Piper PA-28-236 DAKOTA, Pilot Operating Handbook

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PIPER AIRCRAFT CORPORATION SECTION 9
PA-28-236, DAKOTA SUPPLEMENT 9
ISSUED: JULY 23, 1982 REPORT: VB-910
9-73
Figure 7-15 (cont)
1. AUTOPILOT CONTROL WHEEL SWITCH CAP - Molded
plastic unit mounted on the left horn of the pilot’s control wheel
which provides mounting for three switch units associated with
the autopilot and manual electric trim systems.
2. MANUAL ELECTRIC TRIM CONTROL SWITCHES - A
split switch unit in which the left half provides power to engage
the trim servo clutch and the right half to control the direction
of motion of the trim servo motor. Both halves of the split trim
switch must be actuated in order for the manual trim to operate
in the desired direction. When the autopilot is engaged, operation
of the manual electric trim will automatically disconnect the
autopilot.
3. CONTROL WHEEL STEERING (CWS) BUTTON - When
depressed, allows pilot to manually control the aircraft (disengages
the servos) without cancellation of any of the selected modes.
Will engage the Flight Director mode if not previously engaged.
Automatically synchronizes the Flight Director/ Autopilot to the
pitch attitude present when the CWS switch is released, or to the
present pressure altitude when operating in the ALT hold mode.
Will cancel GS couple. The aircraft must pass through the glide
slope to allow GS recouple.
4. AUTOPILOT DISCONNECT/TRIM INTERRUPT (AP DISC/
TRIM INTER) Switch - When depressed and released will
disengage the autopilot and cancel all operating Flight Director
modes. When depressed and held will interrupt all electric trim
power (stop trim motion), disengage the autopilot, and cancel all
operating Flight Director modes.