Garmin G1000 System Overview

TM

G1000

System Overview

for the Beechcraft A36/G36

Record of Revisions

Revision Date of Revision Revision Page Range Description

A 7/19/05 ----------- Initial release

Garmin G1000 System Overview for the Beechcraft A36/G36 190-00571-00 Rev. A

SYSTEM OVERVIEW

No. 1 GIA 63

Integrated Avionics Unit

System Inegration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS

Glideslope

AFCS Mode Logic

Flight Director Calculations

Servo Communication

No. 2 GIA 63

Integrated Avionics Unit

System Integration Processors

I/O Processors

VHF COM

VHF NAV/LOC

GPS

Glideslope

Servo Communication

GTX 32

or GTX 33

Transponder

High-Speed Data Bus (Ethernet)

Reversionary

Control

GEA 71

Engine/Airframe

Unit

GDC 74A

Air Data

Computer

OAT

Airspeed

Altitude

Vertical Speed

GRS 77

AHRS

Attitude

Rate of Turn

Slip/Skid

GMU 44

Magnetometer

Heading

GPS Output

GPS Output

Reversionary

Control

GSA 81

Pitch Servo

Autopilot Calculations

GSA 81

Pitch Trim Servo

Autopilot Calculations

GSA 81

Roll Servo

Autopilot Calculations

GSA 81

Yaw Servo

Autopilot Calculations

2.1 INTRODUCTION

This System Overview Pilot’s Guide provides a basic
description of the G1000 System as it pertains to the
Beechcraft A36/G36. The description includes the Garmin
Automatic Flight Control System (AFCS).

2.2 SYSTEM DESCRIPTION

System. A G1000 system block diagram is given in Fig­ure 2.2.1. Refer to the Pilot’s Guide Appendices for LRU
specifications.

This section gives a brief description of the G1000

190-00571-00 Rev. A Garmin G1000 System Overview for the Beechcraft A36/G36

Figure 2.2.1 G1000 System Block Diagram

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SYSTEM OVERVIEW

• GDU 1040/GDU 1043 – The G1000 features two
displays, the GDU 1040 and GDU 1043. The GDU
1040 is a 10.4-inch LCD display with 1024 x 768
resolution and is configured as a Primary Flight
Display. The GDU 1040 displays the Flight Director
command bars, system annunciations and alerts,
pilot-selectable references, and flight information.
The GDU 1043 is configured as a Multi Function
Display which contains the dedicated AFCS keys
and GPS/Navigation controls. The displays com­municate with each other through a high-speed data
bus (HSDB) Ethernet connection. Each display is
also paired via an ethernet connection.

• GMA 1347 – Installed between the MFD and PFD,
the GMA 1347 integrates NAV/COM digital audio,
intercom system and marker beacon controls. The
GMA 1347 communicates with both GIA 63s using
an RS-232 digital interface. The GMA 1347 also
controls manual display reversionary mode.

• GIA 63 – There are two GIA 63s. The GIA 63 func-
tions as a main communication hub, linking all LRUs
with the PFD and the MFD displays. Each GIA 63
contains a GPS receiver, VHF COM/NAV/GS receiv­ers, and system integration microprocessors. Each
GIA 63 is paired with a respective display through
an ethernet connection. The GIAs are not paired
together and do not communicate with each other
directly.

Each GIA 63 also contains the AFCS software

which controls the Flight Director. During normal
operation, the GRS 77 AHRS and GDC 74A Air Data
Computer send attitude and air data information
to the GIA 63s. This information, combined with
GPS and other system data, is used by the Flight
Director and Autopilot. Flight Director commands
are calculated within the #1 GIA 63 and are sent to
the PFD for display and mode annunciation. Flight
information is also sent to the GSA 81 servos for
Autopilot operation. A GIA #1 failure results in the
loss of the AFCS system. Any GIA 63 failure results
in loss of the Autopilot function.

• GRS 77 – The GRS 77 is an Attitude and Heading
Reference System (AHRS) that provides aircraft
attitude and heading information to both the
G1000 displays and the GIA 63s. The unit contains
advanced sensors, accelerometers and rate sensors.
In addition, the GRS 77 interfaces with both the
GDC 74A Air Data Computer and the GMU 44
Magnetometer. The GRS 77 also utilizes GPS signals
sent from the GIA 63. Attitude and heading infor­mation is sent using an ARINC 429 digital interface
to both GDU 1040s and GIA 63s. AHRS modes of
operation are discussed later in this document.

• GMU 44 – The GMU 44 Magnetometer measures
local magnetic field information. Data is sent to
the GRS 77 AHRS for processing to determine air­craft magnetic heading. This unit receives power
directly from the GRS 77 and communicates with
the GRS 77 using an RS-485 digital interface.

