Piper COMANCHE PA-24-180 Service Manual page 134

SECTION V
SURFACE CONTROLS
S-1. Inroduction
Thi section i comprised of informaion
for removnl insmulation rigging and
adjustment of surface controls and their related component throughout the PA-24 series urcrf. For the
removal nd inmllion
of rucnurl
urfces refer to Section IV.
5-2. Dcripdon.
The primary fligbh controls of the PA-24 eries re of the conventional type operated by
dual control wheels and dual sea of rudder pedal. A sytemn of cables, pulleys, beilcrnks and pus-pull
rods ransfer the movement of the control wheel and rudder pedals to the ailerons, suabilaor and rudder.
The aileron controls const of two control wheels connected by torque tubes to sprockets on each end
of the square rub.
A chain is wrapped aound 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 balane 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 subilator control cables are connected to the control wheel torque ubes. 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 cbles connect to the subilator balance arm which in turn is connected to the stabiltor
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 stabilaror.
The rudder is controlled by rudder pedals installed on both the pilot and copilot sides. Cbles are
connected to both sides of the rudder pedl assembly and are outed aft through the bottom of the fuselage
to the rudder horn. When one rudder pedal is pushed, the cable pulls the rudder horn uroing the rudder.
The rudder pedals also urn the nose wheel when in the down and locked position. Refer to Secton VI
which covers Landing Gear and Brake System.
The subilator trim is operated by an overhead crank in the cockpit and conrolled by cabies extending
through the cabin ceiling to the ail secton. As the crank is turned, the cable moves, which in turn rotates a
drum in the ail section. A push-pull rod is connected to an actuator screw which in rum 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 cab.
The rudder trim is operated by a control knob mounted below the instrument panel on the nose gear
wheel well cover and controlled by cubes 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-l shows the positions and travels of the various control
surfaces.
5-3. Troubleshooting. Troubles peculir to the Comanche control system are listed in Table V-ll at the end
of this section along with their probable causes and suggested remedies. When troubleshooting, check
electncally operated controls from the power supply to the items affected.
SURFACE CONTROLS
ISSUED: 8/18/72
1 F14
PIPER COMANCHE SERVICE MANUAL