Piper Arrow IV, Руководство по обслуживанию, Страница: 236 / 752

GENERAL.
This chapter 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.
DESCRIPTION AND OPERATION.
The airplane 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 wheels
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 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 bellcrank which in turn is connected to the stabilator by a push-pull tube.
When the control wheels are moved forward or aft, the cables move the bellcrank up and down pushing or
pulling the tube which rotates 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.
TROUBLESHOOTING.
Troubles peculiar to the Flight Controls are listed in Chart 2701, along with their probable causes and
suggested remedies.
27-00-02
Page 27-01
Revised: July 13, 1983
1J20
PIPER AIRCRAFT
PA-28RT-201 / 201T
MAINTENANCE MANUAL