Garmin G1000 AFCS

TM

G1000

AFCS Pilot’s Guide for

Beechcraft A36/G36

Record of Revisions

Revision Date of Revision Revision Page Range Description

A
B

07/20/05
07/28/05

9-1 – 9-29
9-1 – 9-29

Initial release
Go Around button description change

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

190-00609-00 Rev. B

INTRODUCTION

9.1 INTRODUCTION

pitch, roll, and pitch trim GSA 81 servos and provides:

NOTE: This Pilot’s Guide assumes that the reader
is already familiar with the G1000 Integrated
Cockpit System. Refer to the G1000 Cockpit
Reference Guide and G1000 Pilot’s Guides
for further information concerning the G1000
system.

IMPORTANT: The information contained in this
guide is always superseded by the approved
Airplane Flight Manual Supplement.

AFCS OVERVIEW

The GFC 700 is a digital Automatic Flight Control Sys­tem (AFCS) which is fully integrated within the G1000
system avionics architecture. The System Overview locat­ed near the front of this binder provides a block diagram
to support this system description. The GFC 700 AFCS is
made up of the following Line Replaceable Units (LRUs):

• GDU

• GDU 1043 Multi-Function Display (MFD)

• GIA 63 Integrated Avionics Units (2)

• GSA

• GSM 85 Servo Mounts (4)

The GFC 700 AFCS system can be divided into three
main operating functions:

1040 Primary Flight Display (PFD)

81 Servos (4)

the GSA 81 yaw servo and includes self monitoring.

GIA 63 Integrated Avionics Units

trols 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, Manual Electric Trim, and the Yaw Damper
functions.

Autopilot — Autopilot operation occurs within the

• Automatic Flight Control

• Servo Monitoring

Yaw Damper — Yaw damper operation is provided by

Each GIA 63 contains the AFCS software which con-

Flight Director — Flight Director operation takes
place within the #1 GIA 63 and the GDU 1040 PFD. The
Flight Director provides the system with:

• Command Bars showing Pitch/Roll Guidance

• Pitch/Roll Mode Selection & Processing

• Autopilot Communication

190-00609-00 Rev. B

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

9-1

INTRODUCTION

GSA 81 AFCS Servos (4)

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:

• Pitch

• Roll

• Pitch Trim

• Yaw

Each servo moves its respective aircraft control surface
in response to commands generated by internal servo cal

­culations. 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.

GSM 85 Servo Mounts (4)

The GSM 85 servo mounts are used to connect the
servos to the aircraft control system. They contain a spi­ral capstan which connects via a bridle cable to the main
aircraft control cables. There is also a slip clutch to limit
overpower forces in the unlikely event of a mechanical
jam. An engage clutch is used to disconnect the capstan

from the servo when the AFCS is disengaged.

Dedicated AFCS Controls

Refer to Figure 2.3.1 located in the System Overview.
The GDU 1043 MFD has the following dedicated AFCS
keys located on the lower left side of the bezel:

• AP Key

– Engages/disengages the Autopilot

• FD Key – Activates/deactivates the Flight Director
only

Pressing the

FD key turns on the Flight Direc­tor in the default vertical and lateral 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.

• NAV Key

• ALT Key

– Selects/deselects the Navigation mode

– Selects/deselects the Altitude Hold

mode

• VS Key – Selects/deselects the Vertical Speed
mode

• FLC Key

– Selects/deselects the Flight Level

Change mode

• YD Key

• HDG Key

– Engages/disengages the Yaw Damper

– Selects/deselects the Heading Select

mode

• APR Key – Selects/deselects the Approach mode

• NOSE UP/NOSE DN Keys – Controls the active

pitch reference for the Pitch Hold, Vertical Speed,
and Flight Level Change modes

9-2

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

190-00609-00 Rev. B

INTRODUCTION

Additional AFCS Controls

The following buttons and switches used by the AFCS
are located in the cockpit separately from the PFD and
MFD:

• AP DISC (Autopilot Disconnect) Button —
Disengages the Autopilot and Yaw Damper and
interrupts pitch trim operation

This button may be used to mute the aural

alert associated with an Autopilot discon­nect. The AP DISC button is colored red
and is located forward of the MET switch on
the pilot’s control wheel left grip. The AP
DISC button mutes AP disconnect alerting
if pressed during an alert. The

MET ARM
switch may also be used to cancel AP discon­nect alerting.

