Raytheon Beech Baron E55 - Page 320

Ra~ytheon
AiKraft
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
and
wear.
Refer
to
Chart
1
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 (1),
check the small
O-ring
of
the
valve;
then
I
look for defects
in the valve
(Ref.
Figure
8).
c.
If the leak is from the
junction
ofthe barrel end
plug (4)
with the
cylinder
assembly
walls
(10),
check
the
O-ring
(5)
in the barrel
end
plug
(4).
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.
I
Smooth
minor
nicks,
burrs
and scratches.
Those
parts
that
are
scratched
or
have
worn
paint
may
be
stripped
and
repainted
with the
same
type
of
paint
as
that removed
or
to
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 the
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
component
by
more
than 10%. Refer
to
Chart
1
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.
MAIN
GEAR ASSEMBLY
NOTE:
Prior
to
assembly,
immerse all internal
parts
(except
felt
pad (14))
in
hydraulic
fluid
(13,
Consumable
I
Materials
Chart,
Section
2)
(Ref. Figure 8).
a.
Install
the
O-ring
(13)
in
the
upper
brazed
bearing (12)
of
the
cylinder
assembly
(10).
Two
dowel rods
may
be
used
to
work
O-ring (13)
into
position
(Ref.
Figure
8
and
10).
Jun
30/04Page
26
SECTION
5
E22