flight director will engage altitude capture and then
During transitions to armed altitudes the flight
control system will briefly sound an alert tone when the
aircraft passes within 1000 feet of the selected
altitude. In addition, an alert annunciator illuminates
on the altitude/vertical speed indicator when the
aircraft is between 1000 and 300 feet above or below
the armed altitude. The annunciator will illuminate
again briefly when the aircraft reaches the selected
altitude. Subsequent alerts are provided if the aircraft
deviates 300 feet or more from the selected altitude.
Altitude select will engage automatically with
selection of climb or descent modes, provided that a
higher or lower altitude is displayed in the altitude pre-
select window on the altitude and vertical speed
Illumination of the altitude hold mode annunciator,
placarded ALT, indicates that the altitude hold mode
has been selected and is engaged.
Selector Switch. Pressing the altitude hold push-
button selector switch, placarded ALT, selects the
flight director altitude hold mode.
In the altitude hold mode the flight director
commands pitch attitudes for capture and tracking of
the barometrically corrected aircraft altitude current at
the moment of mode selection. Altitude hold can be
entered directly or in conjunction with the altitude
select mode. Engaging altitude hold directly during a
climb or descent will allow the aircraft to fly through the
desired altitude and then recover from the other side.
For this reason, altitude is most useful for engagement
when vertical speed is less than 500 feet per minute.
Selecting altitude hold after the altitude select
mode has been engaged cancels altitude select and
causes the ARM annunciator to extinguish. The flight
director will command the aircraft to hold the altitude
present at the moment of mode selection.
Altitude hold commands may be modified by
holding the autopilot vertical trim rocker switch in the
up or down position either momentarily or for several
seconds at a time. Momentary switch activation
modifies target altitudes at the rate of 20 feet per click.
Continuous vertical trim operation causes the flight
appropriate, at 500 feet per minute until the switch is
m. Autopilot Operation.
(1) Autopilot Self Test.
1. AVIONICS MASTER PWR ON.
2. EFIS POWER switches ON.
3. AP / TRIM POWER switch ON.
4. Allow 3-4 minutes for gyros to erect
HDG and ATTITUDE flags clear.
5. AP FAIL and AP TRIM FAIL
Annunciators illuminate upon initial
application of AP/TRIM POWER and
then extinguish (followed by an audio
test tone) after successful completion
of the self-test. Allow 60 seconds
after gyros are valid.
temporarily engages the servos during the
overpower the autopilot as required.
Illumination of the AP FAIL annunciator
other than during initial power-up indicates
a failure. This failure annunciation will
result in power being removed from the
roll, pitch, yaw, pitch trim, and rudder trim
servos. The flight director may remain
functional depending upon the nature of
the failure. The continual self-test feature
may also inhibit flight director, autopilot
and electric trim use without illumination of
the AP FAIL annunciator.
(2) Flight Control/Autopilot System Preflight
1. AP XFER switch Select pilot's side.
2. AP mode selector button (AP ) Press
to engage autopilot.
3. Flight controls Overpower autopilot
in pitch, roll, and yaw axis.
If unable to overpower the autopilot in any
axis, do not use.
4. Auto trim Check.