Piper PA-28-236 DAKOTA, Pilot Operating Handbook

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SECTION 9 PIPER AIRCRAFT CORPORATION
SUPPLEMENT 11 PA-28-236, DAKOTA
REPORT: VB-910 ISSUED: OCTOBER 14, 1986
9-86
(14.) Press the DN switch - the TEST light remains off as long as
the DN switch is held.
(15.) Press the UP switch - the TEST light remains off as long as
the UP switch is held.
(16.) Momentarily press the TEST switch - HDG and ATT lights
remain on and the TEST light goes out.
b. COMMAND TRIM SYSTEM - To be performed before the first
flight of each day. ·
(1.) Using the control wheel trim switch, verify normal trim up
and down operation.
(2.) Press and hold the center bar on the control wheel trim switch.
Observe that the trim system does not operate.
(3.) Release the center bar on the control wheel trim switch. Move
the control wheel trim switch fore and aft. Observe that the
trim system does not operate.
This completes the test sequences.
CAUTIONS
Any failure of the above procedures indicates
that a failure exists in the system and the system
shall not be operated until the failure. has been
located and corrected.
Check the elevator trim position before takeoff.
c. COMPASS SYSTEM (NSD 360A)
(For other compass systems, refer to appropriate manufacturer’s
instructions)
(1.) Check slaving switch in SLAVE or SLAVE No. 1 or No. 2
position, as appropriate. (Slaving systems with RMI output
provide only slave and free gyro positions.)
(2.) Rotate card to center slaving meter - check HDG displayed
with magnetic compass HDG.
(3.) Perform standard VOR receiver check.
2. IN-FLIGHT PROCEDURE - AUTOPILOT
a. Rotate heading bug to desired heading.
b. Trim aircraft for existing flight condition (all axes). Engage
autopilot.
c. During maneuvering flight - control aircraft through use of the
heading bug and the pitch modifier. (HDG-ATT modes)