• CWS (Control Wheel Steering) Button —
Momentarily disengages the Autopilot and
synchronizes the Flight Director’s command bars
to the current aircraft attitude

• MET (Manual Electric Trim) Switch — Used
to command Manual Electric Pitch Trim

This switch is a composite switch, split into

left and right switches, on the left grip of the
pilot’s control wheel. The right switch is the
ARM contact and the left switch controls the
DN (forward) and UP (rearward) contacts.
Pressing the ARM switch disengages the
Autopilot, if currently engaged, but does not
affect Yaw Damper operation. Manual trim
commands are generated only when both
sides of the switch are operated simultane­ously. If one side of the switch is active for
more than three seconds without the other
side also being active, the trim switches are
ignored until both switches (ARM, UP/DN)
are inactive. This condition is annunciated as
‘PTRM’ in the AFCS System Status field on the
PFD.

• GA (Go Around) Button — Disengages the

190-00609-00 Rev. B

The CWS button is located on top of the right

grip of the pilot’s control wheel. Upon release
of the CWS button, the Flight Director may
establish new reference points, depending
on the current pitch and roll modes. CWS
operation details are discussed in the respec

-

tive mode sections of this manual.

Autopilot and selects the Go Around pitch and
roll modes on the Flight Director

The

GA button is located in the throttle

handle.

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

9-3

INTRODUCTION

9-4

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

190-00609-00 Rev. B

FD OPERATION

9.2 FLIGHT DIRECTOR OPERATION

The Flight Director function provides pitch and roll
commands to the AFCS system and displays them on the
PFD. With the Flight Director activated, the pilot can
hand-fly the aircraft to follow the path shown by the com­mand bars. The Flight Director, when engaged, also pro­vides the commands to the Autopilot.

Active Mode

Armed Mode

Roll Axis Modes

System Status Field
(See Annunciations &
Alerts Pilot’s Guide)

Yaw Damper Status

Autopilot Status

Active Mode

AFCS Status Bar

Activating the Flight Director

Pressing the FD key or AP key (when FD is not active)
activates the Flight Director in default pitch/roll modes.
Pressing the GA button, or any other Fight Director mode
key activates the Flight Director in the respective mode(s).
When active, the Flight Director may be turned off by
pressing the FD key, if the Autopilot is not engaged.

NOTE: The FD key is disabled when the Autopilot
is engaged.

Mode Reference

Armed Mode

Pitch Axis Modes

Selected Altitude
Box

Flight Director
Command Bars

190-00609-00 Rev. B

Figure 9.2.1 PFD AFCS Display

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

9-5

FD OPERATION

AFCS Status Bar

Flight Director mode annunciations are displayed on

the PFD, whenever the Flight Director is active. Figure

9.2.1 shows each individual AFCS Status Bar field. Roll
modes are displayed on the left side and pitch modes are
displayed on the right. Armed modes are displayed in
white and active modes are displayed in green. Refer to
Section 9.3 for Flight Director mode information.

Command Bars

Upon activation, the Flight Director displays command
bars on the PFD. Figure 9.2.2 shows the command bars.
The command bars move together vertically to indicate
pitch commands, and will bank left or right to indicate
roll commands. If the attitude information being sent to
the Flight Director becomes invalid or unavailable, the
command bars are removed from the display.

9-6

Figure 9.2.2 Command Bars

Flight Director Limitations

The maximum commanded pitch and roll attitudes
are limited to values established during AFCS certifica­tion. Maximum commanded pitch and roll rates are also
limited. Pitch commands are limited to 20 degrees nose
up and 15 degrees nose down. Roll commands are lim­ited to 22 degrees of bank and a 5 degrees/second bank
rate. Limits may be different from these values in certain
modes, as noted in the section for the mode operation.

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

190-00609-00 Rev. B

FD MODES

9.3 FLIGHT DIRECTOR MODES

Flight Director modes are normally selected indepen­dently for the pitch and roll axes. Unless otherwise speci
fied, all mode keys are alternate action (i.e. press on, press
off).

PITCH MODES

The GFC 700 AFCS offers the following pitch modes:

• Pitch Hold (default)

• Altitude Hold

• Vertical Speed

• Flight Level Change

• Glideslope

• Go Around

Table 9.3.1 equates each pitch mode to the respective
key or switch, and gives accompanying mode annuncia
tions. Mode annunciations for pitch modes are shown in
green during normal operation.

Mode

Key

{default} Pitch Hold PIT

ALT Altitude Hold ALT FT nnnnn

VS Vertical Speed VS FPM nnnn

Pitch

Mode

Annunciation

Window

-

-

Overspeed Protection

While Vertical Speed, Flight Level Change, or default
Pitch Hold modes are selected, airspeed is monitored by
the Flight Director. In these modes, pitch commands
are limited to provide overspeed protection. Overspeed
protection occurs in situations where the Flight Director
cannot acquire and maintain the pitch mode reference for
the selected pitch mode without exceeding the certified
maximum Autopilot airspeed.

