequency (121.5 MHz) in the active frequency ﬁeld.

COM

VOL/SQ Knob

– Controls COM audio level. Audio volume level is shown in the ﬁeld as a percentage.

Pressing this knob turns the COM automatic squelch ON and OFF.

Direct-to Key

– Allows the user to enter a destination waypoint and establish a direct course to the selected destination (speciﬁed by the identiﬁer, chosen from the active route, or taken from the map pointer position).

FPL Key

– Displays the active Flight Plan Page for creating and editing the active ﬂight plan, or for accessing

stored ﬂight plans.

CLR

Key (DFLT MAP)

Navigation Map Page immediately, press and hold

Dual FMS Knob

– Used to select the page to be viewed (only on the MFD). The large knob selects a page

– Erases information, cancels an entry, or removes page menus. To display the

CLR

(MFD only).

group (MAP, WPT, AUX, NRST), while the small knob selects a speciﬁc page within the page group. Pressing the small different windows using the small and large while the small

knob turns the selection cursor ON and OFF. When the cursor is ON, data may be entered in the

knobs. The large knob is used to move the cursor on the page,

knob is used to select individual characters for the highlighted cursor location. When the G1000 displays a list that is too long for the display screen, a scroll bar appears along the right side of the display, indicating the availability of additional items within the selected category. Press the small to activate the cursor and turn the large

FMS

Knob to scroll through the list.

FMS

Knob

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SYSTEM OVERVIEW

MENU Key

– Displays a context-sensitive list of options. This list allows the user to access additional features

or to make setting changes that relate to certain pages.

PROC Key

– Selects approaches, departures, and arrivals from the ﬂight plan. If a ﬂight plan is used, available procedures for the departure and/or arrival airport are automatically suggested. If a ﬂight plan is not used, the desired airport and the desired procedure may be selected. This key selects IFR departure procedures (DPs), arrival procedures (STARs), and approaches (IAPs) from the database and loads them into the active ﬂight plan.

ENT Key

– Accepts a menu selection or data entry. This key is used to approve an operation or complete

data entry. It is also used to conﬁrm selections and information entries.

Dual

ALT Knob

– Sets the selected altitude in the box located above the Altimeter. The large knob selects

the thousands, while the small

knob selects the hundreds. Altitude Select is used by the Automatic Flight

Control System in certain modes, in addition to the standard G1000 Altitude Alerter function.

AUDIO PANEL CONTROLS

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Figure 1-4 Audio Panel Controls (GMA 1347)

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SYSTEM OVERVIEW

NOTE:

COM1 MIC

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

– Selects the #1 transmitter for transmitting. COM1 receiver is simultaneously selected when this key is pressed, allowing received audio from the #1 Com receiver to be heard. COM2 receiver audio 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 receiver is simultaneously selected when this key is pressed, allowing received audio from the #2 Com receiver to be heard. COM2 can be deselected by pressing the COM2 Key, or COM1 can be added by pressing the COM1 Key.

COM2

COM3 MIC

COM3

COM 1/2

TEL

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

– Not used.

– Split COM is disabled.

– Not used.

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

is pressed.

SPKR

– Pressing this key selects and deselects the corresponding cockpit speaker. Com and Nav receiver

audio will be heard on the speaker.

MKR/MUTE

– Mutes the currently received Marker Beacon Receiver audio. Unmutes when new marker

beacon audio is received. Also stops play of the Clearance Recorder.

HI SENS

DME

NAV1

ADF

NAV2

AUX

MAN SQ

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

– Pressing turns DME audio on or off.

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

– Pressing turns on or off the audio from the ADF receiver.

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

– Not used.

– 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 audio.

Press again to begin playing the previously recorded memory

block. Each subsequent press of the PLAY Key will begin playing the next recorded block

Key to stop play.

. Press the MKR/MUTE

1-10

PILOT

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

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SYSTEM OVERVIEW

COPLT

PILOT Knob

illuminated. Turn to adjust intercom volume or squelch. The MAN SQ Key must be selected to allow squelch adjustment.

PASS Knob

selected to allow squelch adjustment.

Reversionary Mode Button

– 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

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

– Pressing manually selects Reversionary Mode.

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SYSTEM OVERVIEW

1.4 SECURE DIGITAL (SD) CARDS

NOTE:

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

NOTE:

Refer to Appendix B for instructions on updating databases.

The PFD and MFD data card slots use Secure Digital (SD) cards and are located on the upper right side of the display bezels. Each display bezel is equipped with two SD card slots. SD cards are used for aviation database and system software updates as well as terrain database storage.

Installing an SD card:

1) Insert the SD card in the SD card slot (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 1-5 Display Bezel SD Card Slots

1-12

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1.5 SYSTEM POWER-UP

SYSTEM OVERVIEW

NOTE:

See the Pilot’s Operating Handbook (POH) 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 1-6. 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.

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 1-7) 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 1-6 PFD Initialization Figure 1-7 MFD Power-Up Splash Screen

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SYSTEM OVERVIEW

1.6 SYSTEM OPERATION

NOTE:

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

can be adjusted from the remaining display.

The displays are connected together via a single Ethernet bus for high-speed communication.

connected to a single display, as shown in Figure 1-1. This allows the units to share information, enabling true system integration modes and G1000 System Annunciations.

. This section discusses normal and reversionary G1000 display operation, as well as the various AHRS

Each IAU is

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 1-8 Normal Mode

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

1-14

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.

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SYSTEM OVERVIEW

Figure 1-9 Reversionary Mode

If the system fails to detect a display problem, reversionary mode may be manually activated by pressing the Audio Panel’s red Pressing this button again deactivates reversionary mode.

DISPLAY BACKUP

button (refer to the Audio Panel and CNS Section for further details).

Pressing the

button activates/deactivates

DISPLAY BACKUP

reversionary mode

Figure 1-10 DISPLAY BACKUP Button

AHRS OPERATION

NOTE:

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. 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).

Refer to Appendix A for speciﬁc AHRS alert information.

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

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SYSTEM OVERVIEW

Attitude/Heading Invalid

AHRS

no-GPS

Mode

AHRS Normal

Operation

AHRS no-

Mag Mode

AHRS no-Mag/

no-Air Mode

Heading Invalid

available

unavailable

una

ail

available

unavailable

available

Airspeed Data

Magnetometer

unavailable

available

GPS

Figure 1-11 AHRS Operation

GPS INPUT FAILURE

NOTE:

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.

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

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

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 affect 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.

1-16

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G1000 SYSTEM ANNUNCIATIONS

SYSTEM OVERVIEW

NOTE:

For a detailed description of all annunciations and alerts, refer to Appendix A. Refer to the Pilot’s

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

When an LRU or an LRU function fails, a large red ‘X’ is typically displayed on windows associated with the failed data (Figure 1-12 displays all possible ﬂags and responsible LRUs). Upon G1000 power-up, certain windows remain invalid as equipment begins to initialize. All windows should be operational within one minute of power-up. If any window remains ﬂagged, the G1000 System should be serviced by a Garminauthorized repair facility.

GIA 63W

Integrated

Avionics Units

GEA 71 Engine

Airframe Unit

GIA 63W

Integrated

Avionics Unit

GIA 63W

Integrated

Avionics Units

GDC 74A Air

Data Computer

GRS 77 AHRS

GMU 44

Magnetometer

GIA 63W Integrated

Avionics Units

GDC 74A Air

Data Computer

Figure 1-12 G1000 System Failure Annunciations

GTX 33 Transponder

GIA 63W Integrated

Avionics Units

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.

Softkey

Bezel-Mounted Softkeys (Press)

Figure 1-13 Softkeys (Second-Level PFD Conﬁguration)

Softkey Names

(Displayed)

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SYSTEM OVERVIEW

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 the previous level. The ALERTS Softkey is visible at all softkey levels. The 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

INSET

PFD

OFF

DCLTR (3)

TRAFFIC

TOPO

TERRAIN

STRMSCP

NEXRAD

XM LTNG

DFLTS

WIND

DME

OPTN 1 OPTN 2 OPTN 3

OFF

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

DCLTR (No Declutter): All map features visible

DCLTR-1: Declutters land data

DCLTR-2: Declutters land and SUA data

DCLTR-3: Removes everything except for the active ﬂight plan Displays trafﬁc information on Inset Map Displays topographical data (e.g., coastlines, terrain, rivers, lakes) and

elevation scale on Inset Map Displays terrain information on Inset Map Displays Stormscope information on Inset Map (optional) Displays NEXRAD weather and coverage information on Inset Map

(optional)

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

Displays softkeys to select wind data parameters Longitudinal and lateral components Total direction and speed Total direction with headwind and crosswind speed components Information not displayed Displays/removes DME Information Window (optional)

1-18

BRG1

BRG2

Cycles the Bearing 1 Information Window through:

NAV1 – NAV 1 waypoint frequency or identiﬁer and GPS-derived distance

GPS – GPS waypoint identiﬁer and GPS-derived distance

ADF – ADF Cycles the Bearing 2 Information Window through:

NAV2 – NAV 2 waypoint frequency or identiﬁer and GPS-derived distance

GPS – GPS waypoint identiﬁer and GPS-derived distance

ADF – ADF

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SYSTEM OVERVIEW

VOR1

VOR2

GPS

DME

ALERTS

OBS

CDI

DME

XPDR

IDENT

TMR/REF

NRST

ALT UNIT

STD BARO

STBY

ALT

GND

VFR

CODE

IDENT

METERS

HPA

0 — 7

IDENT

BKSP

Displays softkeys for setting the altimeter and BARO settings to metric units Displays altimeter in meters Displays the BARO setting as inches of mercury Displays the BARO setting as hectopascals Sets barometric pressure to 29.92 in Hg (1013 hPa if HPA softkey is

selected)

