AIRCRAFT FLIGHT
MANUAL
BRISTELL B23
Document No.: ADXC-73-001-AFM
Non-approved page
Revision: A2
7-44
Date of Issue: 15.04.2021
control stick (CWS), by pressing any trim button or by pressing the AP
Key on the GMC 307.
NOTE
In case of trim system failure (loss of power to trim system) the AP
disconnect by trim button is also inoperative
Manual disengagement is indicated by a five-
second flashing yellow ‘AP’
annunciation and an aural alert. Cancel the aural alert by pressing and
releasing the AP/CWS Button again (GSA 28 autopilot only) Automatic
disengagement is indicated by a flashing red ‘AP’ annunciation and an
aural alert. Touch to acknowledge. Automatic disengagement occurs due
to: System failure, Invalid sensor data or Inability to compute default
autopilot modes.
A small amount of pressure or force on the pitch controls can cause the
autopilot automatic trim to run to an out-of-trim condition. Therefore, any
application of pressure or force to the controls should be avoided when
the autopilot is engaged. Overpowering the autopilot during flight will
cause the autopilot’s automatic trim to run, resulting in an out-of-trim
condition or cause the trim to hit the stop if the action is prolonged. In this
case, larger than anticipated control forces are required after the
autopilot is disengaged.
Abnormal occurrences
If an autopilot failure or trim failure is suspected to have occurred,
perform the
following steps:
1) Firmly grasp the control stick.
2) Press and hold the AP DISC Switch. The autopilot will disconnect and
power is removed from the trim motor. Power is also removed from all
primary servo motors and engaged solenoids. Note the visual and aural
alerting indicating autopilot disconnect.
3) Retrim the aircraft as needed. Substantial trim adjustment may be
needed.
4) Pull the appropriate circuit breaker(s) to electrically isolate the servo
and solenoid components.
5) Release the AP DISC Switch.