Wing Bolt And Nut Inspection And Replacement - Beechcraft TRAVEL AIR 95 Shop Manual

5
YEARS 5
YEARS
5
YEARS
5
YEARS
NEW
INITIAL
SECOND FIRST REPLACEMENT
REPEAT INSPECTION
AIRPLANE
INSPECTION
INSPECTION INTERVAL
AND REPLACEMENT
CYCLE
5
YEARS
5
YEARS
5
YEAAS
AIRPLANES
SECOND
FIRST REPLACEMENT
REPEAT INSPECTION
5 YEARS OLD INSPECTION INTERVAL
AND
REPLACEMENT
CYCLE
OR
OLDER
INITIAL
INSPECTION
35-31-36
NOTE
NOTE
The first inspection for airplanes five years
old
At each replacement
interval,
all wing attach
or older
must
be performed at
the
first
hardware (bolts, washers, and nuts) must be
scheduled
inspection
following
the
issue
date
replaced.
of
revision
C4.
35-31-37
Wing Bolt And Nut inspection And Replacement
Cycle
Chart
1
NOT E CAUTION
Beech Aircraft
Corporation
supplies wing
Assure that
the
95-110025-1 (shown
in
Figure
attach
hardware (bolts and
nuts) that
have been
4-1
and
4-1C), the
95-110025-3
(shown in
given an additional magnetic
particle
inspection
Figure 4-1A),
and the
50-105011
(shown
in
since manufacture.
These
components may
be
Figure 4-1B) washers
have
a full complete
identified by
the green
dye
on the
head
of the
radius
with no sharp edges that
could mark
the
bolt
and on some portion of the nut.
fittings. Replace any
washers that have an
incomplete
radius
or sharp
edges.
WARNING
d. If the
bolts
and nuts do not exceed the
life limit
shown
in
Chart
1,
visually inspect each bolt and nut with a
Use
only the components specified
in
the
10-power or stronger magnifying glass; inspect
for
applicable
illustrations. DO NOT INSTALL corrosion,
cracks and
mechanical damage. The cadmium
THE BLACK P/N H-20 NUTS,
these
nuts plating may display
areas that appear
rubbed, discolored or
have been dry film lubricated
with
molybdenum
polished. These
areas are
usually
the
result
of
prevailing
disulfide. When
MIL-C-16173
Grade II
installation procedures and are of
no
significance.
A bolt
corrosion preventive compound is
added to
should
not be rejected because of cadmium plating
these
nuts,
the
additional
lubrication
may cause
deterioration; however,
any component
that is cracked,
improper preload in
the
bolt
when
it is
torqued
corroded
or
has mechanical damage must be replaced.
to the wet torque values
specified in Figures
4-
e.
Using
the
magnetic particle inspection process
1, 4-lA, 4-lB, and 4-lC.
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
b. Starting at the lower
wing attach
point
on each
(corrosion, cracks, and mechanical damage),
they
may be
side,
remove,
inspect, and retorque one bolt at a time until reused after demagnetization
and cleaning.
the complete set of eight bolts and nuts have been f.
Clean
the spar
fitting bolt bores with naphtha or
inspected. methyl ketone (1 or
2,
Chart 2). Do not
strip the
epoxy
paint
c.
Using a
nonmetallic brush, thoroughly
clean the
from
this area.
Inspect
the surface conditionof each
fitting;
bolt, washers, and
nut
with naphtha
or
methyl ethyl
ketone focus
special attention on the
washer
seat and
bolt bore
(1 or 2,
Chart
2).
area.
If
scoring,
corrosion pitting,
or washer impressions are
C4
4-6C