Selects OBS mode on the CDI when navigating by GPS (only available with

active leg) Cycles through GPS, VOR1, and VOR2 navigation modes on the CDI Displays the DME Tuning Window, allowing selection of the DME 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) Allows manual selection of ground mode in certain conditions Automatically enters the VFR code (1200 in the U.S.A. only) Displays transponder code selection softkeys 0-7 Use numbers to enter code Activates the Special Position Identiﬁcation (SPI) pulse for 18 seconds,

identifying the transponder return on the ATC screen 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 Activates the Special Position Identiﬁcation (SPI) pulse for 18 seconds,

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

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Figure 1-14 Top Level PFD Softkeys

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SYSTEM OVERVIEW

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

ALERTSSTRMSCP

DME

ALERTS

Press the STD BARO or BACK Softkey to return to

the top-level softkeys

BRG2 (NAV2)

BRG2 (GPS)

BRG2 (OFF

)

BRG1 (NAV1

)

BRG1 (GPS)

BRG1 (OFF

)

DME

ALT UNIT

METERS IN HPA

DME

ALERTS

Figure 1-15 INSET Softkeys

1-20

Figure 16 PFD Conﬁguration Softkeys

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

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

ALERTS

DME

ALERTS

PFD IN REVERSIONARY MODE

SYSTEM OVERVIEW

Figure 1-17 Transponder Softkeys

In the event of a display failure, the G1000 System automatically switches to reversionary mode. The following information indicates G1000 data that displays differently in reversionary mode. All other critical ﬂight data displays in the same format as in normal operating mode and is discussed in other sections of the

System Overview.

ENGINE

LEAN

CYL SLCT

Displays the LEAN and SYSTEM Softkeys Displays the CYL SLCT Softkey to facilitate engine leaning The Cylinder Select Softkey cycles through selection of each

cylinder indicated by changing the cylinder display to light blue

SYSTEM

Displays the DEC FUEL, INC FUEL, and RES FUEL

Softkeys

DEC FUEL INC FUEL RST FUEL

Decreases gallons remaining by one gallon for each press Increases gallons remaining by one gallon for each press Resets fuel used to zero and gallons remaining to full

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SYSTEM OVERVIEW

ALERTS

ENGINE

BACK

LEAN

SYSTEM

CYL SLCT

ALERTS

ENGINE

BACK

LEAN

SYSTEM

DEC FUEL

INC FUEL

RST FUEL

Press the ENGINE Softkey on this level to return to the previous page level.

Press the

ENGINE Softkey on this level to return to the previous page level.

Press the BACK Softkey on any level to return to the default page level.

DME

ALERTS

ENGINE

ALERTS

ENGINE

BACK

LEAN

SYSTEM

Figure 1-18 Softkeys in Reversionary Mode

1-22

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SYSTEM OVERVIEW

MFD SOFTKEYS

The MFD softkeys allow controlling and viewing of many functions, including engine instruments, fuel system data, GPS, comunication, navigation, ﬂight planning, terrain, trafﬁc, and weather. Each softkey sublevel has a visible at all softkey levels. The label changes if messages are issued.

BACK Softkey which can be selected to return to the previous level. The ALERTS Softkey is

NAVIGATION MAP PAGE

ENGINE

MAP

DCLTR (3)

DEC FUEL INC FUEL RST FUEL

TRAFFIC TOPO

TERRAIN AIRWAYS

STRMSCP NEXRAD

XM LTNG

Pressing this softkey makes the

RST FUEL

Decreases gallons remaining by one gallon for each press Increases gallons remaining by one gallon for each press Pressing the

gallons remaining to full Enables second-level Navigation Map softkeys Displays trafﬁc information on Navigation Map Displays topographical data (e.g., coastlines, terrain, rivers,

lakes) and elevation scale on Navigation Map Displays terrain information on Navigation Map Cycles through choices of airway information

AIRWY ON – Displays all airways

AIRWY LO – Displays low altitude airways only

AIRWY ON – Displays high altitude airways only Displays/removes Stromscope lightning data Displays NEXRAD weather and coverage information on

Navigation Map (optional feature) Displays XM lightning information on Navigation Map

(optional feature) Selects desired map detail; cycles through declutter levels:

softkeys available

RST FUEL

Softkey resets fuel used to zero and

DEC FUEL, INC FUEL

, and

SHW CHRT

190-00692-00 Rev. B

DCLTR (No Declutter): All map features visible

DCLTR-1: Declutters land data

DCLTR-2: Declutters land and SUA data

DCLTR-3: Removes everything except for the active ﬂight

plan When available, displays optional airport and terminal

procedures charts

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SYSTEM OVERVIEW

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

(optional) (optional)

(optional)

ENGINE

MAP

DCLTR

SHW CHRT

DCLTR-1

DCLTR-2

DCLTR-3

TRAFFIC

TOPO

TERRAIN

AIRWAYS

STRMSCP

NEXRAD

XM LTNG

BACK

ENGINE

DEC FUEL

INC FUEL

RST FUEL

Press the ENGINE Softkey on this level to return to the top softkey level.

Figure 1-19 MFD Softkeys

1-24

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SYSTEM OVERVIEW

1.7 ACCESSING G1000 FUNCTIONALITY

MENUS

The G1000 has a MENU Key that, when pressed, displays a context-sensitive list of options. This options list allows the user to access additional features or make settings changes which speciﬁcally relate to the currently displayed window/page. There is no all-encompassing menu. Some menus provide access to additional submenus that are used to view, edit, select, and review options. Menus display ‘NO OPTIONS’ when there are no options for the window/page selected. The main controls used in association with all window/page group operations are described in section 1.3. Softkey selection does not display menus or submenus.

Navigating the Page Menu Window:

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

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

when the option list is longer than the window).

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

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

removes the displayed menu.

No Options with

NRST Window

Displayed on the

PFD

Options

with FPL

Window

Displayed

Figure 1-20 Page Menu Examples

MFD PAGE GROUPS

NOTE:

speciﬁc pages.

Refer to the GPS Navigation, Hazard Avoidance, and Additional Features sections for details on

The page group and active page title box are displayed in the upper center of the screen, below the Navigation Data Box.

190-00692-00 Rev. B

Page Group Active Page Title

Figure 1-21 Page Title Box

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SYSTEM OVERVIEW

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

placement of the current page within the group are indicated.

Page Groups

Figure 1-22 Page Group Icons

Pages in Current Group

Selected Page

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

on the conﬁguration of optional equipment.

Selecting a page using the FMS Knob:

1) Turn the

Turn

large FMS

the

small FMS

Knob until the desired page group is selected.

Knob until the desired page is selected.

There are also several pages (Airport Information and XM Information screens) which are selected ﬁrst from

within a main page group with the

FMS Knobs, then with the appropriate softkey at the bottom of the page. In

this case, the page remains set to the selected screen until a different screen softkey is pressed.

Map Pages (MAP)

Navigation Map

Trafﬁc Map

Stormscope

Weather Data Link

(service optional)

Terrain Proximity/TAWS

Figure 1-23 Map Pages

1-26

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Waypoint Pages (WPT)

Airport Information screens

SYSTEM OVERVIEW

- Airport Information

(INFO softkey)

- Departure Information

(DP softkey)

- Arrival Information

(STAR softkey)

- Approach Information

(APR softkey)

- Weather Information

(WX softkey)

Intersection Information

NDB Information

VOR Information

User Waypoint Information

Airport

Information

Screens

Figure 1-24 Waypoint Pages

Auxiliary Pages (AUX)

Trip Planning

Utility

GPS Status

System Setup

XM Satellite screens

- XM Information

(INFO softkey)

- XM Radio

(RADIO softkey)

System Status

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Figure 1-25 Auxiliary Pages

Garmin G1000 Pilot’s Guide for Piper PA32

Satellite Screens

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SYSTEM OVERVIEW

Nearest Pages (NRST)

Nearest Airports

Nearest Intersections

Nearest NDB

Nearest VOR

Nearest User Waypoints

Nearest Frequencies

Nearest Airspaces

Figure 1-26 Nearest Pages

In addition to the main page groups accessed exclusively using the planning (FPL) and loading procedures (PROC) which are accessed by bezel key. In some instances, softkeys may be used to access the Procedure Pages.

The Flight Plan Pages are accessed using the by turning the small FMS Knob.

The Procedure pages may be accessed at any time on the MFD by pressing the initialized, and when a departure, approach, or arrival is selected, the appropriate Procedure Loading Page is opened. Turning the FMS Knob does not scroll through the Procedure pages (note the single page icon in the lower right corner).

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

FMS Knobs, there are pages for ﬂight

PROC Key. A menu is

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Flight Plan Pages (FPL)

Active Flight Plan

- Wide View, Narrow View (VIEW softkey)

Flight Plan Catalog

SYSTEM OVERVIEW

- Stored Flight Plan ( softkey)

Procedure Pages

(PROC)

Departure Loading

Arrival Loading

Approach Loading

NEW

Figure 1-27 Flight Plan Pages

Figure 1-28 Procedure Pages

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

page may change while the page icon remains the same.

