Piper PA-24 Comanche, Руководство по обслуживанию, Страница: 249 / 846

PIPER COMANCHE SERVICE MANUAL
04/01/09 V - SURFACE CONTROLS
1F15
SECTION V
SURFACE CONTROLS
5-1.
Introduction
This section is comprised of information for removal installation, rigging and adjustment of surface
controls and their related component throughout the PA-24 series aircraft. For the removal and
installation of structural surfaces refer to Section IV.
5-2.
Description.
The primary flight controls of the PA-24 series are of the conventional type operated by dual control
wheels and dual sets of rudder pedals. A system of cables, pulleys, bellcranks and push-pull rods transfer
the movement of the control wheel and rudder pedals to the ailerons, stabilator and rudder.
The aileron controls consist of two control wheels connected by torque tubes to sprockets on each end of
the square tubes. A chain is wrapped around the sprockets to synchronize the control wheels. An
additional chain and sprocket is fixed on the left control tube which is coupled to the primary aileron
control cable. The cable is routed under the floor along the side of the fuselage to the main spar and out
through the wings to the bellcrank in each wing. A one piece balance cable is also connected to the
bellcranks. As the control wheels are moved, the control cables move the bellcranks and actuate push-
pull rods to move the ailerons.
The stabilator control cables are connected to the control wheel torque tubes. From the connecting
points, cables are routed around a series of pulleys 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 torque tube. When the control wheel is moved forward or aft, the cables move the balance arm
up and down turning the torque tube and stabilator.
The rudder is controlled by rudder pedals installed on both the pilot and copilot sides. 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 cable pulls the rudder horn turning the
rudder. The rudder pedals also turn the nose wheel when in the down and locked position. Refer to
Section VI which covers Landing Gear and Brake System.
The stabilator trim is operated by an overhead crank in the cockpit and controlled by cables extending
through the cabin ceiling to the tail Section. As the crank is turned, the cable moves, which in turn
rotates a drum in the tail section. A push-pull rod is connected to an actuator screw which in turn is
moved by the cable drum. The push-pull rod is attached to the stabilator trim tab. When the actuator
screw is moved, the push-pull rod moves the trim tab.
The rudder trim is operated by a control knob mounted below the instrument panel on the nose gear
wheel well cover and controlled by tubes and bungee mechanism extending forward to the nose gear
steering arm. The movable surfaces have adjustable stops as well as adjustments on their cables or
control rods, so their range of movement can be altered. Table V-I shows the positions and travels of the
various control surfaces.
5-3.
Troubleshooting.
Troubles peculiar to the Comanche control system are listed in Table V-II at the end of this section along
with their probable causes and suggested remedies. When troubleshooting, check electrically operated
controls from the power supply to the items affected.