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190-00571-00 Rev. AGarmin G1000 System Overview for the Beechcraft A36/G36

SYSTEM OVERVIEW

• GDC 74A – The GDC 74A Air Data Computer
processes information from the pitot/static system
as well as the outside air temperature (OAT) sensor.
The GDC 74A provides pressure altitude, airspeed,
vertical speed and OAT information to the G1000
system, and communicates with the GIA 63s,
GDU 1040s and GRS 77 using an ARINC 429 digital
interface.

• GEA 71 – The GEA 71 receives and processes signals
from the engine and airframe sensors. Sensor types
include engine temperature and pressure sensors as
well as fuel measurement and pressure sensors. The
GEA 71 communicates with both GIA 63s using an
RS-485 digital interface.

• GTX 33 – The GTX 33 is a solid-state, Mode-S
transponder that provides Modes A, C and S opera­tion. The GTX 33 is controlled through the PFD
and communicates with both GIA 63s through an
RS-232 digital interface.

• SA 81 AFCS Servos – Four GSA 81 servos are
used for automatic control of the aircraft flight
control surfaces. One servo is used for the each of
the following:

Each servo moves its respective aircraft control

surface in response to commands generated by
internal servo calculations. For pitch trim, the servo
positions the aircraft pitch trim surface in response
to commands generated by automatic and manual
electric pitch trim calculations. Calculations are
performed using data sent through the common
serial data bus from the GIA 63. Manual Electric
Pitch Trim is also provided in response to the Manual
Electric Trim (

MET) switch.

Optional Equipment

This System Overview only covers the baseline
configuration of the G1000. Descriptions and procedures
relating to optional equipment is covered in the G1000
Optional Equipment Pilot’s Guide. Consult a Garmin
authorized service center for A36/G36 optional equipment
availability and configuration.

• Pitch

• Roll

• Pitch Trim

• Yaw

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SYSTEM OVERVIEW

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SYSTEM OVERVIEW

4

532 7

6

8

9

10

1

18

19

20

21

22

23

Figure 2.3.1 Display Controls (GDU 1043)

28

24

25

26

27

11

12

13

14

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15

16

17

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SYSTEM OVERVIEW

2.3 DISPLAY CONTROLS

The G1000 controls and keys have been designed to
simplify the operation of the system and minimize work
load as well as the time required to access sophisticated
functionality. The following list provides an overview of
the controls located on the display bezel.

• (1) Dual ALT Knob – Sets the reference altitude in
the box located above the Altimeter. The large knob
selects thousands, while the small knob selects
hundreds.

• (2) NAV VOL/ID Knob – Controls the NAV audio
level. Press to toggle the Morse code identifier ON
and OFF. Volume level is shown in the field as a
percentage.

• (3) NAV Frequency Toggle Key – Toggles the
standby and active NAV frequencies.

• (4) Dual NAV Knob – Tunes the MHz (large knob)
and kHz (small knob) standby frequencies for the
NAV receiver. Press to toggle the tuning cursor (cyan
box) between the NAV1 and NAV2 fields.

• (5) Heading Knob – Manually selects a heading
when turned. Synchronizes the heading bug with
the compass lubber line when pressed.

• (6) Joystick – Changes the map range when rotated.
Activates the map pointer when pressed.

-

• (8) 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 (cyan box) between the COM1 and
COM2 fields.

• (9) COM Frequency Toggle Key – Toggles 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.

• (10) COM VOL/SQ Knob – Controls COM audio
level. Pressing this knob turns the COM automatic
squelch ON and OFF. Audio volume level is shown
in the field as a percentage.

• (11) 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 cursor position).

• (12) FPL Key – Displays the active Flight Plan Page
for creating and editing the active flight plan, or for
accessing stored flight plans.

• (13) CLR Key (DFLT MAP) – Erases information,
cancels an entry, or removes page menus. To display
the Navigation Map Page immediately, press and hold
CLR (MFD only).

2-6

• (7) CRS/BARO Knob – The large knob sets the
altimeter barometric pressure and the
adjusts the 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.

small knob

190-00571-00 Rev. AGarmin G1000 System Overview for the Beechcraft A36/G36

• (14) Dual FMS Knob – Used to select the page to be
viewed (only on the MFD). The large knob selects a
page group (MAP, WPT, AUX, NRST), while the small
knob selects a specific page within the page group.
Pressing the small knob turns the selection cursor
ON and OFF. When the cursor is ON, data may be
entered in the different windows using the small and
large knobs. The large knob is used to move the
cursor on the page, while the small 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 FMS/PUSH CRSR knob to activate the cursor
and turn the large FMS knob to scroll through the
list.