MFD SYSTEM PAGES

In the Auxiliary (AUX) Page Group, there are two system pages: System Setup (page 5 of 6) and System Status (page 6 of 6). The System Setup Page allows management of various system parameters, while the System Status Page displays the status of all G1000 System LRUs.

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SYSTEM OVERVIEW

SYSTEM SETUP PAGE

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

• Time display format (local or UTC )

• Displayed measurement units

• Airspace alerts

• Audio alert voice

• MFD Data Bar ﬁelds

Selecting the System Setup Page:

1) Turn the large FMS Knob to select the AUX Page group.

2) Turn the small FMS Knob to display the System Setup Page.

• GPS Course Deviation Indicator (CDI) range

• COM transceiver channel spacing

• Displayed nearest airports

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Figure 1-29 System Setup Page

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.

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SYSTEM OVERVIEW

Creating a proﬁle:

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

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

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

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

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

cannot begin with a blank as the ﬁrst letter.

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 AUX - System Setup Page.

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

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

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

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

Renaming a proﬁle:

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

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

3) Turn the large FMS Knob to highlight ‘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.

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

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

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

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SYSTEM OVERVIEW

Deleting a proﬁle:

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

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

3) Turn the large FMS Knob to highlight ‘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 Date/Time Box on 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. The time offset is used to deﬁne current local time. UTC (also called “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.

Setting the system time format:

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

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

3) Turn the small FMS Knob to select the desired system time format (local 12hr, local 24hr, UTC) and press the ENT Key.

Setting the current time offset:

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

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

3) Turn the FMS Knobs to enter the time offset and press the ENT Key.

DISPLAY UNITS

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

the following displayed data:

• Nav angle (auto, true)

Affects the BRG ﬁeld in the PFD Navigation Status Box.

Affects the BRG, DTK, TKE, TRK, and XTK ﬁelds in the MFD Navigation Status Box.

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When set to ‘AUTO’, magnetic variation is ﬁgured into the displayed value. When ‘TRUE’ is selected,

no magnetic variation is calculated and a ‘T’ is displayed next to the value.

• Distance and speed (metric, nautical)

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SYSTEM OVERVIEW

Affects the DIS ﬁeld in the PFD Navigation Status Box and the range setting of the Inset Map.

Affects all distance and speed displays on the MFD with the exception of the displayed wind speed

displayed on the Navigation Map Page. Wind speed is affected on the Trip Planning Page.

• Altitude and vertical speed (feet, meters)

Affects the Altitude and Vertical Speed References in the AFCS Status Box on the PFD.

Affects all altitude and elevation displays on the MFD, with the exception of VNAV altitudes on the

Active Flight Plan Page.

• Barometric pressure (inches of mercury, hectopascals)

Affects the altimeter setting on the PFD and the pressure display on the Trip Planning Page.

• Temperature (Celsius, Fahrenheit)

Affects all temperature displays on the PFD.

Affects the temperature display on the Trip Planning Page. Does not affect the Engine Indicating

System display.

• Fuel and fuel ﬂow (pounds, kilograms)

Affects all fuel and fuel ﬂow displays.

• Weight (pounds, kilograms)

Affects aircraft weights on the Weight Planning Page.

• Position (HDDD°MM.MM’, HDDD°MM’SS.S”)

Affects all position displays.

Changing a display unit setting:

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

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

3) Turn the small FMS Knob to select from a list of measurement units and press the ENT Key when the desired

unit is highlighted. Press the CLR Key to cancel the action without changing the units.

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 MFD 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

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• Restricted

• MOA (Military)

• Other airspaces

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SYSTEM OVERVIEW

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

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

3) Turn the FMS Knobs to enter an altitude buffer value and press the ENT Key.

Turning an airspace alert on or off:

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

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

3) 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.

Enabling/disabling an arrival alert:

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

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

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

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

Changing the arrival alert trigger distance:

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

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

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

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

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SYSTEM OVERVIEW

AUDIO ALERTS

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

Changing the audio alert voice:

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

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

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

MFD DATA BAR FIELDS

The MFD Data Bar Fields Box on the System Setup Page displays the current conﬁguration of the MFD Navigation Status Box. By default, the Navigation Status Bar is set to display ground speed (GS), distance to next waypoint (DIS), estimated time en route (ETE), and en route safe altitude (ESA).

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

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

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

3) Turn the small FMS Knob to display and scroll through the data options list and press the ENT Key when the

desired data selection is highlighted.

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

• Bearing (BRG)

• Distance (DIS)

• Desired Track (DTK)

• En Route Safe Altitude (ESA)

• Estimated Time of Arrival (ETA)

• Estimated Time En Route (ETE)

• Ground Speed (GS)

• Minimum Safe Altitude (MSA)

• True Air Speed (TAS)

• Track Angle Error (TKE)

• Track (TRK)

• Vertical Speed Required (VSR)

• Crosstrack Error (XTK)

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 2.0 nm beyond 30 nm from the departure airport. The CDI range is set to 2.0 nautical miles during the en route phase of ﬂight. Within 31 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, or less using angular scaling. This transition normally occurs within 2.0 nm of the ﬁnal approach ﬁx (FAF) and the desired track is within 45 degrees of the IAF to FAF segment.

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SYSTEM OVERVIEW

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 en route and terminal phases and ramps down to the proper scaling during an approach.

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

• Selected CDI range (auto, 2 nm, 1 nm, 0.3 nm)

• Current system CDI range (2 nm, 1 nm, 0.3 nm)

Refer to the Course Deviation Indicator discussion in the Flight Instruments section for a more detailed discussion of CDI scaling.

Changing the CDI range:

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

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

3) Turn the small FMS Knob to display and scroll through the range list and press the ENT Key when the desired

selection is highlighted.

COM CONFIGURATION

NOTE

8.33 kHz VHF communication frequency channel spacing is not approved for use in the United States.

Select the 25.0 kHz channel spacing option for use in the United States.

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

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

3) Turn the small FMS Knob to select the desired spacing and 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 zero 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) While on the System Setup Page, press the FMS Knob momentarily to activate the ﬂashing cursor.

1-36

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

3) Turn the small FMS Knob to display and scroll through the runway options (any, hard only, hard/soft, water) and press the ENT Key when the desired selection is highlighted.

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SYSTEM OVERVIEW

Selecting nearest airport minimum runway length matching criteria:

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

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

3) Turn the FMS Knobs to enter the minimum runway length (zero to 99,999 feet) and press the ENT Key.

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 Piper service center or Garmin dealer informed.

Figure 1-30 Example System Status Page

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

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

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1.8 DISPLAY BACKLIGHTING

The G1000 display and control backlighting can be adjusted either automatically or manually.

AUTOMATIC ADJUSTMENT

The existing instrument panel dimmer bus normally controls the PFD and MFD backlighting as well as the PFD and MFD bezels, MFD Control Unit, AFCS Control Unit and audio panel key annunciator lighting. When the dimmer bus is not used by the G1000 system, photocell technology automatically controls backlighting adjustments. Photocell calibration curves are pre-conﬁgured to optimize display appearance through a broad range of cockpit lighting conditions.

MANUAL ADJUSTMENT

NOTE:

The avionics dimming knob may also be used to adjust backlighting. Refer to the POH for details.

NOTE:

In normal mode, backlighting can only be adjusted from the PFD. In reversionary mode, it can also

be adjusted from the MFD.

NOTE:

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

Backlighting may also be adjusted manually for all of the displays and the associated bezels. The audio panel key backlighting is directly tied to the PFD key backlighting setting.

Adjusting display backlighting manually:

1) Press the

Key on the PFD to display the PFD Setup Menu Window. ‘AUTO’ becomes highlighted to the

right of ‘PFD DSPL’.

Figure 1-31 Manual Display Backlighting Adjustment

2) Turn the small

ENT

Key. The intensity value becomes highlighted.

FMS

Knob to display the selection box. Turn the

FMS

Knob to select ‘MANUAL’, then press the

1-38

3) Turn the small

Turn the large FMS Knob to highlight ‘AUTO’ to the right of ‘MFD DSPL’ and repeat steps 2 and 3.

5) Press the

CLR

FMS

Knob to select the desired backlighting, then press the

Key to remove the PFD Setup Menu Window from the display.

ENT

Key.

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Adjusting key backlighting manually:

SYSTEM OVERVIEW

1) Press the

Key on the PFD to display the PFD Setup Menu Window. ‘AUTO’ becomes highlighted to the

right of ‘PFD DSPL’.

2) Turn the large

FMS

Knob to highlight ‘PFD DSPL’. Turn the small

arrowhead to display ‘PFD KEY’.

3) Turn the large

4) Turn the

5) Turn the small

6) Turn the large

FMS

Knob to highlight ‘AUTO’ and turn the small

FMS

Knob to select ‘MANUAL’, then press the

FMS

Knob to select the desired backlighting, then press the

FMS

Knob to highlight ‘MFD DSPL’ and turn the small

arrowhead to display ‘MFD KEY’.

Figure 1-32 Manual Key Lighting Adjustment

FMS

Knob to display the selection box.

ENT

Key. The intensity value becomes highlighted.

Knob in the direction of the green

ENT

Key.

FMS

Knob in the direction of the green

7) Repeat steps 3 to 5.

8) Press the

CLR

Key to remove

the PFD Setup Menu Window from the display.

