Raytheon Beech Baron E55 - Page 177

Raytheon
Aircraft
Company
BARON
55
AND
58
SHOP
MANUAL
WING FORWARD
SPAR
CARRY-THROUGH S~RUCTURE
REPAIR/INSPECTION
1
NOTE:
The
extent
of
repair/inspection
is
limited
to
cracking
in
the radius
of
the
web
flange
and
cracks
in
the
web
face around the
fasteners
in
the lower
front
spar
cap.
BEND
RADIUS
CRACK
The
following
procedure
should
be
performed
to
repairlinspect
cracks
in the bend radius
(Ref.
Figure
16).
1
CAUTION:
Caution
must
be used
during
the
stop drilling
operation.
Do
not
drill
into
the
spar
cap,
skin
or
any
other
structure.
A thin
stainless steel
sheet
may
be
used
to
prevent
damaging
adjacent
structure.
a.
A
crack
up
to
4.0
inches
in
length
must
be
stop-drilled
with
a
#30
drill bit
at
the
crack
ends.
The
area
must
be
repaired
per
the
applicable
kit listed in
Chart
6
within the
next
100
flight
hours
or
next
scheduled
inspection.
whichever
occurs
first.
b.
A
crack
exceeding
4.0 inches
in
length
must
be
repaired
PRIOR TO
FURTHER
FLIGHT
per
the
applicable
kit
listed in
Chart
6.
WEB
FACE
CRACK
The
following
procedure
should
be
performed
to
repair/inspect
cracks
in
the web face
around
the
huck-bolt fasteners
(Ref.
Figure
16):
CAUTION:
Do
not
stop
drill,
due
to
the
possibility
of
damaging
structure
behind
web
face.
a.
Any
crack
shall be
repaired
per
the
applicable
kit
listed
in
Chart
6
within
the
next
25
flight
hours
or
the
next
scheduled
inspection,
whichever
occurs
first.
b.
A
crack
passing
through
two
fasteners
and
extending beyond
for
less
than
0.5
inch
on
both
ends
shall
be
repaired
per
the
applicable
kit
listed in
Chart
6
within
the
next
25
flight
hours
or
the
next
scheduled
inspect~on,
whichever
occurs
first.
c.
A crack
passing
through
two
fasteners
and
extending beyond
for
mom
than
0.5
inch
on
either
end
shall
be
repaired
PRIOR
TO
FURTHER
FLIGHT
per
the
applicable
kit listed
in
Chart
6.
COMBINATION
BEND
RADIUS
AND
WEB FACE
CRACKS
a.
If cracks
are
found
in
both the
forward and aft frames
on
the
same
side
of the
airplane,
in
either
the web face
and/or
the
bend
radius,
and
any
of
the
cracks
are more
than
1.0
inch
long,
a
repair
shall
be made
PRIOR
TO
FURTHER
FLIGHT.
b.
If
cracks
are
found
in
both the
forward
and
aft frames
on
the
same
side
of
the
airplane,
in
either
the
web
face
and/or
the
bend
radius,
and
all
of
the
cracks
are
less than
1.0 inch
long,
a
repair
shall
be
made
per
the
applicable
kit
listed
in
Chart
6
within
the
next
25
flight
hours,
or
the
next
scheduled
inspection,
whichever
occurs
first.
c.
If
a
fuselage
skin crack
is discovered
around
the
opening
for the lower
forward
carry-through
fitting,
an
external
skin
doubler
may
be
required.
Contact
the
Technical
Support
Department
at
Raythean
Aircraft
Company
for
further
instructions.
d.
Install
the
carry-through
cover
and the
pilot’s
and
copilot’s
seats.
E23
SECTION 3
23