When in overspeed mode, the airspeed reference box
appears above the airspeed tape, flashing alternatively be­tween the annunciations depicted in the figure below:

Figure 9.3.1 Overspeed Annunciations

When an Autopilot overspeed warning occurs, the pi­lot should reduce engine power and/or adjust the pitch
reference to slow the aircraft. When the overspeed con­dition is resolved, the annunciation disappears and the
previous pitch mode resumes control.

GO AROUND Go Around GA

190-00609-00 Rev. B

FLC Flight Level Change FLC KT nnn

APR Glideslope GS

Table 9.3.1 Pitch Modes

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

9-7

FD MODES

Pitch Hold Mode (PIT)

When the Flight Director is activated (the FD key is
pressed), Pitch Hold is selected by default. Pitch Hold
mode is indicated by the annunciation ‘PIT’ appearing in
the active pitch mode field in green. In Pitch Hold mode,
the Flight Director maintains a constant pitch attitude,
known as a pitch reference. The pitch reference conforms
to the aircraft attitude at the moment of engagement.

Pitch Hold mode is active

Changing the Pitch Reference

When operating in Pitch Hold mode, the pilot can ad

­just the pitch reference using the NOSE UP/NOSE DN
keys in 0.5-degree increments. Flight Director pitch ref­erence can also be changed by pressing the CWS button,
hand-flying the aircraft to establish a new pitch reference,
then releasing the CWS button.

Altitude Hold mode is armed

9-8

Flight Director
command bars
maintain desired
pitch reference

Figure 9.3.2 Pitch Hold Mode

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

190-00609-00 Rev. B

FD MODES

Altitude Hold Mode (ALT)

The Altitude Hold mode is engaged by pressing the
ALT key. In this mode, the Flight Director establishes the
current aircraft altitude as the altitude reference.

Changing the Altitude Reference

If desired, the pilot can press the
hand-fly the aircraft to a new altitude reference. When
the CWS button is released at the desired altitude, the
new altitude is established as the altitude reference.

NOTE: If the Selected Altitude is captured during
CWS maneuvering, the Flight Director altitude
reference is not changed. To adjust the altitude
reference in this case, the pilot must again press
the CWS button after the Selected Altitude is
captured.

Altitude Hold Mode is active

CWS button and

Altitude Arm/Capture

Altitude Hold mode is armed automatically when the
Flight Director is in Pitch Hold, Vertical Speed, Flight
Level Change, and Go Around modes. This is indicated
by the annunciation ‘ALT’, shown in white to the right of
the active pitch mode as shown in Figure 9.3.3. When
armed, the Flight Director captures and levels off at the
Selected Altitude. When the Flight Director starts the al

­titude capture, it transitions to the Altitude Hold mode
and holds Selected Altitude. The white ‘ALT’ annuncia­tion moves to the active pitch mode field and flashes green
for ten seconds, indicating to the pilot the transition to
Altitude Hold mode.

Altitude Reference

Selected Altitude

Flight Director
command bars
hold pitch attitude
to maintain the
altitude reference

190-00609-00 Rev. B

Figure 9.3.3 Altitude Hold Mode

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

Selected Altitude Bug

9-9

FD MODES

Vertical Speed Mode (VS)

The Vertical Speed mode is activated by pressing the
VS key. The annunciation ‘VS’ appears in the active pitch
mode field, along with the vertical speed reference on the
right. A separate vertical speed reference box appears di­rectly above or below the Vertical Speed tape depending
on the whether the aircraft is climbing or descending. A
vertical speed reference bug is displayed on the tape as
well.

In Vertical Speed mode, the Flight Director acquires
and maintains the vertical speed reference established
by the pilot. Current aircraft vertical speed becomes the
vertical speed reference at the moment of Vertical Speed
mode engagement.

Vertical Speed Reference

Vertical Speed Mode is active

Flight Director

command bars

indicating a climb

at the prescribed

vertical speed,

to the Selected

Altitude

Changing the Vertical Speed Reference

The vertical speed reference is changed in 100-fpm in

­crements by using the NOSE UP/NOSE DN keys. Pilots
may also press the CWS button and hand-fly the aircraft
to attain a new vertical speed. Upon releasing the CWS
button, the new vertical speed reference is established.

NOTE: The vertical speed reference is limited to
between +1500 and –3000 fpm.

Altitude Hold Mode is Armed.