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SYSTEM OVERVIEW

BLANK PAGE

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SECTION 2 FLIGHT INSTRUMENTS

FLIGHT INSTRUMENTS

WARNING:

to the backup instruments.

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

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

• Airspeed Indicator, showing

– True airspeed

– 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

• Glideslope, Glidepath, and Vertical Deviation Indicators

• Vertical Speed Indicator (VSI)

• Horizontal Situation Indicator, showing

– Turn Rate Indicator

– Bearing pointers and

information windows

– DME Information Window

• Course Deviation Indicator (CDI)

• Generic timer

• System time

• Outside air temperature (OAT)

• Wind data

• Vertical Navigation indications

The PFD also displays various alerts and annunciations.

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NAV Frequency Box

Airspeed Indicator

True Airspeed

Current Heading

Current Track Bug

Course Deviation Indicator (CDI)

Horizontal Situation Indicator (HSI)

Outside Air Temperature (OAT)

Softkeys

System Time

Transponder Status Box

Figure 2-1 Primary Flight Display (Default)

Selected Heading Bug

Turn Rate Indicator

Barometric Altimeter Setting

Vertical Speed Indicator (VSI)

Selected Altitude Bug

Altimeter

Selected Altitude

COM Frequency Box

Navigation Status Box

Slip/Skid Indicator

Attitude Indicator

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Trafﬁc Annunciation

Vspeed Reference

Selected Heading

Wind Data

Inset Map

DME Information Window

Bearing Information Windows

Flight Plan Window

Minimum Descent Altitude/Decision Height

Annunciation Window

Selected Course

Current Vertical Speed

Glideslope Indicator

Marker Beacon Annunciation

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Figure 2-2 Primary Flight Display (Additional Information)

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2.1 FLIGHT INSTRUMENTS

AIRSPEED INDICATOR

NOTE:

Refer to the Pilot’s Operating Handbook (POH) for speed criteria and Vspeed values.

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

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

The numeric labels and major tick marks on the moving tape are marked at intervals of 10 knots, while minor tick marks on the moving tape are indicated at intervals of 5 knots. Speed indication starts at 20 knots, with 60 knots of airspeed viewable at any time. The actual airspeed is displayed inside the black pointer. The pointer remains black until reaching never-exceed speed (V

Airspeed Trend Vector

Vspeed References

Actual Airspeed

Speed Ranges

True Airspeed

), at which point it turns red.

Figure 2-4 Red Pointer at V

Figure 2-3 Airspeed Indicator

A color-coded (white, green, yellow, and red) speed range strip is located on the moving tape. The colors denote ﬂaps operating range, normal operating range, caution range, and never-exceed speed (V

). A red range

is also present for low speed awareness.

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 V

, 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.

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FLIGHT INSTRUMENTS

Vspeeds (Glide, VR, VX, and VY) can be changed and their ﬂags turned on/off from the Timer/References Window (Figure 2-5). 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 ﬂags on/off:

1) Press the

2) Turn the

TMR/REF

large FMS

Softkey.

Knob to highlight the desired Vspeed.

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

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

4) Press the

5) Turn the

6) To remove the window, press the

Figure 2-5 Timer/References Window (Model 206)

ENT

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

small FMS

Knob clockwise to ON or counterclockwise to OFF.

CLR

Key or the

TMR/REF

Softkey.

Figure 2-6 Timer/References Menu

Turning all Vspeed ﬂags ON/OFF:

1) Press the

2) Press the

3) To view all Vspeed ﬂags, highlight ‘All References On’ and press the

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

TMR/REF

Key.

Softkey.

ENT

Key (Figure 2-6).

ENT

Restoring all Vspeed defaults:

1) Press the

2) Press the

3) Turn the

4) Press the

TMR/REF

FMS

ENT

Softkey.

Key.

Knob to highlight ‘Restore Defaults’.

Key.

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ATTITUDE INDICATOR

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

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

Roll Pointer

Roll Scale

Horizon Line

Aircraft Symbol

Land Representation

Pitch Scale

Slip/Skid Indicator

Sky Representation

Roll Scale Zero

Figure 2-7 Attitude Indicator

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

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

Figure 2-9 Slip/Skid Indication

Nose High Nose Low

Figure 2-8 Pitch Attitude Warnings

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 laterally away from the pointer to indicate lateral acceleration (slip/skid). One bar displacement from the roll pointer is equivalent to one ball displacement on a traditional Slip/Skid Indicator.

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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.

The Selected Altitude is displayed above the Altimeter in the box indicated by a selection bug symbol. A bug corresponding to this altitude is shown on the tape; if the Selected Altitude exceeds the range shown on the tape, the bug appears at the corresponding edge of the tape. The metric value, when selected, is displayed in a separate box above the Selected Altitude.

Setting the Selected Altitude:

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

increments).

The minimum descent altitude/decision height (MDA/DH) value is also available for the Selected Altitude.

Selected Altitude

Selected Altitude Bug

Altitude Trend Vector

Minimum Descent Altitude/

Decision Height Bug

Current Altitude

Barometric Setting

Figure 2-11 Altimeter (Metric)Figure 2-10 Altimeter

Selected and current altitudes can also be displayed in meters (readouts displayed above the normal readouts

in feet; Figure 2-11). Note that the altitude tape does not change scale.

Displaying altitude in meters:

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

2) Press the ALT UNIT Softkey.

3) Press the METERS Softkey to turn on metric altitude readouts (see Figure 2-11).

4) Press the

BACK

Softkey to return to the top-level softkeys.

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.

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

Selecting the Altimeter barometric 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.

Changing altimeter barometric pressure setting units:

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

2) Press the ALT UNIT Softkey.

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

Or, press the HPA Softkey to display the barometric pressure setting in hectopascals (hPa; see Figure 2-11).

4) Press the

BACK

Softkey to return to the top-level softkeys.

VERTICAL SPEED INDICATOR (VSI)

The Vertical Speed Indicator (VSI, Figure 2-12) displays the aircraft vertical speed using a non-moving tape labeled at 1000 and 2000 fpm with minor tick marks every 500 fpm. The current vertical speed is displayed in the pointer along the tape. Digits appear in the pointer when the climb or descent rate is greater than 100 fpm. If the rate of ascent/descent exceeds 2000 fpm, the pointer appears at the corresponding edge of the tape and the rate appears inside the pointer.

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

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FLIGHT INSTRUMENTS

VERTICAL DEVIATION, GLIDESLOPE, AND GLIDEPATH INDICATORS

The Vertical Deviation Indicator (VDI; Figure 2-12) uses a magenta chevron to indicate the baro-VNV vertical deviation when Vertical Navigation (VNV) is being used; the VDI appears in conjunction with the “TOD within 1 minute” alert. The VDI is removed from the display if vertical deviation becomes invalid. See the GPS Navigation Section for details on VNV features, and refer to Section 2.2, Supplemental Flight Data, for more information about VNV indications on the PFD.

The Glideslope Indicator (Figure 2-13) appears to the left of the Altimeter whenever an ILS frequency is tuned in the active NAV ﬁeld. A green diamond acts as the Glideslope Indicator, like a glideslope needle on a conventional indicator. If a localizer frequency is tuned and there is no glideslope, “NO GS” is annunciated.

The glidepath is analogous to the glideslope for GPS approaches supporting WAAS vertical guidance (LNAV+V, L/VNV, LPV) and is generated by the system to reduce pilot workload during approach. When an approach of this type is loaded into the ﬂight plan and GPS is the selected navigation source, the Glidepath Indicator (Figure 2-14) appears as a magenta diamond. If the approach type downgrades past the ﬁnal approach ﬁx (FAF), “NO GP” is annunciated.

Full-scale deﬂection (two dots) is 1000 feet.

Vertical

Deviation

Indicator

Deviation Indicators (VSI and VDI)

VNV Target Altitude

Vertical Speed Indicator

Required Vertical Speed

Vertical Speed Pointer

Figure 2-12 Vertical Speed and

Marker Beacon

Annunciation

Glideslope

Indicator

Figure 2-13 Glideslope Indicator

Glidepath

Indicator

Figure 2-14 Glidepath Indicator

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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 in a 360˚ compass-rose format.

The HSI contains a Course Deviation Indicator (CDI) with a course pointer arrow, a To/From arrow, 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

Selected Heading

Current Track Bug

Lateral Deviation Scale

Navigation Source

Aircraft Symbol

Course Deviation Indicator (CDI)

Rotating Compass Rose

To/From Indicator

Course Pointer

Heading Bug

Flight Phase

Selected Course

Turn Rate/Heading Trend Vector

Current Heading

Lubber Line

Figure 2-15 Horizontal Situation Indicator (HSI)

A digital reading of the current heading appears on top of the HSI. The current track is represented on the HSI by a magenta diamond bug. To the upper left of the HSI, the Selected Heading is shown in light blue; the light blue bug on the compass rose corresponds to the Selected Heading. The Selected Course is shown to the upper right of the HSI. The color of the Selected Course corresponds to the selected navigation source: magenta for GPS or green for NAV (VOR, LOC).

Current Track Bug

Selected Heading Selected Course

Figure 2-16 Heading and Course Indications

Current Heading

Selected Heading Bug

Adjusting the Selected Heading:

Turn the

HDG

Knob to set the Selected Heading on both PFDs.

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

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Adjusting the Selected Course:

FLIGHT INSTRUMENTS

Turn the

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

CRS

Knob to set the Selected Course (for each PFD).

