Piper Cherokee LANCE, Руководство по обслуживанию

Страница: 145 / 854

PIPER CHEROKEE SIX / LANCE SERVICE MANUAL
03/27/08 V - SURFACE CONTROLS
1G13
SECTION V
SURFACE CONTROLS
5-1. DESCRIPTION AND OPERATION.
The Cherokee Six is controlled in flight by the use of three standard primary control surfaces, consisting
of ailerons, stabilator and rudder. Operation of these controls is through the movement of the control
column-tee bar assembly and rudder pedals. On the forward end of each control column is a sprocket
assembly. A chain is wrapped around the sprockets to connect the right and left controls and then back to
idler sprockets on the column’s tee bar, which in turn connect to the aileron primary control cables. The
cables operate the aileron bellcrank and push-pull rods. The stabilator is controlled by a cable connected
to the bottom of the tee bar assembly and at the balance arm of the stabilator. Cables also connect the
rudder pedals with the rudder horn.
Provisions for directional and longitudinal trim control is provided by an adjustable trim mechanism for
the stabilator and rudder. The stabilator trim is controlled by a wheel and drum mounted on the floor
tunnel between the front seats. Cables routed aft from the drum to the tail cone operate a screw assembly
which in turn moves the stabilator trim tab. The rudder trim is controlled by a knob and screw assembly
attached to the rudder pedal assembly.
The wing flap system consists of an operating handle, a cable routed from the handle to a torque tube
and push-pull rods. Through the push-pull rods and torque tube, the flaps are interconnecting and can be
positioned in three locations of 10, 25 and 40 degrees.
5-2. STANDARD PRACTICES AND PROCEDURES.
This section explains the removal, installation, and rigging and adjustment procedures for the control
assemblies of the various structural surfaces. For the removal and installation of the structural surfaces of
the airplane, refer to Section IV. The assemblies need not be removed in order of paragraph since each
paragraph describes the individual removal and installation of the various assemblies.
The following tips may be helpful in the removal and installation of the various assemblies:
a. It is recommended, though not always necessary, to level and place the airplane on jacks during
rigging and adjustment, especially when using a bubble protractor or level.
b. Remove the turnbuckle barrels from cable ends before withdrawing the cable through the structures.
c. Tie a cord to the cable end before drawing cable through structures to facilitate reinstallation of
cable.
d. When turnbuckles have been set to correct tension, no more than three threads should be exposed
from either end of the turnbuckle barrel.
e. When push rods or rod ends are provided with an inspection hole, the screw shall be screwed in
sufficiently far to pass the hole. This can be determined visually or by feel, inserting a piece of wire
into the inspection hole. Where no inspection hole is provided, there shall be a minimum of 3/8 inch
thread engagement.
f. When installing rod end jam nuts, refer to Figure 5-1b for proper installation method.
g. Cable tensions should be taken with the appropriate control surface in its neutral position.
NOTE: Cable rigging tensions specified must be corrected to ambient temperature in the area
where the tension is being checked, using Table V-I.