PIPER AIRCRAFT, INC.
PA-28-161, WARRIOR III
MAINTENANCE MANUAL
PAGE 1
Nov 30/06
2G7
27-00-00
GENERAL
1. Description and Operation
The PA-28-161 Warrior III is controlled in flight by standard three-axis control surfaces, consisting of
ailerons (roll), stabilator (pitch) and rudder (yaw). Operation of these controls is through the movement of
dual control columns and dual rudder pedal sets. The individual surfaces are connected to their control
components through the use of cables and push-pull tubes. Provision for directional (yaw) and
longitudinal (pitch) trim control is provided by adjustable trim mechanisms for the rudder and stabilator,
respectively. The flaps are mechanically operated and can be positioned in four locations: 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. On early
installations a self-centering system was part of the aileron controls to maintain wings level attitude.
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 and
down rotating the stabilator at 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.
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