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

The heading displayed on the HSI and all other navigation angles (track, heading, course, bearing) are magnetic when the NAV ANGLE is set to ‘Magnetic’ on the AUX - System Setup Page. When ‘True’ is selected, all navigation angles and the HSI display a ‘T’ next to the angle value (Figure 2-17). When an approach referenced to true north has been loaded into the ﬂight plan, the system generates a message alerting the pilot to switch the NAV ANGLE setting to ‘True’ at the appropriate time.

Figure 2-17 Heading and Course Indications (True)

Changing the navigation angle setting:

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

2) Press the FMS Knob to activate the cursor.

3) Turn the

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

large FMS

Knob to highlight ‘Nav Angle’ in the ‘Display Units’ box (Figure 2-18).

Figure 2-18 System Setup Page,

Navigation Angle Settings

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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. A standard-rate turn is shown on the indicator by the trend vector stopping at the standard turn rate tick mark, corresponding to a predicted heading of 18˚ from the current heading. At rates greater than 4 deg/sec, an arrowhead appears at the end of the magenta trend vector and the prediction is no longer valid (Figure 2-19).

Half-std Turn Rate

BEARING POINTERS AND INFORMATION WINDOWS

Std Turn Rate

Figure 2-19 Turn Rate Indicator and Trend Vector

Arrow Shown for Turn Rate > 4 deg/sec

NOTE:

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

Distances in the Bearing Information windows and GPS bearing pointers turn yellow when operating

in Dead Reckoning Mode.

Two bearing pointers and associated information can be displayed on the HSI by pressing the PFD Softkey

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

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

Information windows (Figure 2-20) 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 bearing source and is tuned to an ILS frequency, the bearing pointer is removed from

the HSI and the frequency is replaced with “ILS”. When NAV1 or NAV2 is the selected bearing source, the frequency is replaced by the station identiﬁer when the station is within range. If GPS is the bearing source, the active waypoint identiﬁer is displayed in lieu of a frequency.

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FLIGHT INSTRUMENTS

Under the following conditions, the bearing pointer is removed from the HSI and “NO DATA” is displayed

in the information window:

• The NAV radio is not receiving the tuned VOR station

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

Selecting bearing display and changing sources:

1) Press the PFD Softkey.

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

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

4) Press the BRG Softkey a third time to change the bearing source to ADF.

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.

The DME Information Window (labeled ‘DME’; see Figure 2-20) is displayed above the BRG1 Information Window and shows the tuning mode (NAV1, NAV2, or HOLD), frequency, and actual DME 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.

Tuning Mode

Frequency

Distance

DME Information Window

Distance to

Bearing Source

Station

Identiﬁer

Bearing 1

Pointer

Bearing 2

Pointer

Waypoint

Selected

Bearing

Source

Bearing 1 Information Window

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Pointer

Icon

Bearing 2 Information Window

Figure 2-20 HSI with Bearing and DME Information

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Pointer

Icon

Bearing

Source

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FLIGHT INSTRUMENTS

COURSE DEVIATION INDICATOR

NOTE:

The GPS CDI is removed from the display when operating in Dead Reckoning Mode.

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. If the course deviation data is not valid, the CDI is not displayed.

Flight Phase

Navigation Source

Scale

Crosstrack Error

CDI

Figure 2-21 Course Deviation Indicator

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

Figure 2-22 Navigation Sources

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Changing navigation sources:

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

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

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

box over the NAV2 standby frequency.

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

GPS

Selected

Pressing the

through Navigation Sources

CDI

Softkey Cycles

The CDI has the same angular limits as a mechanical CDI when coupled to a VOR or localizer (LOC). When coupled to GPS, the full scale limits for the CDI are deﬁned by a GPS-derived distance. If the CDI exceeds the maximum deviation on the scale (two dots) while coupled to GPS, the crosstrack error (XTK) is displayed below the white aircraft symbol.

NAV1 Selected for Tuning

LOC1

Selected

Figure 2-23 Selecting a Navigation Source

NAV2 Selected for Tuning

VOR2

Selected

The system automatically switches from GPS to LOC navigation source and changes the CDI scaling accordingly when all of the following occur:

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

• 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 a Vector-to-Final (VTF; see the GPS Navigation Section) also causes the HSI to switch to LOC navigation source; GPS steering guidance is not provided after this switch.

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GPS CDI SCALING

When GPS is the selected navigation source, the ﬂight plan legs are sequenced automatically and

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

The current GPS CDI scale setting is displayed as ‘System CDI’ on the AUX - System Setup Page and the full-

scale deﬂection setting may also be changed (2.0 nm, 1.0 nm, 0.3 nm, or Auto) from this page (

Changing the selected GPS CDI setting:

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

2) Press the FMS Knob to activate the cursor.

Figure 2-24

3) Turn the

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

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

large FMS

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

Figure 2-24 System Setup Page,

GPS CDI Settings

If the selected scaling is smaller than the automatic setting for enroute and terminal phases, the CDI is

scaled accordingly and the selected setting is be displayed rather than the ﬂight phase annunciation. Receiver Autonomous Integrity Monitoring (RAIM) protection limits follow the selected CDI scale and corresponding ﬂight phases.

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

current phase of ﬂight (Figure 2-25, Table 2-1).

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FLIGHT INSTRUMENTS

2.0 nm

Enroute

(Oceanic if >200 nm

from nearest airport)

0.3 nm

Missed

Approach

1.0 nm

Approach

1.0 nm

Terminal

1.0 nm

Terminal

0.3 nm

Departure

CDI Full-scale Deflection

31 nm from Destination Airport

30 nm from Departure Airport

Refer to accompanying

approach CDI scaling figures

Figure 2-25 Automatic CDI Scaling

• Once a departure procedure is activated, the CDI is scaled for departure (0.3 nm).

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

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

If the next leg in the departure procedure is not a CA, CD, CF, CI, CR, DF, FA, FC, FD, FM, IF, or TF leg

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

• Thirty nautical miles from the departure airport (or at the last departure waypoint if farther than 30 nm from the departure airport), the system automatically selects the enroute phase of ﬂight and changes the CDI scaling to 2.0 nm over a distance of 1.0 nm.

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

• Within 31 nm of the destination airport (terminal area), the CDI scale gradually ramps down from 2.0 nm to 1.0 nm over a distance of 1.0 nm; if a transition back to enroute ﬂight occurs, the CDI scale increases back to 2.0 in the same manner.

• During approach operations, the CDI scale ramps down even further (see Figures 2-26 and 2-27). This transition normally occurs within 2.0 nm of the ﬁnal approach ﬁx (FAF). The CDI switches to approach scaling automatically once any portion of the approach procedure becomes active or if Vector-to-Final (VTF) is selected.

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

ﬁnal approach segment course.

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

approach legs must be aligned within 3° of the ﬁnal approach segment course and the aircraft position must be prior to the turn initiation point.

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FLIGHT INSTRUMENTS

1.0 nm

2 nm

FAF

0.3 nm

course width

Landing

Threshold

CDI Full-scale Deflection

angle based on database information

CDI scale varies if VTF is activated

1.0 nm

2 nm

350 ft

angle set by system

0.3 nm

FAF

CDI Full-scale Deflection

CDI scale is set to the smaller of 0.3 nm

or an angle set by the syste

CDI scale varies if VTF is activated

Figure 2-26 Typical LNAV and LNAV+V Approach CDI Scaling

Figure 2-27 Typical LNAV/VNAV and LPV Approach CDI Scaling

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

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

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

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

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

Flight Phase Annunciation Automatic CDI Full-scale Deﬂection

Departure DPRT 0.3 nm Terminal

TERM 1.0 nm

Enroute ENR 2.0 nm Oceanic OCN 2.0 nm

Approach (Non-precision)

Approach (Non-precision with

LNAV

1.0 nm decreasing to 350 feet depending on variables (see Figure 2-26)

LNAV + V

Vertical Guidance) Approach

(LNAV/VNAV) Approach

(LPV)

L/VNAV

LPV

1.0 nm decreasing to a speciﬁed course width, then

0.3 nm, depending on variables (see Figure 2-27)

Missed Approach MAPR 0.3 nm

Table 2-1 Automatic GPS CDI Scaling

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OBS MODE

FLIGHT INSTRUMENTS

NOTE:

VNV is inhibited while automatic waypoint sequencing has been suspended.

Enabling Omni-bearing Selector (OBS) Mode suspends the automatic sequencing of waypoints in a GPS ﬂight plan (GPS must be the selected navigation source), but retains the current “active-to” waypoint as the navigation reference even after passing the waypoint. ‘OBS’ is annunciated to the lower right of the aircraft symbol when OBS Mode is selected (see Figure 2-28).

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

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. Press the CRS Knob to synchronize the

Selected Course with the bearing to the next waypoint.

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

OBS Course

GPS Selected

Extended

Course Line

Pressing the

190-00692-00 Rev. B

OBS

Softkey

Enables OBS Mode

OBS Mode Enabled

Pressing the

Returns to Normal Operation

Figure 2-28 Omni-bearing Selector (OBS) Mode

OBS

Softkey Again

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FLIGHT INSTRUMENTS

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

Softkey label changes to SUSP.

SUSP Annunciation

Pressing the

Automatic Waypoint Sequencing

SUSP

Softkey Suspends

Figure 2-29 Suspending Automatic Waypoint Sequencing

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2.2 SUPPLEMENTAL FLIGHT DATA

FLIGHT INSTRUMENTS

NOTE:

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

Map, and wind data.

