Piper Cherokee Six - Page 157

PIPER CHEROKEE SIX SERVICE MANUAL
SECTION V
SURFACE CONTROLS
5-1. INTRODUCTION.
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-lb for
proper
installation
method.
5-2. DESCRIPTION.
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.
SURFACE CONTROLS
Revised:
9/18/78
1G13