Garmin PA32 User Manual

Piper

PA32

Copyright © 2007 Garmin Ltd. or its subsidiaries. All rights reserved.

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: [phone] Fax: [phone]

Garmin AT, Inc., 2345 Turner Road SE, Salem, OR 97302, U.S.A.
Tel: [phone] Fax [phone]

Garmin (Europe) Ltd., Unit 5, The Quadrangle, Abbey Park Industrial Estate, Romsey, Hampshire S051 9DL, U.K.
Tel: [phone] Fax: [phone]

Garmin Corporation, No. 68, Jangshu 2nd Road, Shijr, Taipei County, Taiwan
Tel: [phone] Fax: [phone]

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.

LIMITED WARRANTY

LIMITED WARRANTY

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

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

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

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

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

190-00692-00 Rev. B

Garmin G1000 Pilot’s Guide for Piper PA32

i

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.

Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. Bii

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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Garmin G1000 Pilot’s Guide for Piper PA32

iii

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

190-00692-00 Rev. Biv

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

190-00692-00 Rev. B

Garmin G1000 Pilot’s Guide for Piper PA32

v

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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TABLE OF CONTENTS

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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Garmin G1000 Pilot’s Guide for Piper PA32

vii

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

Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. Bviii

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

• 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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Garmin G1000 Pilot’s Guide for Piper PA32

1-1

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

Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. B

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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Garmin G1000 Pilot’s Guide for Piper PA32

1-3

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

Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. B

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

Ve

rtical Speed

GRS 77

AHRS

Attitude

Rate of Turn

Slip/Skid

GMU 44

Magnetometer

Heading

GPS Output

GPS Output

Reversionary

Control

GMA 1347

Audio Panel

PFD

GDU 1040

S-TEC System

Fifty-Five

X

Autopilot

MFD

GDU 1040

SYSTEM OVERVIEW

Figure 1-1 Basic G1000 System

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Garmin G1000 Pilot’s Guide for Piper PA32

1-5

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

L3

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

h

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

Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. B

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

3

5

7

8

9

1

NAV VOL / ID Control

2

NAV Frequency Transfer Key

3

Dual NAV Knob

4

Heading Knob

5

Joystick

6

CRS/BARO Knob

7

Dual COM Knob

8

COM Frequency Transfer Key

9

COM VOL/SQ Knob

190-00692-00 Rev. B

17

Figure 1-3 PFD/MFD Controls

10

Direct-to Key

11

FPL Key

12

CLR Key (DFLT MAP)

13

Dual FMS Knob

14

MENU Key

15

PROC Key

16

ENTKey

17

Dual ALT Knob

10

11

12

13

Garmin G1000 Pilot’s Guide for Piper PA32

14

15

16

1-7

SYSTEM OVERVIEW

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

1

NAV VOL/ID Knob

Volume level is shown in the field as a percentage.

2

NAV Frequency Transfer Key

3

Dual

4

Heading Knob

5

Joystick

6

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

7

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.

8

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.

9

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.

10

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).

11

FPL Key

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

stored flight plans.

12

CLR

Key (DFLT MAP)

Navigation Map Page immediately, press and hold

13

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

1-8

Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. B

SYSTEM OVERVIEW

14

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.

15

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.

16

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.

17

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

11

13

15

17

18

20

22

1

3

5

7

9

2

4

6

8

10

12

14

16

19

21

23

190-00692-00 Rev. B

24

Figure 1-4 Audio Panel Controls (GMA 1347)

Garmin G1000 Pilot’s Guide for Piper PA32

1-9

SYSTEM OVERVIEW

NOTE:

1

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.

2

COM1

3

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.

4

COM2

5

COM3 MIC

6

COM3

7

COM 1/2

8

TEL

9

PA

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

– Not used.

– 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.

10

SPKR

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

audio will be heard on the speaker.

11

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.

12

HI SENS

13

DME

14

NAV1

15

ADF

16

NAV2

17

AUX

18

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.

19

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

20

PILOT

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

Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. B

SYSTEM OVERVIEW

21

COPLT

22

PILOT Knob

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

23

PASS Knob

selected to allow squelch adjustment.

24

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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Garmin G1000 Pilot’s Guide for Piper PA32

1-11

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

Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. B

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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Garmin G1000 Pilot’s Guide for Piper PA32

1-13

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.

Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. B

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:

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.

190-00692-00 Rev. B

Garmin G1000 Pilot’s Guide for Piper PA32

1-15

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

available

unavailable

una

v

ail

ab

le

available

unavailable

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

Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. B

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

OR

GIA 63W

Integrated

Avionics Unit

GIA 63W

Integrated

Avionics Units

GDC 74A Air

Data Computer

GRS 77 AHRS

OR

GMU 44

Magnetometer

GIA 63W Integrated

Avionics Units

GDC 74A Air

Data Computer

Figure 1-12 G1000 System Failure Annunciations

GTX 33 Transponder

OR

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

On

Bezel-Mounted
Softkeys (Press)

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

Softkey Names

(Displayed)

190-00692-00 Rev. B

Garmin G1000 Pilot’s Guide for Piper PA32

1-17

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

Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. B

SYSTEM OVERVIEW

VOR1

VOR2

GPS

DME

ALERTS

OBS

CDI

DME

XPDR

IDENT

TMR/REF

NRST

ALT UNIT

STD BARO

STBY

ON

ALT

GND

VFR

CODE

IDENT

METERS

IN

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

190-00692-00 Rev. B

Figure 1-14 Top Level PFD Softkeys

Garmin G1000 Pilot’s Guide for Piper PA32

1-19

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

ALERTS

ALERTS

ALERTS

Figure 1-15 INSET Softkeys

1-20

Figure 16 PFD Configuration Softkeys

Garmin G1000 Pilot’s Guide for Piper PA32

190-00692-00 Rev. B