Selected Altitude

Vertical Speed
Reference Box

Vertical Speed
Reference Bug

9-10

Figure 9.3.4 Vertical Speed Hold Mode

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

190-00609-00 Rev. B

FD MODES

Flight Level Change Mode (FLC)

The Flight Level Change mode is selected by press­ing the FLC key. This mode acquires and maintains the
airspeed reference. The airspeed reference is displayed
directly above the airspeed tape and in the pitch reference
field to the left of the ‘FLC’ annunciation. The airspeed
reference is set to current aircraft airspeed when engaged.

NOTE: The Selected Altitude should be set before
engaging Flight Level Change mode.

Flight Level Change Mode is active

Airspeed Reference
Box

Flight Level Change mode maintains the airspeed ref­erence while climbing or descending to the Selected Alti­tude. The pilot must adjust the engine power to allow the
Autopilot to fly the aircraft at a pitch attitude which cor­responds to the airspeed reference and the desired flight
profile (descent or climb). The Flight Director maintains
current altitude until either engine power or the airspeed
reference are adjusted and does not allow the aircraft to
climb or descend away from the Selected Altitude.

Changing the Airspeed Reference

The airspeed reference may be adjusted in 1-knot
increments between 80 and 190 knots, using the

NOSE UP/NOSE DN keys. The pilot may also press the
CWS button, hand-fly the aircraft to a new airspeed, then
release the CWS button.

Airspeed Reference

Altitude Hold Mode is armed

Airspeed Reference
Bug

190-00609-00 Rev. B

Figure 9.3.5 Flight Level Change Mode

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

9-11

FD MODES

Glideslope Mode (GS)

Glideslope mode is only available when the Flight
Director is operating in the Approach mode. Glideslope
mode is automatically armed under the following condi­tions:

• A valid localizer frequency is tuned

• The LOC mode is selected on the HSI, with valid
deviation indicator

• The APR key is pressed

Figure 9.3.6 Glideslope Mode Armed

NOTE: Pressing the CWS button while the

Glideslope mode is active does not cancel the
mode. The Autopilot guides the aircraft back to
the glideslope upon releasing the CWS button.

Upon reaching the glideslope, the Flight Director tran­sitions to Glideslope mode and begins to intercept and
track the glideslope.

Approach Mode active, Autopilot engaged

Active ILS
frequency is tuned

Flight Director
command bars
indicating descent
on localizer/
glideslope path

LOC1 is the
active navigation
receiver on the
HSI

Glideslope Mode is active

Figure 9.3.7 Approach Mode

9-12

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

190-00609-00 Rev. B

Go Around Mode (GA)

Pressing the GA button engages the Flight Director in a
wings level, 7-degree pitch-up attitude. Go Around mode
disengages the Autopilot, and cancels all armed modes in­cluding Altitude Hold. Other roll modes may be selected
after Go Around mode engagement. Subsequent Auto­pilot engagement is also allowed. An attempt to modify
the pitch attitude (e.g with the CWS button or the NOSE
UP/NOSE DN keys) results in the Flight Director revert­ing to Pitch Hold mode.

Autopilot disconnect annunciation
Go Around Mode is
active for the Roll and
Pitch axis modes

flashes yellow for 5 seconds

FD MODES

Flight Director
command bars
indicating climb

190-00609-00 Rev. B

Figure 9.3.8 Go Around Mode

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

9-13

FD MODES

ROLL MODES

Wings Level/Roll Hold Mode (ROL)

The GFC 700 offers the following roll modes:

sence of a specific roll mode (i.e., the FD key is pressed),

• Roll Hold

Roll Hold mode is active under the following conditions:

• Heading Select

• Navigation

• Approach

• Go Around

The table below equates each roll mode to the respec

-

tive key and gives accompanying mode annunciations.

Key Function

Annunciation

Window

{default} Roll Default ROL

HDG Heading Select HDG

VOR Enroute
Arm/Capture/Track

VOR

Changing the Roll Reference

GPS Arm/Capture/Track GPS

NAV

APR

BC Arm/Capture/Track BC
LOC Arm/Capture/Track;

(No Glideslope)
GPS Arm/Capture/Track
VOR Approach

Arm/Capture/Track

LOC

GPS

VAPP

ILS Approach
Arm/Capture/Track
(Glideslope Pitch Mode

LOC

pressing the
angle, then releasing the CWS button. The selection of
Wings Level or Roll Hold is the same as for mode engage­ment.

automatically armed)

GA Go Around (Wings Level) GA

Whenever the Flight Director is activated in the ab-

• If the aircraft bank angle is

greater than or equal to

6 degrees, Roll Hold mode is selected by default.
The Flight Director maintains the roll attitude of
the aircraft at the moment of selection.

• If the aircraft bank angle is less than 6 degrees,
Wings Level is selected by default, and the Flight
Director rolls the wings level.

Both modes are annunciated by ‘ROL’.

