Raytheon Beech Baron E55 - Page 328

Rll~heOll
Aircraft
Company
BARON
55
AND
58
SHOP
MANUAL
I
REPAIRS
a.
Visually inspect
castings
for cracks and
pitting;
and
finished
surfaces
for
scoring,
pitting,
nicks,
cracks,
distortion
I
and
wear.
Refer
to
Chart
2
for
tolerances
to
aid
in
determining
the
extent
of
wear.
Replace
all defective
and
excessively
worn
parts.
b.
If
fluid leaks
have been
observed
on
top
of the
air
valve
assembly
(3),
check the
small
O-ring
~4)
of
the
valve;
I
then
look
for defects
in the valve
(Ref. Figure
9).
c.
If
the
leak
is
from
the
junction
of
the
orifice tube
assembly
(6)
with
the
cylinder
assembly
(9)
walls,
check
the
0-
ring
(7)
in the
orifice tube
(6).
d. All
parts
or
assemblies
may
be
repaired
if
any
of
the
following problems
exist:
Slight
scoring
of shafts
may
be
corrected
by
lapping
carefully
with
a
flat oil
stone.
NOTE: Do
not
exceed 10%
of the
component
material thickness when
removing
nicks,
burrs
and scratches.
Smooth
minor
nicks,
burrs
and scratches.
Those
parts
that
are
scratched
or
have
worn
plating
may
be
stripped
and
replated
with the
same
type
of
plating
as
that
removed
or
be
replaced
with
new
parts.
Minor
thread
damage,
chase
to
clean
or
smooth.
NOTE:
Corrosion
damage
requires inspection
to
determine
the
depth
of
penetration
and
cross-sectional
area
change.
The
damaged
area
must
be
thoroughly
cleaned and the
corrosion
must
be removed.
The
deterioration
caused
by
corrosion
or
removal
of corrosion
must not
reduce
the material thickness
of
any
I
component
by
more
than
10%.
Refer
to
Chart
2
for
MAIN
LANDING
GEAR
WEAR
TOLERANCES
AND
INSPECTION
PROCEDURES
on
components.
For
additional
information
contact
the
Technical
Support
Department
of
Raytheon
Aircraft
Company,
P.O. Box
85,
Wichita,
KS
67201.
I
Remove corrosion
if
applicable
and
apply
corrosion
prevention
materials
as
necessary
per
MIL-C-5541
or
cadmium
plate
per
Fed
QQ-P-416,
Type
II.
Bushings
that
check within allowable
wear
tolerances
may
be
reused.
When evidence
of
damage
exists
to
steel
parts,
magnetic
particle
inspect
per
MIL-STD-1949.
NOTE:
Do
not
remove
paint
or
primer
from
the
area
to
be
fluorescent
or
dye
penetrant
inspected
per
MIL-STD-
6866.
If
the
finish absorbs the
penetrant
so
that bleed
out
prevents
satisfactory
inspection
or
if
a
new
finish
has
not
cured
for
at
least
30
days,
contact
the
Technical
Support
Department
of
Raytheon
Aircraft
Company,
P.O.
Box
85,
Wichita,
KS
67201.
When evidence
of
damage
exists
to
metal
parts
other than
steel,
fluorescent
penetrant
inspect
per
MIL-STD-
6866,
Type
i.
Replace damaged
or
unserviceable
parts
with
new or
serviceable
parts.
Jun
30104Page
34
SECTION
5