SYSTEM OVERVIEW

NOTE: The selected COM (displayed in green)

is controlled by the COM MIC key on the audio
panel (GMA 1347).

• (18) AP Key – Engages/disengages the Autopilot.

Controls 19 through 28 are considered Flight Director

‘Mode Select’ keys.

• (19) FD Key – Activates/deactivates the Flight
Director. Pressing the FD key turns on the Flight
Director in the default pitch and roll modes.
Pressing the FD key again deactivates the Flight
Director and removes the command bars, unless
the Autopilot is engaged. If the Autopilot is
engaged, the FD key is disabled.

• (15) 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.

• (16) 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.

• (17) 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.

• (20) NAV Key – Selects/deselects the Navigation
mode.

• (21) ALT Key – Selects/deselects the Altitude
Hold mode.

• (22) VS Key – Selects/deselects the Vertical Speed
mode.

• (23) FLC Key – Selects/deselects the Flight Level
Change mode.

• (24) HDG Key – Selects/deselects the Heading
Select mode.

• (25) APR Key – Selects/deselects the Approach
mode.

• (26, 27) NOSE UP/NOSE DN Keys – Controls
the active pitch reference for the Pitch Hold, Verti­cal Speed, and Flight Level Change modes.

• (28) YD Key – Engages/disengages the Yaw
Damper.

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SYSTEM OVERVIEW

Common AFCS Controls

The following controls appear on both the PFD and

MFD and perform specific functions for the AFCS:

• (1) Dual ALT Knob – Sets Selected Altitude,
displayed in the Selected Altitude box. Selected
altitude provides an altitude setting for the
Altitude Capture/Hold mode, in addition to the
standard G1000 altitude alerter function.

• (5) Heading Knob – Sets Selected Heading on
the HSI. Selected Heading provides the heading
reference to the Flight Director while operating in
Heading Select mode.

• (7) CRS/BARO Knob – Sets Selected Course
on the HSI. Selected Course provides course
reference to the Flight Director when operating in
Navigation and Approach modes.

2.4 SECURE DIGITAL CARDS

The GDU 1040 data card slots use Secure Digital (SD)
cards. SD cards are used for aviation database updates
and terrain database storage.

To install an SD card:

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

To remove an SD card:

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

NOTE: Refer to the Pilot’s Guide Appendices for

instructions on updating the aviation database.

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190-00571-00 Rev. AGarmin G1000 System Overview for the Beechcraft A36/G36

2.5 SYSTEM POWER-UP

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

While the system begins to initialize, test annunciations
are displayed to the pilot at power-up, as shown in the
figure below. All system annunciations should be cleared
within one (1) minute of power-up. The GMA 1347 also
annunciates all bezel lights briefly upon power-up.

SYSTEM OVERVIEW

NOTE: Refer to the Beechcraft A36/G36 Pilot’s
Operating Handbook (POH) for specific proce­dures concerning avionics power application and
emergency power supply operation.

On the PFD, the AHRS system displays the ‘AHRS
ALIGN: Keep Wings Level’ message and begins to initial­ize. The AHRS should display valid attitude and heading
fields within one (1) minute of power-up. The AHRS can
align itself both while taxiing and during level flight.

NOTE: Refer to the Pilot’s Guide Appendices for
AHRS initialization bank angle limitations.

NOTE: See the Annunciations and Alerts Pilot’s
Guide for additional information regarding
system annunciations and alerts.

Figure 2.5.1 PFD Initialization Display

190-00571-00 Rev. A Garmin G1000 System Overview for the Beechcraft A36/G36

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SYSTEM OVERVIEW

When the MFD powers up, the MFD Power-up Page

displays the following information:

• System version

• Copyright

• Checklist filename

• Land database name and version

• Obstacle database name and version

• Terrain database name and version

• Aviation database name, version and effective
dates

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

Press the

ENT key to acknowledge this information

and proceed to the Navigation Map Page.

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Figure 2.5.2 MFD Power-up Page

190-00571-00 Rev. AGarmin G1000 System Overview for the Beechcraft A36/G36

SYSTEM OVERVIEW

2.6 DISPLAY BACKLIGHTING

The G1000 PFD and MFD displays use photocell
technology to automatically adjust for ambient lighting
conditions. Photocell calibration curves are pre-config­ured to optimize display appearance through a broad
range of cockpit lighting conditions. The PFD, MFD, and
GMA 1347 bezel/key lighting is typically controlled di­rectly by the existing instrument panel dimmer bus.