Figure 9.3.9 Roll Hold Mode

The pilot can establish a new reference to hold by

CWS button, establishing the desired bank

9-14

Table 9.3.2 Roll Modes

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

190-00609-00 Rev. B

Heading Select Mode (HDG)

The Heading Select mode acquires and maintains the
Selected Heading shown on the PFD. The Selected Head­ing is adjusted by using the HDG knob on the PFD or
MFD. Adjustment is shown by a heading bug on the HSI
and by the Selected Heading box.

Turns are commanded in the same direction as the bug
movement, even if the bug is turned more than 180 de­grees from the present heading (e.g. a 270-degree turn to
the right). However, heading bug changes of more than
340 degrees at a time result in a turn reversal.

FD MODES

NOTE: Pressing the CWS button and hand-flying
the aircraft does not change the Selected Head­ing. The Autopilot guides the aircraft back to
the Selected Heading upon releasing the CWS
button.

Flight Director
command bars
tracking Selected
Heading

Selected Heading
Box

Heading Select Mode

Altitude Hold Mode is active

Selected Heading
Bug

Figure 9.3.10 Heading Select Mode

190-00609-00 Rev. B

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

9-15

FD MODES

Navigation Mode (GPS, VOR, LOC, or BC)

The Navigation mode acquires and tracks the selected
navigation receiver on the HSI (e.g. GPS, VOR or LOC).
The Flight Director follows GPS roll steering commands
when the HSI is in GPS mode, and creates roll steering
commands from the Selected Course and deviation when
the HSI is in VOR, LOC, or BC modes. The Selected
Course is controlled using the CRS knob.

Note that the selected navigation receiver must have
a valid signal (VOR, LOC) or active GPS course (GPS) in
order for the Flight Director to enter Navigation mode.

The Navigation mode can be used to fly non-precision
GPS and LOC approaches where glideslope tracking is not
required. It also automatically selects Backcourse mode
when the localizer front course is greater than 105 degrees
from the aircraft heading.

NOTE: When making a backcourse approach, set
Selected Course to the localizer front course.

Navigation/Approach Mode Armed

If the course deviation indicator is greater than 1 dot
when the Navigation or Approach modes are selected,
the mode is automatically armed. The armed annuncia

­tion appears in white to the left of the active roll mode as
shown in Figure 9.3.11.

Navigation/Approach mode (GPS selected on HSI) is armed

Figure 9.3.11 Approach Mode Armed

Navigation Mode is active, using GPS source

Flight Director
command bars
indicating a left
turn to track
GPS course and a
climb to intercept
Selected Altitude

Flight Level Change Mode is active, Altitude Hold is armed

Selected Course

GPS is active
navigation receiver
on the HSI

Figure 9.3.12 Navigation Mode

9-16

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

190-00609-00 Rev. B

Approach Mode (GPS, VAPP or LOC)

The Approach mode acquires and tracks the selected
navigation receiver on the HSI (GPS, VOR or LOC). This
mode uses the selected navigation receiver deviation and
desired course inputs to fly the approach. The Approach
mode provides greater sensitivity for VOR tracking than
Navigation mode, and allows the Autopilot to fly an ILS
approach with a glideslope.

NOTE: The Glideslope mode is automatically
armed when LOC mode is selected.

FD MODES

NOTE: Pressing the CWS button and hand-flying
the aircraft does not change the Selected Course
while in Navigation or Approach modes. The
Autopilot guides the aircraft back to the Selected
Course (or GPS Flight Plan) when the CWS button
is released.

Flight Director

command bars

indicating descent

on localizer/

glideslope path

LOC2 is the
active navigation
receiver on the
HSI

Approach Mode is active

Glideslope Mode is active

Figure 9.3.13 Approach Mode

190-00609-00 Rev. B

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

9-17

FD MODES

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

190-00609-00 Rev. B

AUTOPILOT

9.4 AUTOPILOT AND YAW DAMPER OPERATION

OVERVIEW

The Autopilot controls the aircraft pitch and roll atti­tudes, while following commands received from the Flight
Director. Pitch autotrim provides trim commands to the
pitch trim servo, to relieve any sustained effort required
by the pitch servo. The Yaw Damper reduces Dutch roll
tendencies and coordinates turns.

Autopilot Engagement

When the AP key is pressed, the system engages (acti­vates) the Autopilot and the Yaw Damper, if they are not
already engaged. If the Flight Director is not already ac­tive, it is also activated when the AP key is pressed, and
starts in default pitch and roll modes.

Autopilot engagement is displayed in the center of the
AFCS mode annunciator field. Autopilot engagement is
indicated by a green ‘AP’ and is accompanied by a green
‘YD’ to indicate Yaw Damper operation unless the Yaw
Damper has been disengaged.

