Raytheon Beech Baron E55 - Page 175

Raytheon
Aircraft
Company
BARON
55
AND
58
SHOP
MANUAL
c.
Perform
a
visual
inspection
of
the
cleaned
areas
for
evidence
of
cracks.
d.
Perform
a
fluorescent
or
dye
penetrant
inspection
of
the
cleaned
area
per
MIL-STD-6866
and
inspect
for
evidence
of cracks.
e.
If
cracks
are discovered,
determine the crack size
and method
of
repair
as
outlined
in
the
WING
FORWARD
SPAR
CARRY-THROUGH
STRUCTURE
REPAIR/INSPECTION
procedure.
f.
If
no
cracks
are
noted,
install
the
carry-through
cover
and
the
pilot’s
and
copilot’s
seats.
WING FORWARD
SPAR CARRY-THROUGH
STRUCTURE
INSPECTION
WITH
REPAIR
KIT
NOTE:
The
areas
identified
in
Figure
16
should
be
inspected
for
cracking
at
the
intervals
specified
for
repa~red
i
structure
by
Chart
5
using
the
following
inspection procedure:
a.
Remove
the
pilot’s
and
copilot’s
seats
and the
carry-through
cover
to
obtain
access
to
the
front
spar
carry-through
structure.
b.
Thoroughly
clean
the forward and
aft
frames
(webs
and
reinforcing
doubler)
of
the
front
spar
carry-through
structure
in the
areas
shown in
Figure
16
with
solvent
(18,
Consumable
Materials
Chart,
Section
2).
c.
Perform
a
visual
inspection
of the
cleaned
areas
for
evidence
of
cracks.
d.
Perform
a
fluorescent
or
dye
penetrant
inspection
of
the
cleaned
area
per
Mit-STD-6866
and
inspect
for
evidence
of
cracks.
e.
If
cracks
are
discovered
in the doubler
or
the
existing
web
face,
the
crack has
progressed
beyond
the douMer
profile;
contact
the Technical
Support Department
at
Raytheon
Aircraft
Company
for further
instructions.
f.
If
no
cracks
are
noted,
install the
carry-through
cover
and
the
pilot’s
and
copilot’s
seats.
Ena
SECTION
3
27