If desired, the PFD and MFD display backlighting can
be adjusted manually. The PFD, MFD and GMA 1347
bezel/key brightness can also be adjusted manually. The
GMA 1347 bezel/key brightness is directly tied to the
MFD bezel/key adjustment.

NOTE: Refer to the Primary Flight Display Pilot’s
Guide for instructions on adjusting backlighting
manually.

2.7 SYSTEM OPERATION

Normal Mode

The PFD and MFD are connected together on a single
Ethernet bus, allowing for high-speed communication be
tween the two units. Each GIA 63 is connected to a single
display, as shown in Figure 2.2.1. This allows the units to
share information, thus enabling true system integration.

In normal operating mode, the PFD displays graphical
flight instrumentation instead of the traditional gyro in­struments. Attitude, heading, airspeed, altitude and verti
cal speed are all shown on one display. The MFD shows a
full-color moving map with navigation information. Both
displays offer control for COM and NAV frequency selec­tion, as well as for the heading, course/baro and altitude
reference functions. On the left of the MFD display, the
Engine Indication System (EIS) cluster shows engine and
airframe instrumentation. Figure 2.7.1 gives an example
of the G1000 system in normal mode.

-

-

Figure 2.7.1 Normal Mode

190-00571-00 Rev. A Garmin G1000 System Overview for the Beechcraft A36/G36

2-11

SYSTEM OVERVIEW

Reversionary Mode

Should a failure occur in either display, the G1000
automatically enters reversionary mode. In reversionary
mode, all important flight information is shown on the re­maining display. An example of reversionary mode entry
due to a failed PFD is shown in Figure 2.7.2.

If a display fails, the GIA 63-GDU 1040 Ethernet inter
face is cut off. Thus, the GIA can no longer communicate
with the remaining display (refer to Figure 2.2.1), and the
NAV and COM functions provided to the failed display by
the GIA are flagged as invalid on the remaining display.
The system reverts to using backup paths for the GRS 77,
GDC 74A, GEA 71 and GTX 33, as required. The change
to backup paths is completely automated for all LRUs,
and no pilot action is required.

NOTE: The system alerts the pilot when backup
paths are utilized by the LRUs. Refer to the
Annunciations and Alerts Pilot’s Guide for further
information regarding these and other system
alerts.

-

Reversionary mode may also be manually activated by
the pilot if the system fails to detect a display problem.
Reversionary mode is activated manually by pressing
the red DISPLAY BACKUP button at the bottom of the
GMA 1347 Audio Panel. Pressing this button again deac­tivates reversionary mode.

AFCS Preflight Test

When power is applied to the G1000, the AFCS sys­tem starts preflight system tests. ‘PFT’ is annunciated on
the PFD at the AFCS System Status field. The Autopilot
disconnect aural alert tone sounds at the end of the test
and the ‘PFT’ annunciation disappears.

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Figure 2.7.2 Reversionary Mode

190-00571-00 Rev. AGarmin G1000 System Overview for the Beechcraft A36/G36

SYSTEM OVERVIEW

AHRS Operation

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

GPS Input Failure

The G1000 system provides two sources of GPS infor­mation. If a single GPS receiver fails, or if the informa­tion provided from one of the GPS receivers is unreliable,
the AHRS seamlessly transitions to using the other GPS
receiver. An alert message informs the pilot of the use of
the backup GPS path. If both GPS inputs fail, the AHRS
continues to operate in reversionary ‘No GPS’ mode so
long as the air data and magnetometer inputs are available
and valid.

Air Data Input Failure

A failure of the air data input has no effect on AHRS
output while AHRS is operating in normal/primary mode.
A failure of the air data input while the AHRS is operating
in reversionary ‘No GPS’ mode results in invalid attitude
and heading information on the PFD (as indicated by red
‘X’ flags).

Magnetometer Failure

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

NOTE: Please refer to the Annunciations and
Alerts Pilot’s Guide for specific AHRS alert infor­mation.

NOTE: Pilots should be aware that aggressive
maneuvering in any of the three reversionary
modes listed below can degrade AHRS accu­racy.

Available AHRS Functions Available Sensor Inputs

AHRS Mode

Pitch Roll Heading

GPS Input

(At least one)

GMU 44

Magnetometer
Normal/Primary X X X X X X
Reversionary:

No GPS
Reversionary:

No Magnetometer

X X X - X X

X X - X - X

Reversionary:
No Magnetometer

X X - X - -

No Air Data

190-00571-00 Rev. A Garmin G1000 System Overview for the Beechcraft A36/G36

GDC 74A

Air Data Computer

2-13

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190-00571-00 Rev. A© 2005 Garmin Ltd. or its subsidiaries