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

• Inset Map

• Outside air temperature (OAT)

• DME Information Window

• Wind data

• Transponder Status Box

• System Time

• PFD Setup Menu

• Windows displayed in the lower right corner of the PFD:

– Timer/References

– Nearest Airports

– Flight Plan

– Alerts

– Procedures

– DME Tuning

• Minimum Descent Altitude/ Decision Height readout

• Glideslope, Glidepath, and Vertical Deviation Indicators

• Altimeter Barometric Setting

• Selected Altitude

• VNAV Target Altitude

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

190-00692-00 Rev. B

TMR/REF

large FMS

Figure 2-30 Timer/References Window

Softkey.

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

ENT

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FLIGHT INSTRUMENTS

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

ENT

Key.

small FMS

ENT

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

Knob to select the timer counting direction.

digits are reset.

9) To remove the window, press the

CLR

Key or the

TMR/REF

Softkey.

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 2-31 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. ‘Time Format’ is highlighted.

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

4) Press the ENT Key to conﬁrm selection. ‘Time Offset’ is highlighted (for local time formats).

5) Enter the desired time offset (±HH:MM) for local time formats.

6) Press the ENT Key to conﬁrm selection.

Figure 2-32 System Setup Page,

Date/Time Settings

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FLIGHT INSTRUMENTS

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

Figure 2-33 Outside Air Temperature

WIND DATA

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

• Longitudinal and lateral components (Option 1)

• Total wind direction and speed (Option 2)

• Total direction with head and crosswind speed components (Option 3)

Option 2Option 1

Option 3

Figure 2-34 Wind Data

No Data

Displaying wind data:

1) Press the PFD Softkey.

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

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

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

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FLIGHT INSTRUMENTS

VERTICAL NAVIGATION (VNV) INDICATIONS

When a VNV ﬂight plan has been activated, VNV indications (VNV Target Altitude, RSVI, VDI) appear on the PFD in conjunction with the “TOD within 1 minute” message (Figure 2-35) and “Vertical track” voice alert. See the GPS Navigation section for details on VNV features. VNV indications are removed from the PFD according to the criteria listed in Table 2-2.

Top of Descent Message

VNV Target Altitude

Vertical Deviation Indicator

Required Vertical Speed Bug

GPS is Selected

Navigation Source

Figure 2-35 Vertical Navigation Indications (PFD)

Enroute Phase of Flight

VNV Indication Removed

Criteria

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

Required Vertical

Speed (RSVI)

X X X X X X

Vertical

Deviation (VDI)

VNV Target

Altitude

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

unsupported ﬂight plan leg type (see GPS Navigation Section) Aircraft > 250 feet below active VNV Target Altitude Current crosstrack or track angle error has exceeded limit Active altitude-constrained waypoint can not be reached within

maximum allowed ﬂight path angle and vertical speed

Last altitude-constrained waypoint in active ﬂight plan reached

Table 2-2 VNV Indication Removal Criteria

X X X

X X X X X X

X X

(30 sec before)

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2.3 PFD ANNUNCIATIONS AND ALERTING FUNCTIONS

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

information on alerts and annunciations.

G1000 ALERTING SYSTEM

Messages appear in the Alerts Window (in the lower right corner of the PFD; Figure 2-36) 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 new message is generated, pressing the ALERTS Softkey to acknowledge the message causes it to turn gray.

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

ALERTS

Softkey. If the window is already open when a

Annunciation Window

Alerts Window

Softkey Annunciation

Figure 2-36 G1000 Alerting System

The ALERTS Softkey label changes to display the appropriate annunciation when an alert is issued. The annunciation ﬂashes and the appropriate aural alert sounds until acknowledged by pressing the softkey. The softkey then reverts to the ALERTS label, and when selected 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).

WARNING

Caution indicates the existence of abnormal conditions on the aircraft that may require pilot intervention. A ﬂashing

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FLIGHT INSTRUMENTS

cautions. The ﬂashing CAUTION annunciator continues to ﬂash until acknowledged by the pilot (by pressing the

CAUTION

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).

Softkey).

Figure 2-37 Softkey Annunciation (ALERTS Softkey labels)

MARKER BEACON ANNUNCIATIONS

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

Inner MarkerMiddle MarkerOuter Marker

ADVISORY

Altimeter

Figure 2-38 Marker Beacon Annunciations

TRAFFIC ANNUNCIATION

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

• The PFD Inset Map is enabled, displaying trafﬁc

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

Indicator for 5 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

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FLIGHT INSTRUMENTS

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 2-39 Trafﬁc and Example TAWS Annunciations

ALTITUDE ALERTING

The Altitude Alerting function provides the pilot with visual and aural alerts when approaching the Selected Altitude. Whenever the Selected Altitude is changed, the Altitude Alerter is reset. The Altitude Alerter is independent of the installed AFCS. The following occur when approaching the Selected Altitude:

• Upon passing through 1000 feet of the Selected Altitude, the Selected Altitude (shown above the Altimeter)

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

• 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 feet Within 200 feet Deviation of ±200 feet

Figure 2-40 Altitude Alerting Visual Annunciations

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MINIMUM DESCENT ALTITUDE/DECISION HEIGHT ALERTING

For altitude awareness, a minimum descent altitude/decision height (MDA/DH) can be set in the Timer/ References Window. When active, the altitude setting is displayed to the lower left of the Altimeter and with a bug at the corresponding altitude along the Altimeter (once the altitude is within the range of the tape). The following visual annunciations alert the pilot when approaching the MDA or DH:

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

with the altitude in light blue text. The bug appears on the altitude tape in light blue once in range.

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

• Once the aircraft reaches the MDA/DH, the bug and text turn yellow and the aural alert, “Minimums

Minimums”, is generated.

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

Altitude ReachedWithin 100 feetWithin 2500 feet

MDA/DH Bug

MDA/DH Setting

Figure 2-41 Minimum Descent Altitude/Decision Height Alerting Visual Annunciations

The MDA/DH may be set from either PFD and is synchronized on both PFDs. The function is reset when the power is cycled.

Setting the minimum descent altitude/decision height and bug:

1) Press the

2) Turn the large FMS Knob to highlight the ‘Minimums’ ﬁeld (Figure 2-42).

3) Turn the small FMS Knob to select BARO. OFF is selected by default. Press the ENT Key or turn the large FMS

TMR/REF

Softkey.

Knob to highlight the next ﬁeld.

4) Use the small FMS Knob to enter the desired altitude (from zero to 16,000 feet).

5) To remove the window, press the

CLR

Key or the

TMR/REF

Softkey.

Figure 2-42 Minimum Descent Altitude/Decision Height

Setting (Timer/References Window)

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2.4 ABNORMAL OPERATIONS

The annunciations listed in Table 2-3 can appear on the HSI when abnormal GPS conditions occur; see Figure

2-43 for examples. Refer to the GPS Navigation Section for more information on Dead Reckoning Mode.

Annunciation Location Description

LOI

WARN

INTEG OK

Lower left of

aircraft symbol

Lower left of

aircraft symbol

Lower left of

aircraft symbol

Upper right of

aircraft symbol

Table 2-3 Abnormal GPS Conditions Annunciated on HSI

Loss of Integrity Monitoring–GPS integrity is insufﬁcient for the current phase of ﬂight

Warning–RAIM function detects excessive GPS position errors

Integrity OK–GPS integrity has been restored to within normal limits (annunciation displayed for 5 seconds)

Dead Reckoning–System is using projected position rather than GPS position to compute navigation data and sequence active ﬂight plan waypoints

Figure 2-43 Example HSI Annunciations

Dead Reckoning Mode causes the CDI to be removed from the display (when GPS is the selected navigation

source) and the following items on the PFD to be shown in yellow:

• Current Track Bug

• Wind Data (calculated based on GPS information)

• Distances in the Bearing Information windows

• GPS bearing pointers

These items should be veriﬁed when operating in

Dead Reckoning Mode.

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SECTION 3 ENGINE INDICATION SYSTEM

ENGINE INDICATION SYSTEM

NOTE:

The G1000 Engine Indication System (EIS) for the Piper PA32 displays critical engine, electrical, fuel, and other system parameters on the left side of the MFD during normal operations. EIS information can be fully expanded to an entire page (Engine Page) using the

In reversionary mode, the displays are re-conﬁgured to present PFD symbology together with the EIS Display (refer to the System Overview for information about reversionary mode). Information on the engine, electrical system, fuel, and cabin temperature is organized into three displays while the G1000 is in reversionary mode:

• Engine Display – Default display (identical to the EIS Display normally shown on the MFD); 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 indicators

EIS Display

Refer to the Aircraft Flight Manual (AFM) for limitations.

ENGINE Softkey.

Instrument types include dial gauges, horizontal and vertical bar indicators, digital readouts, slide bars, and bar graphs. Green bands indicate normal ranges of operation; yellow and red bands indicate caution and warning, respectively. White bands indicate areas outside of normal operation not yet in the caution or warning ranges.

When unsafe operating conditions occur, the corresponding readouts ﬂash to indicate cautions and warnings. If sensory data to an instrument becomes invalid or unavailable, a red “X” is displayed across the instrument.

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Figure 3-1 MFD (Normally-aspirated)

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3.1 EIS DISPLAY

NOTE:

The Fuel Quantity Indicator displays only to 50 gallons per side when full.

