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Garmin G1000 Cockpit Reference Guide for the Beechcraft A36/G36

SECTION 6 – AUTOMATIC

FLIGHT CONTROL

6-3

Automatic Disengagement

Automatic disengagement typically occurs due to a

failure. Automatic disengagement is annunciated by a

ﬂashing ‘AP’, alternating red on white and white on red

in the Autopilot Status ﬁeld. Also, the autopilot discon-

nect aural alert will be heard. Both the annunciation and

the aural alert will continue until acknowledged by press-

ing the AP DISC button or the MET ARM switch. The

Yaw Damper may or may not disengage, depending on the

cause of the automatic AP disengagement.

Figure 6-6 Automatic Disconnect Annunciation

Automatic Disconnect

Manual Disengagement

The autopilot may also be manually disengaged

by pressing the AP DISC button, the

GA button, the

MET ARM switch, or by pressing the AP key on the MFD.

Manual disengagement is annunciated by a ﬁve-second

ﬂashing yellow ‘AP’ in the Autopilot Status ﬁeld and by

a two-second Autopilot disconnect aural alert. The Yaw

Damper will also disengage with the autopilot.

Figure 6-7 Manual Disconnect Annunciation

Manual Disconnect

Control Wheel Steering

Pressing and holding the CWS button disengages the

servos from the ﬂight control surfaces and allows manual

manuevering of 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 until the CWS button is released.

Figure 6-8 CWS Annunciation

Control Wheel Steering

Yaw Damper

When the autopilot is engaged, the Yaw Damper is au-

tomatically engaged. When the Yaw Damper is active, the

‘YD’ annunciation appears in the Yaw Damper Status ﬁeld

as shown:

Yaw Damper is active.

Figure 6-9 Yaw Damper Active

To disengage the Yaw Damper, press the YD key, or use

the MET switch. The ‘YD’ annunciation turns yellow and

ﬂashes for ﬁve seconds upon disengagement:

Yaw Damper is disengaging.

Figure 6-10 Yaw Damper Disengagement

6.4 LOSS OF DATA

In general, a ﬂashing yellow mode annunciation indi-

cates either the loss of sensor data (AHRS, ADC, or GIA)

or loss of navigation data (VOR, LOC, or GPS) required to

compute commands.

When such a loss occurs, the system automatically re

verts to the default mode for the affected axis (ROL for roll

axis, PIT for pitch axis). The ﬂashing annunciation stops

when the pilot presses the affected mode button or selects

another mode for the axis. If no pilot action is taken, the

ﬂashing annunciation stops after ten seconds.

Figure 6-11 Loss of VOR Signal

6.5 PITCH AXIS MODES

Mode annunciations for active pitch axis modes are

shown in green during normal operation. Note the Go-

Around button is not located on the MFD.

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