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nose rib to the
front spar.
4.
Remove
the
wing
and tail stands,
remove the
e.
Install screws attaching
the nose
skin
to the
front
airplane from
the
jack
and
test
flight
the airplane.
spar.
f.
Install screws
that attach
the
nose
rib at
station
b.
If
the preceding
steps do
not correct
the
wing
66.000 to the
front
spar.
heavy condition,
rig the
flap down on
the
heavy
wing
by
g.
Install
the three
screws
attaching
the
forward
screwing
the
actuator
out. Do
this only as a
last
resort,
section
of
the outboard
rib to the spar.
since
it
will
create
a
drag
on the airplane.
h.
Connect
the navigation
light
wire and
install
the
c.
At the first
scheduled
inspection
after the
wing
wing tip.
has been
adjusted,
check
for
correct
wing
bolt
torque.
i.
Install the screws
that attach
the wing
tip to the
Check
the
drain holes in
the upper wing attach
fittings
to
wing,
assure
that they are
not
obstructed.
j.
Connect
the electrical
wiring
to the landing light.
k.
Cement
the rubber
fillet
to
the root of the
wing,
MVING,
BOL T, NUT, AND
F/TT/NG
/NSPECTION
using
Minnesota Mining and Manufacturing Company EC
750 cement or other fuel-resistant
rubber
cement.
Read the
entire
section
before
removing
any wing
bolts.
1.
Install the fuel
cell.
m.
Install
the access
doors.
I
n.
At
the
first
scheduled
inspection
after
wing
WARNING
installation,
check
for
correct
wing
bolt torque. Check the
drain holes in the
upper wing attach
fittings to
assure
that
The wing
bolts
and nuts
installed in
all
Model
they are unobstructed.
95 twin Bonanza 5-years
old or older must
be
removed
and
inspected.
If the bolts and
nut
prove
to
be free of
all
damage, they
may
be
ADJUSTING
THE
WING
reinstalled
for an additional 5
year period.
At
the end
of this
period the
bolts
and nuts must
After reinstallation of a
wing,
or
repairs
to
it, flight tests
be inspected again. Ten
years after the
initial
may show
one
wing
is chronically heavy. If
so, alter the
inspection
all
wing
bolts
and
nuts
must
be
angle
of attack
of either
or
both
wings
to
correct
the
replaced
with
new
hardware.
Render
difference,
using
the following procedure:
unserviceable
all
components
removed
in
compliance
with this warning.
See Chart
I
for
a.
Raise
the trailing edge of
the
light
wing
to
the inspection
replacement
cycle
of
the
wing
decrease its lift or lower the trailing edge of the heavy
wing
attach
bolts.
(if both
wings
are full
up) to
increase its lift as follows:
1.
Using
a grease
pencil,
outline
the position
of
a.
Before
removing
any
wing attach
bolt, draw
an
the wing on the
fuselage.
outline of the
wing position
on
the fuselage
with
a grease
2. Place the airplane on a 3-point
jack
and
raise
pencil.
If
wing
bolt binding is
encountered
and the
wing
until
the
wheels
are clear. See Section 2 for
jacking
must be shifted,
the
outline
will
be helpful in
returning
the
instructions.
Place
a suitable
cradle
under
the
wing
being
wing
to its original
position.
adjusted
and a wing stand under the opposite
wing.
A
tail
stand will also
be
required
to assure stability.
CAUT/ON
3. Loosen the nuts on the lower
wing
attach
bolts and remove the bolts and nuts from the upper
wing
There
should
be
no wing
bolt binding during
attach fittings. Install new soft aluminum
washers
between
removal
or installation. Do not screw or drive
a
the upper
wing attach
fittings
and replace
the bolts and
bolt in or out of the fittings. If
wing
bolt
nuts. Raise or lower
the
trailing edge
as required
and
binding is encountered,
place
the airplane on
a
retorque
the
wing
attach nuts in the following order: upper
three point
jack
and raise the airplane
until the
forward, upper aft, lower forward and lower aft. There
wheels
are
clear (see Section 2 for
jacking
should
be no gap between the fittings after the last nut is
instructions). Place a suitable cradle under
each
torqued.
Torque
each nut to the value shown in the
wing
and a tail stand under the aft
portion
of
appropriate
illustration (Figure 4-1, 4-1A, 4-1B, and 4-IC).
the fuselage.
Defuel
the
wing,
loosen
the
Coat
the exposed threads that protrude through
the nuts
remaining 3 bolts and
reposition
the
wing until
with
MIL-C-16173
Grade
II corrosion preventive compound
the binding
bolt
moves
freely
through
the
(5, Chart 2).
fittings. Replace the soft aluminum
washers
between
the upper
wing
attach fittings
and
retorque
the bolts
as instructed
under
NOTE
INSTALLING
THE WING. If bolt binding is
not
encountered
and
the
wing
has
not shifted,
After torquing the upper
forward
wing attach
replacement
of the
soft
aluminum
washers
nut,
remove
the holding force from the wing
between the upper wing attach
fittings
is
not
cradle
then
torque
the
remaining
3 nuts.
required.
4-6B
C4
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