Raytheon Beech Baron E55 - Page 168

nircraft
Company
BARON
55
AND
58
SHOP
MANUAL
b.
Starting
at
the lower forward
wing
attach
point
on
each
side,
remove,
inspect,
and
replace
one
bolt and
nut set
at
a
time until
the
complete
set
of
eight
bolts and
nuts
have been
inspected.
c.
Using
a
nonmetallic
brush,
thoroughly
clean the
bolt
washers
and
nut
with solvent
(18
or
19,
Consumable
Materials
Chart,
Section
2).
I
CAUTION:
Assure that
the
50-105011,
95-110025-1 and
95110025-3 washers shown
in
Figures
3
9 10
and
11
have
a
full
complete
radius with
no
sharp edges
which
could
mark the
fittings.
Replace
the washer
if
it
has
an
incomplete
radius
or
sharp
edges.
d.
If
the
bolts
and
nuts
do
not
exceed
the life
limit
shown
in
Figure
12,
visually inspect
each
bolt
and
nut
with
a
10-power
or
stronger
magnifying
glass;
inspect
for
corrosion, cracks,
and mechanical
damage.
The
cadmium
plating
may
display
areas
that
appear
rubbed,
discolored
or
polished.
These
areas are
usually
the
result of
prevailing
installation
procedures
and
are
of
no
significance.
A bolt
should
not
be
rejected
because of
cadmium
plating
deterioration; however,
any
com
ponent
(bolt,
washer
or
nut)
that is
cracked,
corroded
or
has
mechanical
damage
must
be
replaced.
e.
Using
the
magnetic
particle inspection
process
described
in
this
chapter,
check
each
bolt for
circumferential
crack
indications
and each
nut
for
longitudinal
crack
indications.
If
the bolt and
nut
prove
to
be
free
of
all
damage
(corrosion,
cracks,
crack
indications,
and
mechanical
damage),
they
may
be reused after
demagnetization
and
cleaning.
f.
Clean
the
spar
fitting
bolt
bores with solvent
(18
or
19,
Consumable
Materials
Chart,
Section
2).
Do
not
strip
the
epoxy
paint
from this
area.
Inspect
the
surface condition of
each
fitting;
focus
special
attention
on
the washer
seat
and bolt bore
area.
If
scoring,
corrosion
pitting,
or
washer
impressions
are
discovered
in this
area,
contact
the
Technical
Support
Department
of
Raytheon
Aircraft
Company.
If
the
fitting
is
satisfactory,
coat
the
bolt
bore
and
bearing
faces
of
the
fitting
with
coating (54,
Consumable
Materials
Chart,
Section
2).
Allow
the
coating
to
I
remain
on
the
surface
for
approximately
5
minutes. When
the five
minutes have
elapsed,
wash the
coated
areas
with
water
and blow
dry (do
not
wipe dry).
Paint the
treated
areas
with zinc
chromate
primer (24,
Consumable
Materials
Chart,
Section
2).
g.
Coat the
bearing
faces
and bolt
bores
of the
fittings,
the
complete
bolt,
washers and
nut
with
corrosion
preventive
compound (49,
Consumable
Materials
Chart,
Section
2).
h.
Install
the
bolt,
washer
or
washers,
and
nut
into the
wing fittings.
CAUTION:
Ensure that the
wing
bolt wrenches do
not
bottom
out
on
the
wing
fittings.
This could
cause erroneous
torque
readings
and
damage
to
the
fittings.
I
i.
Torque
the
nut to
the
wet
torque
value
shown
in the
appropriate
illustration
(Ref.
Figures
8,
9,
10
and
1
1).
When
a
torque
wrench
adapter
is
used,
the
length
of
the
adapter
must
be added
to
the
length
of
the
torque
wrench
and
the
proper
torque
value
computed
as
detailed
in
Section
1.
j.
Coat
the
exposed
threads
that
protrude
through
the
nut
with
corrosion
preventive
compound (49,
Consumable
Materials
Chart,
Section
2).
k.
Check
that the decal
is
affixed
to
the
appropriate
locations
on
the
airplane (Ref.
Figure
13).
i. At the
first
scheduled
inspection
after the
wing
bolts
have been
loosened and
torqued
or
after
initial
installation,
check
each bolt for
proper
torque.
m.
Check
the
drain
ports
in the
upper
wing
attach
fittings
to
ensure
that
they
are
unobstructed.
Page
SECTION
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