Autopilot Disengagement

Automatic Disengagement

Automatic disengagement typically occurs due to a
system failure. Automatic disengagement is indicated by
a flashing red ‘AP’ annunciation and by the Autopilot dis
connect aural alert, which continue until acknowledged.
To acknowledge the disconnect, the pilot can press the AP
DISC button or the MET ARM switch.

For the Yaw Damper, automatic disengagement will
occur when the Autopilot disengagement is caused by a
failure in a parameter that also affects the Yaw Damper.
This means that the Yaw Damper can remain operational
in some cases where the Autopilot will automatically dis­engage. The Yaw Damper will also disengage upon a lo­calized failure in the Yaw Damper system.

Automatic Disconnect

Figure 9.4.2 Automatic Disconnect Annunciation

-

190-00609-00 Rev. B

Autopilot Engaged

Figure 9.4.1 Autopilot Engaged Annunciation

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

9-19

AUTOPILOT

Manual Disengagement

The Autopilot may also be manually disengaged

by pressing the AP DISC button, the

GA button, the

MET ARM switch, or the AP key on the MFD. Manual

disengagement is indicated by a five-second flashing yel­low ‘AP’ annunciation and by a two-second Autopilot dis­connect aural alert. The AP DISC button or MET ARM
switch may be used to cancel the aural alert (the aural
alert only lasts 2 seconds).

Manual Disconnect

Figure 9.4.3 Manual Disconnect Annunciation

NOTE: Autopilot engagement/disengagement

is not the same as servo engagement/disen­gagement. Servos can be disengaged while the
Autopilot remains engaged (active) through the
use of the CWS switch.

Control Wheel Steering

For most scenarios, releasing the CWS button reen­gages the Autopilot with a new reference. Refer to the
Flight Director Modes section for exact CWS behavior for
each mode.

Yaw Damper

When the YD key is pressed, the system toggles the en-
gagement of the Yaw Damper. Yaw Damper engagement is
indicated by a green ‘YD’ in the center of the AFCS mode
annunciator field. Pressing the AP DISC button will also
disengage the Yaw Damper.

9-20

During Autopilot operations, the pilot may wish to
hand-fly the aircraft without disengaging the Autopilot.
Pressing and holding the CWS button disengages the ser­vos from the flight control surfaces and allows the pilot
to hand-fly the aircraft. At the same time, the Flight Di­rector is synchronized to the aircraft attitude during the
maneuver. The ‘AP’ annunciation is temporarily replaced
by ‘CWS’ in white for the duration of CWS activity.

Control Wheel Steering

Figure 9.4.4 CWS Annunciation

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

190-00609-00 Rev. B

AUTOPILOT

FLIGHT CONTROL

Emergency Control Override

The GSM 85 servo mounts are equipped with slip­clutches that are preset to certain values. This allows the
servos to be overridden in case of an emergency.

NOTE: Refer to the approved AFMS for specific
instructions regarding emergency procedures.

Flight Director - Autopilot Interface

The Flight Director function provides pitch and roll
commands to the GSA 81 servos, based upon the cur­rently active Flight Director modes.

Pitch Axis

The pitch axis of the Autopilot uses pitch attitude rate
to stabilize the aircraft pitch attitude during aircraft up
sets or Flight Director maneuvers. The Flight Director
pitch commands are rate, acceleration, and attitude lim­ited, summed with pitch rate, then sent to the pitch servo
motor.

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Roll Axis

The roll axis of the Autopilot uses roll attitude rate to
stabilize the aircraft roll attitude during upsets or Flight
Director maneuvers. The Flight Director roll commands
are rate, acceleration, and attitude limited, summed with
roll rate, and sent to the roll servo motor.

Yaw Axis

The Yaw Damper uses yaw rate and roll attitude to
damp the natural Dutch roll response. It also uses lateral
acceleration to provide turn coordination. Yaw Damper
operation is independent of Autopilot engagement.

Pitch Trim

The pitch servo measures the output effort (torque)
and provides this signal to the pitch trim servo. The pitch
trim servo commands the motor to reduce the average
pitch servo effort.

When the Autopilot is not engaged, the pitch trim
servo may be used to provide a Manual Electric Pitch
Trim function. This allows the pilot to operate trim from
a control-wheel switch in lieu of manually operating the
trim wheel. Trim speeds are scheduled with airspeed to
provide more consistent response.

