SECTION V
SURFACE CONTROLS
5-1. INTRODUCTION. This section contains the explanation for the removal, installation, rigging and
adjustment procedures for the control assemblies of the various structural surfaces. The assemblies need not be
removed in order of paragraphs since each paragraph describes the individual removal and installation of the
component. For the removal and installation of the structural surfaces of the airplane, refer to Section IV.
5-2. DESCRIPTION. The aircraft is controlled in flight by the use of three standard primary control surfaces,
consisting of the ailerons, stabilator and rudder. Operation of these controls is through the movement of the dual
control columns and dual rudder pedals. The individual surfaces are connected to the control components
through the use of cables and push-pull tubes. Provision for directional and longitudinal trim control is provided
by an adjustable trim mechanism for the rudder and stabilator. The flaps are mechanically operated and can be
positioned in four locations of 0, 10, 25, and 40 degrees.
The aileron controls consist of two-control wheels connected by torque tubes to sprockets on each end of the
horizontal control column. A chain is wrapped around the sprockets and around a double socket on the vertical
post of the control column. The chain is connected to the primary aileron control cable which is routed through
the center of the fuselage to the main spar and out through the wings to a bellcrank in each wing. A balance
cable is also connected to the bellcrank. As the control wheels are moved, the control cables move the bellcranks
and actuate push-pull rods to move the ailerons.
The stabilator controls are also connected to the control column. From the connecting point, cables are
routed around a series of pulleys down under the floor and aft to the tail section of the airplane. The aft end of
the cables connect to the stabilator balance arm which in turn is connected to the stabilator. When the control
wheels are moved forward or aft, the cables move the balance arm on the stabilator up or down rotating the
stabilator at its hinge points.
The rudder is controlled by the pilot's and copilot's rudder pedals. Cables are connected to both sides of the
rudder pedal assembly and are routed aft through the bottom of the fuselage to the rudder horn. When one rudder
pedal is pushed, the cables move in opposite directions turning the rudder horn and rudder. The wing flap system
is operated by a lever located between the front seats.
For a visual description of the various control systems, refer to the illustrated figures throughout this section.
5-3. STANDARD PROCEDURES. The following tips may be helpful in the removal, installation and rigging of
the various assemblies:
a. It is recommended, though not always necessary to level and place the airplane on jacks during rigging and
adjustment.
b. Remove turnbuckle barrels from cable ends before withdrawing the cables through the structures.
c. Tie a cord to the cable end before withdrawing the cable through the structures to facilitate reinstallation of
the cable.
d. Turnbuckle stations are given at their neutral positions.
e. When referring to marking cable ends, etc., before disconnecting, a felt marking pen may be used.
f. Assemble and adjust the turnbuckles so that each terminal is screwed an approximately equal distance into
the barrel. Do not turn the terminals in such a manner that will put a permanent "twist" into the cables.
PIPER AIRCRAFT
PA-28-161 CADET
AIRPLANE MAINTENANCE MANUAL
Issued: FEBRUARY 28, 1989
S U R FACE CONTROL
1F22