The EIS Display shows all critical engine, fuel, and electrical indicators at the left of the MFD. In reversionary

mode, the Engine Display is identical to the EIS Display normally shown on the MFD.

Engine Manifold Pressure

Gauge (MAN IN)

Tachometer (RPM)

Displays manifold pressure in inches of Mercury (in Hg) to indicate engine power

Turbocharged Aircraft – Maximum manifold pressure range displayed in red

Displays propeller speed in revolutions per minute (rpm); the red range

indicates propeller overspeed

Fuel Quantity Indicator

(FUEL QTY GAL)

Fuel Flow Indicator

Displays the amount of fuel in gallons (gal) for each tank, labeled ‘L’ (left)

and ‘R’ (right)

Displays fuel ﬂow in gallons per hour (gph)

(FFLOW GPH)

Oil Temperature Indicator

Displays oil temperature in degrees Fahrenheit (°F)

(OIL °F)

Oil Pressure Indicator

Displays oil pressure in pounds per square inch (psi)

(OIL PSI)

Exhaust Gas Temperature

Displays exhaust gas temperature (EGT) of the hottest cylinder in °F

Indicator (EGT °F)

Normally-aspirated Aircraft

Turbine Inlet Temperature

Indicator (TIT °F)

Turbocharged Aircraft

Cylinder Head Temperature

Indicator (CHT °F)

Emergency Battery Voltage

(EMER BATT)

Essential Bus Voltage

(ESS BUS)

Main Alternator Current

(MAIN ALT)

Displays the temperature at the turbine inlet in °F

Displays the temperature of the hottest cylinder in °F

Displays voltage for the emergency battery

Displays voltage for the essential bus

Displays main alternator current in amperes (A)

If the main alternator fails, changes to display standby alternator current

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ENGINE INDICATION SYSTEM

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Turbocharged

Figure 3-2 EIS (Engine) Display

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ENGINE INDICATION SYSTEM

3.2 ENGINE PAGE

NOTE:

The Fuel Quantity Indicator will display only to 50 gallons per side when full.

The EIS Engine Page displays engine, fuel, fuel calculation, electrical, and cabin temperature information using

round dial gauges, bar indicators, bar graphs, and digital readouts.

Accessing the EIS - Engine Page:

1) Press the ENGINE Softkey.

2) To return to the previously viewed page, press the ENGINE Softkey or turn the large FMS Knob.

Engine Manifold Pressure

Gauge (MAN IN HG)

Tachometer

(RPM)

Engine Temperature Group

(EGT °F, CHT °F, TIT °F)

Electrical Group

(ESS BUS, EMER BATT, MAIN ALT, STBY ALT, BATT)

Fuel Calculations Group

(GAL REM, GAL USED, ENDUR, RANGE NM)

Cabin Temperature Gauge

(CABIN °F)

Displays manifold pressure in inches of Mercury (in Hg) to indicate engine power

Turbocharged Aircraft – Maximum manifold pressure range displayed in red

Displays propeller speed in revolutions per minute (rpm); the red range

indicates propeller overspeed

For each cylinder the head temperatures are displayed in degrees Fahrenheit

(°F)

Normally-aspirated Aircraft – Exhaust gas temperatures (EGT) are displayed

for each cylinder in °F

Turbocharged Aircraft – Turbine inlet temperature is displayed in °F

Voltages for the essential bus and emergency battery, along with currents (in

amperes, A) for the main and standby alternators and battery are displayed using vertical bar indicators and readouts

The totalizer-based fuel remaining and fuel used and the totalizer-based

endurance and range calculations are displayed

Displays cabin temperature in °F

Fuel Quantity Gauges

(L/R FUEL QTY GAL)

Oil Temperature/Pressure

Gauge (OIL °F PSI)

Fuel Flow Gauge

(FFLOW GPH)

Gauges display the amount of fuel in gallons (gal)

Oil temperature in °F is displayed on the left half of the gauge and pressure

is displayed on the right in pounds per square inch (psi)

Displays fuel ﬂow in gallons per hour (gph)

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Figure 3-3 Engine Page (Normally-aspirated)

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Figure 3-4 Engine Page (Turbocharged)

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ENGINE INDICATION SYSTEM

ENGINE TEMPERATURE GROUP

NOTE:

Follow the engine manufacturer’s recommended leaning procedures in the AFM.

Turbocharged Piper models are not equipped with the Lean Assist function.

The Temperature Group displays the head (CHT) and exhaust gas (EGT; displayed for normally-aspirated

aircraft only) temperatures in degrees Fahrenheit for each cylinder using bar graphs and digital readouts. For turbocharged aircraft, Turbine Inlet Temperature (TIT) is shown on a sliding bar scale.

Cylinder Head Temperature Exhaust Gas Temperature

(Normally-aspirated)

Turbine Inlet Temperature

(Turbocharged)

Figure 3-5 Engine Temperature Group

Normally-aspirated aircraft have an ASSIST Softkey for access of the Engine Leaning Assist Function. When the ASSIST Softkey is pressed, the system automatically switches to the ﬁrst peak obtained and displays the temperature deviation from peak (∆PEAK) in degrees Fahrenheit beside the EGT readout for the peaked cylinder. When a cylinder peaks, its number and readout are indicated in light blue and its peak is represented by a light blue bar on the EGT bar graph.

Lean Assist continues to monitor this cylinder unless the temperature for the cylinder exceeds peak. If peak is exceeded, Lean Assist is reset.

Selecting the Engine Leaning Assist Function (normally-aspirated aircraft):

From the Lean Display, press the ASSIST Softkey to identify the peak. The number and EGT readout for the

peaked cylinder are indicated in light blue and its deviation from peak temperature is displayed beside the EGT Bar Graph.

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ENGINE INDICATION SYSTEM

ELECTRICAL GROUP

The Electrical Group uses vertical bar indicators to display voltages for the essential bus and emergency battery and currents for the main and standby alternators and the battery. Standby alternator current is indicated only when active.

Emergency

Battery Voltage

Essential Bus Voltage Battery Current

Figure 3-6 Electrical Group

Main

Alternator

Current

Standby

Alternator

Current

FUEL CALCULATIONS GROUP

NOTE:

Fuel calculations do not use the aircraft fuel quantity indicators and are calculated from the last time

the fuel was reset.

Fuel used (GAL USED), endurance (ENDUR, HH:MM), and range (RANGE NM) are all calculated based on the displayed fuel remaining (GAL REM) and the fuel ﬂow totalizer. The displayed fuel remaining, for purposes of these calculations, can be adjusted using the following softkeys:

• DEC FUEL – Decreases totalizer-based fuel remaining in one-gallon increments

• INC FUEL – Increases totalizer-based fuel remaining in one-gallon increments

• RST FUEL – Resets totalizer-based fuel remaining to the aircraft’s fuel capacity and sets the GAL USED

display to zero

Fuel Remaining

Fuel Used Calculation

Figure 3-7 Fuel Calculations Group

Endurance Calculation

Range Calculation

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ENGINE INDICATION SYSTEM

3.3 EIS DISPLAY IN REVERSIONARY MODE

When the G1000 displays enter reversionary mode, the EIS for the Piper PA32 is separated into three displays: Engine (identical to the normal EIS Display on the MFD), Lean, and System. For a description of the Engine Display, refer to Section 3.1. The Lean Display presents temperature information and assistance for engine leaning. The System Display shows the fuel calculations, cabin temperature, and electrical parameters. All three displays feature the Engine Manifold Pressure Gauge, Tachometer, and Fuel Quantity and Fuel Flow Indicators.

The Lean and System displays can be accessed while in reversionary mode by pressing the followed by the LEAN or SYSTEM Softkey. The Engine Display is shown by default and does not require a softkey press to be displayed unless another display is currently shown. To return to the Engine Display from the Lean or System Display, press the

EIS Display

ENGINE or BACK Softkey.

ENGINE Softkey,

Figure 3-8 Reversionary Mode (Turbocharged)

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LEAN DISPLAY

ENGINE INDICATION SYSTEM

NOTE:

The EIS Lean Display provides information and a user interface to perform engine leaning. Exhaust gas (EGT) and head (CHT) temperatures for each cylinder are displayed in bar graph form with a readout for the temperature of the selected cylinder shown below each graph. By default, the cylinder with the hottest temperature is selected (number highlighted in light blue) when the LEAN Softkey is pressed. Turbine inlet temperature (TIT) is shown in place of EGT for turbocharged aircraft.

Bars for cylinders with temperatures in the normal range are shown in white. On the CHT Bar Graph, a warning condition for a cylinder is indicated in red.

The CYL SLCT Softkey becomes available after pressing the LEAN Softkey. The CYL SLCT Softkey can be utilized to cycle through the cylinders and obtain information about a cylinder, highlighted in light blue on the bar graph(s). This softkey is disabled when the ASSIST Softkey is pressed or when a cylinder experiences a warning (red) condition; this softkey remains disabled until the temperature returns to normal.

Follow the engine manufacturer’s recommended leaning procedures in the AFM.

Turbocharged Piper models are not equipped with the Lean Assist function.

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 temperatures:

From the Lean Display, press the CYL SLCT Softkey to cycle through each cylinder and view its temperature

information. The selected cylinder number is highlighted in light blue.

An Engine Leaning Assist Function is available to assist in the leaning process for normally-aspirated aircraft. When the the temperature deviation from peak (∆PEAK) in degrees Fahrenheit below the EGT readout for the peaked cylinder. When a cylinder peaks, its number is indicated in light blue and its peak is represented by a light blue bar on the EGT bar graph. Lean Assist continues to monitor this cylinder unless the temperature for the cylinder exceeds peak. If peak is exceeded, Lean Assist is reset.