190-00609-00 Rev. B

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

9-21

AUTOPILOT

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

190-00609-00 Rev. B

9.5 PROCEDURES

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VOR

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CZQ)

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PROCEDURES

This section provides a scenario-based set of proce­dures showing various GFC 700 modes used during a
flight. In this scenario, the aircraft departs Reid-Hillview
Airport (KRHV) from runway 13L, en route to Fresno
Yosemite International Airport (KFAT). The pilot desires
to climb to an altitude of 7,000 feet MSL and fly head­ing of 070 degrees to intercept airway V107. The pilot
flies airway V107 to Panoche VORTAC (PXN) using VOR
navigation, then flies airway V230 using a GPS flight plan.
On this leg, the pilot descends to 3,000 feet prior to reach­ing Clovis VORTAC (CZQ) and loads the ILS approach to
R29R at KFAT. The pilot then flies the ILS approach and
executes a missed approach. Figure 9.5.1 depicts a map
of the flight plan.

NOTE: The diagrams in the following examples
are for instructional purposes only and may not
be current.

190-00609-00 Rev. B

Figure 9.5.1 Flight Plan Overview

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

9-23

PROCEDURES

1.

2.

3.

4.

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VS

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ALT Mode

Selected Altitude of 7,000 MSL

5.

Departure

To Climb to Selected Altitude and Fly an
Assigned Heading:

1. Upon takeoff, the pilot sets the Selected Alti
tude to 7,000 feet, using the
the Autopilot capture this altitude, the pilot
may select from Pitch Hold, Vertical Speed, or
Flight Level Change. In this example, Vertical
Speed is used.

2. Upon reaching the desired vertical speed
of 1,000 fpm, the pilot presses the
enabling the Flight Director in Vertical Speed
mode. Altitude Hold is armed automatically.

After activating Vertical Speed mode, the pilot

presses the AP key, engaging the Autopilot in
default roll (ROL) and Vertical Speed modes.

ALT

knob. To have

VS

key,

3. With the Autopilot engaged in a climb, the pilot
sets the Selected Heading to 070 degrees using
the

HDG

knob, then presses the

HDG

Autopilot follows the heading bug on the HSI

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and turns the aircraft to the desired heading.

4. As the aircraft climbs to the Selected Altitude,
the Flight Director changes from Vertical
Speed mode to Altitude Hold mode. This is
annunciated by the green ‘ALT’ annunciation
flashing for ten seconds, informing the pilot of
the new mode.

5. Upon reaching the Selected Altitude, the
Autopilot completes the capture process and
levels the aircraft. From this point, the Flight
Director continues to operate in Altitude Hold
mode.

key. The

9-24

Figure 9.5.2 Departure

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

190-00609-00 Rev. B

Intercepting a VOR

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VOR Mo

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(PX

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After climbout, the Autopilot continues to fly the aircraft
on a heading of 070 degrees at an altitude of 7,000 feet.
The pilot now wishes to intercept airway V107 to Panoche
VORTAC (PXN).

To Intercept a VOR:

1. The pilot tunes the VOR frequency, then sets

CDI

the HSI mode to VOR, using the

Selected Course is then set to 116 degrees

CRS

using the

knob. Note that at this point,
the Flight Director is still in Heading mode and
the Autopilot continues to fly 070 degrees.

NAV

The pilot presses the

key. This arms the
Navigation mode and the white annunciation
‘VOR’ appears to the left of the active pitch
mode.

softkey.

PROCEDURES

2. At a predetermined point, the Flight Director
changes from Heading mode to Navigation
mode, and the green annunciation ‘VOR’
flashes. The Autopilot begins turning to inter­cept the Selected Course.

3. The Autopilot continues the turn until the
aircraft is established on the Selected Course.

NOTE: Changing the HSI mode cancels the
Navigation mode and causes the Flight Director
to revert back to the default roll (ROL) mode.

190-00609-00 Rev. B

Figure 9.5.3 Intercepting a VOR

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

9-25

PROCEDURES

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Clovis�

VORTAC

(CZQ)

Panoche�
VORTAC

(PXN)

Flying a Flight Plan/GPS Course

As the aircraft closes upon Panoche VORTAC, the pilot
chooses to enter and fly a GPS flight plan for the next leg,
airway V230. To do this, the pilot enters PXN, CZQ, and
KFAT into the active flight plan.

To fly a GPS Flight Plan:

1. The aircraft is currently tracking inbound on
the 116 degree radial of Panoche VORTAC.
The pilot enters Panoche VORTAC (PXN) and
Covis VORTAC (CZQ) into the GPS flight plan,
in preparation to intercept this leg.

2. With the flight plan entered, the pilot presses
the

CDI

softkey until the HSI is in GPS mode.
Doing this cancels VOR mode on the HSI, and
the Flight Director loses the VOR signal. As a
result, the VOR annunciation flashes yellow and
the Flight Director reverts to default roll (ROL)
mode.

