Piper PA-28-236 DAKOTA, Pilot Operating Handbook

Page: 287 / 367

PIPER AIRCRAFT CORPORATION SECTION 9
PA-28-236, DAKOTA SUPPLEMENT 8
ISSUED: JUNE 9, 1982 REPORT: VB-910
9-37
SECTION 7- DESCRIPTION AND OPERATION
The KAP 100 Autopilot is certified in this airplane with roll axis control.
The various instruments and the controls for the operation of the KAP 100
Autopilot are described in Figures 7-1 thru 7-11.
The KAP 100 Autopilot has an optional electric pitch trim system. The
trim system is designed to withstand any single inflight malfunction. A trim
fault is visually and aurally annunciated.
A lockout device prevents autopilot engagement until the system has
been successfully preflight tested.
The following conditions will cause the Autopilot to automatically
disengage:
(a) Power failure. .
(b) Internal Flight Control System failure.
(c) With the KCS 55A Compass System, a loss of compass valid
(displaying HDG flag) disengages the Autopilot when a mode using
heading information is engaged. With the HDG flag present only the
autopilot wings level mode can be selected.
(d) Roll rates in excess of 16° per second will cause the autopilot to
disengage except when the CWS switch is held depressed.