ASSIST Softkey is pressed, the system automatically switches to the ﬁrst peak obtained and displays

Selecting the Engine Leaning Assist Function (normally-aspirated aircraft):

From the Lean Display, press the ASSIST Softkey to identify the peak. The EGT for the selected cylinder (number

highlighted in light blue) and its deviation from peak temperature are displayed beneath the EGT Bar Graph.

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ENGINE INDICATION SYSTEM

Engine Manifold Pressure

Gauge (MAN IN HG)

Tachometer

(RPM)

Fuel Quantity Indicator

(FUEL QTY GAL)

Fuel Flow Indicator

(FFLOW GPH)

Turbine Inlet Temperature

Indicator (TIT °F)

Turbocharged aircraft

Exhaust Gas Temperature

Bar Graph (EGT °F)

Normally-aspirated aircraft

Cylinder Head

Temperature Bar Graph (CHT °F)

Displays manifold pressure in inches of Mercury (in Hg) to indicate engine power

Turbocharged Aircraft – Maximum manifold pressure range displayed in red

Displays propeller speed in revolutions per minute (rpm); the red range

indicates propeller overspeed

Displays the amount of fuel in gallons (gal) for each tank, labeled ‘L’ (left)

and ‘R’ (right)

Displays fuel ﬂow in gallons per hour (gph)

Displays the temperature at the turbine inlet in degrees Fahrenheit (°F)

Displays exhaust gas temperatures (EGT) for all cylinders in °F; the readout

is for the hottest cylinder

Displays head temperatures for all cylinders with a readout for the hottest

cylinder in °F

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ENGINE INDICATION SYSTEM

TurbochargedNormally-aspirated

Figure 3-9 Lean Display (Reversionary Mode)

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ENGINE INDICATION SYSTEM

SYSTEM DISPLAY

NOTE:

Fuel calculations do not use the aircraft fuel quantity indicators and are calculated from the last time

the fuel was reset.

The EIS System Display shows the engine manifold pressure, tachometer, fuel quantity and ﬂow, fuel calculations, and oil, cabin, and electrical indications. Fuel calculations are based on the displayed fuel remaining (GAL REM) and the fuel ﬂow totalizer. The fuel remaining can be adjusted using the following softkeys:

• DEC FUEL – Decreases totalizer-based fuel remaining in one-gallon increments

• INC FUEL – Increases totalizer-based fuel remaining in one-gallon increments

• RST FUEL – Resets totalizer-based fuel remaining (GAL REM) relative to the aircraft’s fuel capacity and sets

the displayed fuel used (GAL USED) to zero

Engine Manifold Pressure

Gauge (MAN IN)

Tachometer (RPM)

Fuel Quantity Indicator

(FUEL QTY GAL)

Fuel Flow Indicator

(FFLOW GPH)

Calculated Fuel Used

(GAL USED)

Calculated Fuel

Remaining (GAL REM)

Oil Pressure

(OIL PSI)

Oil Temperature (OIL °F)

Displays manifold pressure in inches of Mercury (in Hg) to indicate engine power

Turbocharged Aircraft – Maximum manifold pressure range displayed in red

Displays propeller speed in revolutions per minute (rpm); the red range

indicates propeller overspeed

Displays the amount of fuel in gallons (gal) for each tank, labeled ‘L’ (left)

and ‘R’ (right)

Displays fuel ﬂow in gallons per hour (gph)

Displays the calculated amount of fuel used based on the totalizer fuel

ﬂow

Displays the amount of fuel remaining set by the pilot and adjusted for fuel

burn

Displays oil pressure in pounds per square inch (psi)

Displays oil temperature in degrees Fahrenheit (°F)

Cabin Temperature

(CABIN °F)

Battery Current

(BATT)

Emergency Battery

Voltage (EMER BATT)

Essential Bus Voltage

(ESS BUS)

Main Alternator Current

(MAIN ALT)

Displays cabin temperature in °F

Displays battery current in amperes (A)

Displays voltage for the emergency battery

Displays voltage for the essential bus

Displays main alternator current in amperes (A)

If the main alternator fails, changes to display standby alternator current

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ENGINE INDICATION SYSTEM

Accessing the EIS System Display:

1) Press the ENGINE Softkey.

2) Press the SYSTEM Softkey.

3) To return to the default Engine Display, press the ENGINE or BACK Softkey.

Adjusting the fuel totalizer quantity:

From the System Display, press the

Resetting the fuel totalizer:

From the System Display, press the

DEC FUEL or INC FUEL

RST FUEL

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

Softkey to adjust the fuel remaining (GAL REM).

TurbochargedNormally-aspirated

Figure 3-10 System Display (Reversionary Mode)

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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 Piper PA32 aircraft is performed by the following Line Replaceable Units (LRUs):

• GDU 1040 Primary Flight Display (PFD)

• GMA 1347 Audio Panel

• GDU 1040 Multi Function Display (MFD)

• GIA 63W 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.

The Mode S transponder is controlled with softkeys and the (PFD). The Transponder Data Box is located to the left of the System Time Box. The data box displays the active four-digit code, mode, and reply status (Figure 4-1).

• GTX 33 Mode S Transponder

FMS Knob located on the Primary Flight Display

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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

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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 enter transponder codes, select DME modes, and

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

Auto-tune entries when 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.

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Garmin G1000 Pilot’s Guide for Piper PA32

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Page 98

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 Piper PA32 aircraft.

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Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. B

Page 99

AUDIO PANEL AND CNS

COM3

COM 1/2

TEL

SPKR

MKR/MUTE

HI SENS

DME

– Not used in Piper PA32 aircraft.

–

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

– Not used in Piper PA32 aircraft.

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

is pressed.

– 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. Unmutes 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.

– Turns optional DME audio on or off.

NAV1

ADF

NAV2

AUX

MAN SQ

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

– Turns the optional ADF receiver audio on or off.

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

– Not used in Piper PA32 aircraft.

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

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

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

– Selects and deselects the pilot intercom isolation.

– Selects and deselects the copilot intercom isolation.

– Press to switch between volume and squelch control as indicated by 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

190-00692-00 Rev. B

– Manually selects Reversionary Mode.

Garmin G1000 Pilot’s Guide for Piper PA32

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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

changes to white, indicating that neither COM transmitter is active.

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

audio from the other COM radio is muted.

An active COM frequency displayed in green indicates that the COM transceiver is selected on the Audio

Panel (

COM1 MIC

COM2 MIC

Key). 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.

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

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Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. B

Garmin PA32 User Manual

Specifications and Main Features

Frequently Asked Questions

User Manual

SECTION 1 SYSTEM OVERVIEW

1.1 SYSTEM DESCRIPTION

1.2 LINE REPLACEABLE UNITS (LRU)

1.3 G1000 CONTROLS

PFD/MFD CONTROLS

AUDIO PANEL CONTROLS

1.4 SECURE DIGITAL (SD) CARDS

1.5 SYSTEM POWER-UP

1.6 SYSTEM OPERATION

NORMAL DISPLAY OPERATION

REVERSIONARY DISPLAY OPERATION

AHRS OPERATION

G1000 SYSTEM ANNUNCIATIONS

SOFTKEY FUNCTION

1.7 ACCESSING G1000 FUNCTIONALITY

MENUS

MFD PAGE GROUPS

MFD SYSTEM PAGES

1.8 DISPLAY BACKLIGHTING

AUTOMATIC ADJUSTMENT

MANUAL ADJUSTMENT

SECTION 2 FLIGHT INSTRUMENTS

2.1 FLIGHT INSTRUMENTS

AIRSPEED INDICATOR

ATTITUDE INDICATOR

ALTIMETER

VERTICAL SPEED INDICATOR (VSI)

VERTICAL DEVIATION, GLIDESLOPE, AND GLIDEPATH INDICATORS

HORIZONTAL SITUATION INDICATOR (HSI)

COURSE DEVIATION INDICATOR

2.2 SUPPLEMENTAL FLIGHT DATA

GENERIC TIMER

SYSTEM TIME

OUTSIDE AIR TEMPERATURE

WIND DATA

VERTICAL NAVIGATION (VNV) INDICATIONS

2.3 PFD ANNUNCIATIONS AND ALERTING FUNCTIONS

G1000 ALERTING SYSTEM

MARKER BEACON ANNUNCIATIONS

TRAFFIC ANNUNCIATION

TAWS ANNUNCIATIONS

ALTITUDE ALERTING

MINIMUM DESCENT ALTITUDE/DECISION HEIGHT ALERTING

2.4 ABNORMAL OPERATIONS

SECTION 3 ENGINE INDICATION SYSTEM

3.1 EIS DISPLAY

3.2 ENGINE PAGE

ENGINE TEMPERATURE GROUP

ELECTRICAL GROUP

FUEL CALCULATIONS GROUP

3.3 EIS DISPLAY IN REVERSIONARY MODE

LEAN DISPLAY

SYSTEM DISPLAY

SECTION 4 AUDIO PANEL AND CNS

4.1 OVERVIEW

PFD/MFD CONTROLS AND FREQUENCY DISPLAY

AUDIO PANEL CONTROLS

4.2 COM OPERATION

COM TRANSCEIVER SELECTION AND ACTIVATION