Piper Cherokee Six - Page 139

PIPER CHEROKEE SIX SERVICE MANUAL
4-27.
AILERON
BALANCE
WEIGHT
MODIFICATION.
(PA-32-260,
Serial
Nos.
32-1 to
32-1118 incl;
PA-32-300
-300S,
Serial Nos.
32-40000
to 32-40619
incl. )
To facilitate
the use
of new aileron
balance
weight assembly
(P/N
66766-00)
on
above stated
airplanes,
it will
be necessary
to modify
the balance
weight cutout
in the
wing
rib. (Refer
to Figure
4-11.)
The
hole pattern
in
the new
balance
weight
bracket is
the same
as the
old bracket
with
the exception
of two
holes.
When
replacing
the old
bracket with
the new
one, it is
permissible
to use the
new bracket
as a hole
template
to drill the
two new
holes at their
proper location.
To install the
balance weight
assembly, the
following procedure
may be used:
a.
Remove
the aileron
per paragraph
4-6.
b.
Remove
the old balance
weight
by drilling
out the rivets
from
around the
perimeter
of the bracket.
c. Modify
the wing
end rib
balance
arm hole
as shown
in Figure
4-11.
d.
Using the
new bracket
as a template,
drill
the two
new holes
in the rib.
(Refer to
Figure 4-12.)
e.
Place six cherry
lock
rivets, CR22494-2,
in the holes
within the
bracket
and set the rivets.
f. Replace the
six rivets around the perimeter
of the bracket with MS20470
AD3-3, and set.
g.
Prior to installation,
paint
metal parts
where necessary.
h. Install
the aileron per
paragraph 4-6.
4-28. FLAP INSPECTION
AND
MODIFICATION.
(Refer to Figure
4-13.) Inspect
the aft flap
attaching point for security. If it
is found secure, no modification
is
required.
If the clevis bolt
appears to be working
loose from
the anchor nut,
the
attachment
point should
be modified in accordancewith
the
following instructions.
a.
Remove the clevis
bolt and related
parts from
the inboard
flap hinge
attaching point.
b.
The skin
on the flap
must be
modified
in accordance
with Figure
4-13.
c. Remove the existing
anchor nuts from the inboard
flap hinge.
d. Install a
new clevis bolt
and related parts
and secure with
castellated nuts
and cotter pins.
4-29.
STABILATOR DRAIN HOLES. In
order to prevent the accumulation of water
or ice
in the
stabilator when the aircraft is parked,
it is recommended that drain holes
be added in
accordance
with Figure
4-14.
Revised:
7/29/77
STRUCTURE
1F19