Piper PA-24 Comanche Service Manual page 136

PIPER COMANCHE SERVICE MANUAL
SECTlONV
SURFACE CONTJtOLS
~-l.
In1:l'Od1lcUoQ. This section
is
compriHd of iftformation for ranonl.
iDsallatiOD.
riain,
6I\d
adjustlftCftt of surface controls aDd their rdatcd compoDCDts tbrouahout the PA-24 series
&ircnh.
For the
mnoval
and inJtallation of srnacrura1 surfaces.
mer
to Section lV.
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~-2.
Dtlcripdoa. The
primary
flipt conaols of the PA-24 terics are of the
COllftlltioaal
type operated by
dual concrol wheels and dual sets of rudder
pedals. A syncm of
cales.
pulleys. bdlcraaks and push-pull
rods transfer the movement of the control whed and naddcr
ped.Ils to the
ai1croas,
stabiJator and Ndder.
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
sprodtm
to
synchronize the control wheels. An
additional chain and sprocket
is f&Xed on the left control cube which is coupled to the primary aileron
control cable. The cable
is
routed under the
floor ala.. the side
of the falClate to the main
spar
and out
through the wings to the beUcrank in each
winJ.
A one piece balance cable is also connected to the
belleranks. As the contrOl wheels arc moved. the concrol cables move the beUcrank. and actuate push-puU
rods to mOve the ailerons.
The stabilator concrol cables
arc
connected to the control wheel torque
aabcs. From
the connecting
points, cables arc routed around a series of puDcys under the floor and
aft to the tail section of the airplane.
The aft end of the cables connect to the stabilator ballDee arm which in rum
is
cODnected to the stabilator
torque tube.
Whm the contrOl wheel is moved forward or
alt, the cables move the balance arm up and down turning
the torque rube and stabi1&tor. •
The rudder is controlled by rudder pedals
installed
on both the pilot and copilot sides. Cables are
connected to both sides of the nadder pcd&l assembly and are roured aft
throu,h the bottom of the fusel"e
to the rudder horn. When one Ndder pedal is pushed, the cable
puUs
the nadder hom tumina the rudder.
The Ndder pedals also turn the nose wheel when in the down and locked position. Refer to Section VI
which covers Landing Gtar and Brake System.
The stabilator aim is opctated by an overhead crank in the cockpit and eenrrelled by cables e:uending
through the cabin ceiling to the cail section. As the crank is turned, the cable moves, which in tum rotates
;l
drum in the rail seerion. A push-puD rod is connected to an actUator
screw which in turn is moved by the
cable dt'\lm. The push-pull rod is aruched 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 concrol knob mounted below the instrument panel on the nose gear
wheel well cover and contrOlled by tubes and buftICC mechanism e:uendilll forward to the nose gear
steering arm.
The movable surfaces have adjustable stopS u well u adjustmena 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 .:ontrol
surfaces.
5-3. Troubjahooan,. Troubles peculiar to the Comanche control system are listed in Table
Y·n
a.t
the end
of this section along with their probable causes and sugated remedies. When troubleshooting. check
eleemeallv operated controls from the power supply to the items affected.
SURFACE CONTROLS
ISSUED: 8/18/72
1 F14
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