PIPER CHEROKEE SERVICE MANUAL
V - SURFACE CONTROLS
01/31/08
2A10
SECTION V
SURFACE CONTROLS
5-1. INTRODUCTION.
This section contains removal, installation, rigging, adjustment and trim procedures for ailerons, flaps
(less trim), stabilator and rudder flight control surfaces. Also included are similar procedures for the
control column and rudder and steering pedal assembly. For removal, installation, and repair of structural
surfaces of the airplane, refer to Section IV.
5-2. DESCRIPTION.
The PA-28 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 their 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 on the PA-28 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 sprocket 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 up and down rotating the
stabilator on its hinge points.
The rudder is controlled by the pilot’s and co-pilot’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.
Summary of Contents for Cherokee 140 PA-28-140
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