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NOTE
between
the
fittings.
This gap must not exceed
a width
of
.060
inch. When
the
nut is
torqued
to
Discard
the soft
aluminum
washers
installed
the
wet
torque
value shown
in Figure 4-lC,
no
between the
upper
wing
attach
fittings. Install
gap
should
exist
between
the
fittings.
new
washers
when
the
wing
is reinstalled.
f.
Torque
the nuts
in
the
following
order:
Upper
/NSTALLING THE kVING
forward,
upper aft,
Iower forward,
and lower aft. When a
torque
wrench
adapter
is used,
the
length
of the adapter
a.
Using
a nonmetallic
brush
and naphtha
or methyl
must
be
added
to the length of
the torque
wrench
and
the
ethyl
ketone
(I
or 2, Chart 2), clean the
wing
attach
fittings
proper torque value computed
as
detailed in Section 4, Coat
and
hardware
(bolts,
washers,
and nuts),
Inspect
the
wing
the bolt
threads
that protrude
through
the nut
with
MIL-C-
attach
fittings
and
hardware as instructed
under
WING
16173 Grade Il
corrosion
preventive
compound
(5,
Chart 2).
BOLT. NUT, AND FITTING INSPECTION.
CAUT/ON
WARNING
When
torquing
the wing
bolts
assure
that
the
Wing
bolts
that
have
reached
their
life limit (10
wing
bolt
wrenches
do
not
bottom
out
on
the
years after the
initial inspection),
must not
be
wing attach
fittings. Such
an occurrence
could
reused.
cause
false
torque
readings
and
damage
the
fittings.
After torquing
the upper
forward
wing
attach bolt,
remove
the holding force from
the
b.
Coat the fitting bolt bores
and
bearing faces,
wing cradle
prior
to torquing
the remaining
3
bolts,
washers,
and
nuts
with
MIL-C-16173 Grade II
bolts.
corrosion
preventive
compound (5, Chart 2).
g.
Reinstall
the
engine
and connect
engine controls.
CAUT/ON
h.
Connect
all
electrical
wiring
to
the
engine,
nacelle
terminal,
and
the
electrical
components located in
each side
Each bolt
must
be inserted by hand
without
of the
upper
nacelle.
binding. If
a
bolt
cannot
be easily inserted,
i.
Connect the
plumbing
between
the wing root rib
reposition
the wing
until
the
bolt moves freely
and the
fuselage.
in the fittings. Do
not
screw or drive
the
bolt
j.
Connect the flap
wire
bundle
and plumbing
in
the
into the fittings.
aft wheel well.
k.
Replace all
clamps
securing
wiring
bundle
and
engine
controls
to the leading
edge.
c.
Guide
the
flap
shaft
and
retract
rod
into
their
1.
Reinstall the lower
aft nacelle,
wing
leading
edge
respective
positions
and
secure
them. Align
the wing
and
cover and nacelle
fillets.
fuselage fittings
and
insert
the wing
bolts into
the attach
fittings.
INSTALLING THE W/NG
PANEL LEADING EDGE
CAUTION
a.
Support the
aft section
of
the
wing panel
and
align
the leading
edge
hinges.
Bolts,
washers,
and nuts
must
be
oriented
as
b.
Insert a
new
hinge
wire
into the
attaching
hinge,
shown
in the applicable figure for
each
location
as
far as it
will go
by hand.
(Figure 4-1, 4-lA, 4-lB,
and
4-lC).
c.
Drive
the
hinge
wire
using
a telescoping
guide
tube
and
rivet
gun.
As
the wire
is driven in,
remove
sections
of the telescoping
guide.
d.
Start the nuts on
the upper
forward and aft bolts.
Rotate the
wing
trailing edge
until
alignment
with
the
outline drawn on the fuselage is
realized.
After
rotation
is
NOTE
established,
verify
that
the
lower forward bolt is
not
binding in the bolt bore. If bold binding is encountered,
The guide is
made up
of the following
tubes:
adjust
the
wing until the
bolt moves freely.
3/16 x 0.049
steel tubing,
60 inches, 32 inches,
e.
Tighten
the upper
forward and aft nuts.
17 inches, 9 inches, 5 inches
and
2-1/2 inches
long; 1/4
x
0.028
steel
tubing
60
inches, 32
inches, 17 inches, 9 inches, 5 inches and 2-1/2
CAUTION
inches..
Before the
nut
at the lower aft
wing attach
point is torqued, a slight gap may be
noted
d.
Install the machine screws that attach the root
C4
AAA
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