Piper PA-28-236 DAKOTA, Pilot Operating Handbook

Page: 335 / 367

PIPER AIRCRAFT CORPORATION SECTION 9
PA-28-236, DAKOTA SUPPLEMENT 11
ISSUED: OCTOBER 14, 1986 REPORT: VB-910
9-85
SECTION 4 - NORMAL PROCEDURES
1. PREFLIGHT PROCEDURES
NOTE
During system functional check the system
must be provided adequate de voltage (12.0
Vdc min.) and instrument air (4.8 in. Hg. min.).
It is recommended that the engine be operated
to provide the necessary power and that the
aircraft be positioned in a level attitude, during
the functional check.
a. AUTOPILOT/ AUTOTRIM - To be performed before the first
flight of each day.
(1) Trim system switch - on.
(2.) Engage autopilot.
(3.) Move the heading bug left and right of the lubber line.
Observe that the control wheel moves in the direction of the
heading bug displacement.
(4.) Press the DN switch - verify that the control wheel moves in
the down direction. Verify that after approximately a 3 second
delay, the trim moves in the down direction.
(5.) Press the UP switch - verify that the control wheel moves in
the up direction. Verify that after approximately a 3 second
delay, the trim moves in the up direction.
(6.) Grasp control wheel and override roll and pitch servo
actuators to assure override capability.
(7.) Hold control yoke and disengage autopilot by activating the
AP OFF switch on the control wheel.
(8.) Check controls through full travel in roll and pitch to assure
complete autopilot disengagement.
(9.) Press and hold the TEST switch - all mode annunciators light
with AP flashing.
(10.) Release the TEST switch after all annunciator lights except
HDG, ATT, and TEST turn off.
(11.) Press the DN switch - HDG, ATT and TEST remain on.
(12.) Press the UP switch - HDG, ATT and TEST remain on.
(13.) Momentarily press the TEST switch - HDG and ATT remain
on, TEST flashes.