~-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. PIPER COMANCHE SERVICE MANUAL SECTlONV SURFACE CONTJtOLS ~-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 crankis 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. 1 F14 SURFACE CONTROLS ISSUED: 8/18/72