Flashes for five seconds, then transitions to ROL

The pilot must then press the

NAV

key to reac­tivate the Flight Director roll mode to use GPS
guidance. At this moment, the Flight Director
couples to GPS guidance and the Autopilot
steers the aircraft toward the active flight plan
leg.

3. Once the flight plan leg is intercepted, the
Autopilot continues to track GPS guidance to
the end of the flight plan.

9-26

Figure 9.5.4 Transition to GPS Flight

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

190-00609-00 Rev. B

PROCEDURES

1.

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Cruise Altitude of 7,000 MSL

Selected Altitude of 3,000 MSL

ALT Hold Mode

F

L

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e

Flight Level Change Descent

While flying the GPS leg from Panoche VORTAC to
Clovis VORTAC, the pilot chooses to make a Flight Level
Change descent to 3,000 feet in preparation for the ap­proach to KFAT.

To make a Flight Level Change descent:

1. The pilot sets the Selected Altitude to 3,000 feet

ALT

using the

FLC

key. This activates the Flight Level Change
mode. The annunciation ‘FLC’ appears along
with the airspeed reference, which defaults
to the current aircraft airspeed. Altitude Hold
mode is also armed automatically. The pilot
chooses to descend at the current cruise speed
of 142 knots.

2. To allow the Flight Level Change mode to
descend, the pilot reduces power. The Autopilot
maintains 142 knots.

knob. Then the pilot pushes the

3. At the predetermined point, the Flight Direc­tor changes from Flight Level Change mode
to Altitude Hold mode. The annunciation
‘ALT’ flashes in green, informing the pilot of
the capture. After the capture is finished, the
Autopilot holds the aircraft level at the Selected
Altitude.

190-00609-00 Rev. B

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

Figure 9.5.5 FLC Descent

9-27

PROCEDURES

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APPROACHES

ILS Approach

To fly an ILS Approach:

1. The pilot loads the Runway 29R ILS approach
for KFAT into the Flight Plan. The Pilot selects
‘Vectors to Final’ for the transition. Upon
being given vectors from ATC, the pilot sets
the Selected Heading and presses the
The Autopilot turns the aircraft to the desired
heading.

HDG

key.

2. The pilot uses the Heading mode to comply
with ATC vectors, as requested.

3. In preparation for the approach and at the
pilot’s discretion, the pilot tunes the localizer
frequency, then selects the LOC mode on the
HSI.

4. When cleared for the approach, the pilot arms

APR

the Approach mode by pressing the

key.
LOC and GS appear in the roll and pitch armed
field, respectively. The Autopilot and Flight
Director determine when to begin the turn to
intercept the final approach course.

9-28

Figure 9.5.6 ILS Approach to KFAT

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

190-00609-00 Rev. B

PROCEDURES

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GA Mode

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HDG Mode

GPS Mode

CZQ

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5. From this point, the Autopilot flies the ILS. At
the Decision Height, the pilot can press the

AP DISC

button and land the aircraft, or press

the GA button to execute a missed approach.

Go-Around/Missed Approach

To fly a Missed Approach:

1. At the Decision Height, the pilot decides to
execute a missed approach. The pilot applies
climb power and presses the
Flight Director command bars establish a 7­degree nose-up climb for the pilot to follow.
Note that when the GA button is pressed, the
Autopilot disconnects and the AP annunciation
flashes yellow for five seconds.

2. Following the published Missed Approach
Procedure, the pilot climbs to the prescribed
altitude. The pilot presses the
engaging the Autopilot. To have the Autopilot
fly to the hold, the pilot sets the HSI to GPS
mode and presses the
flies direct to Clovis VORTAC according to the
loaded approach.

3. During the climb, the pilot sets a Selected
Altitude at which to hold using the
To climb to the holding altitude, the pilot may
use the
Go Around pitch mode. Doing this causes the
Flight Director to revert to the default Pitch

CWS

Hold (PIT) mode where Altitude Hold is armed.
The pilot may then choose another pitch mode
to continue with the climb, if desired.

GA

button. The

AP

key, re-

NAV

key. The Autopilot

ALT

knob.

button momentarily to cancel the

4. At the holding pattern, the pilot commences
with the hold. To fly the hold using the Auto
pilot, the pilot sets Selected Heading using the

HDG

knob and presses the

HDG

key. The

HDG

knob is used for the remainder of the hold to
guide the aircraft.

Figure 9.5.7 Go Around/Missed Approach

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190-00609-00 Rev. B

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

9-29

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190-00609-00 Rev. B© 2005 Garmin Ltd. or its subsidiaries