Assembly Of Nose Gear Shock Strut - Beechcraft TRAVEL AIR 95 Shop Manual

q. Inflate
the strut
to
approximately
80
psi and
smear
Bushing (15)
O.
D. (minimum) O. 310
in.
the top
and sides of
the
collar
with soap suds
to
test
for
air leaks. Pin (10) O. D. (minimum)
0. 3725 in.
r.
When the
airplane is again on
the
ground with
the Pin (22) large
O. D. (minimum) 0. 3725 in.
weight of the
crafton the
strut, check
the
strut
in-
flation. There should be 2 inches of piston exposed,
with
Bushings
(9)
in line and
L
D. (maximum) 0. 3755 in.
the
airplane
empty
except for fuel.
Distance
between bushing
(9) faces
when in knee (maximum) 1. 505 in.
DISASSEMBLY OF NOSE GEAR SHOCK STRUT
(Airplanes Serial
TD-403
and after) Bearings (25 and 26) I. D. (maximum) 2. 252
in.
a.
Deflate strut and
remove
the
air valve assembly. Bearings (25 and 26) O. D. (minimum) 2. 378 in.
Bushings (27) in line and
L D. (maximum)
.
3755 in.
Do not unscrew
the
air
valve assembly
until
all
Distance between bushing (27)
faces
when
air pressure has been released or it may be in knee (maximum) 1. 505
in.
blown off with considerable
force and
cause
in-
jury
or damage. Barrel
(13) O. D. (minimum)
2. 247 in.
b.
Remove
the
snap
ring retaining
the
orifice
tube
assembly.
ASSEMBLY OF NOSE GEAR SHOCK STRUT
c.
Retract piston
to
push
the
orifice
tube
out of
the
(Airplane
Serial
TD-403
and after)
top
of
the
barrel. Remove
the
orifice
tube.
.
a.
Install the 'O" ring in
the
center
bearing
as shown
d. Invert
the
strut
and drain out
the
hydraulic
fluid.
in Figure 5-2, using
two
dowel rods
to
work it into posi-
tion.
Soak
the
lubricating felt pad in oil (SAE No. 10)
e. Disconnect
the torque
knees by removing
the
bolt
before
installation.
and
bushing. Slide
the
piston
and fork
assembly
out of
the
barrel. Remove
the
collar,
b. Install
the torque
knees using
the
Longer pin in
the
lower
torque
knee.
(CAUTION(
c. Slide
the
barrel
assembly
into
the
nose wheel brace.
Be sure
that
the air pressure
is released prior
d. Slip
the
collar
over
the
barrel and
measure
the
to
disconnecting
the
torque
knee. The
torque
amount of shim
necessary.
Remove the
colar, insert
knees provide
the
extension
stop for
the
lower
the
shim and reinstall
the
collar
and secure. Safety
the
shock absorber cylinder
assembly
and when dis-
bolts.
connected,
the
piston is free
to
slide out of
the
upper barrel
assembly.
NOTE
Peel shim layers as
necessary
for free operation
f. Remove
the
lower
snap ring,
adapter,
and
scraper. but
do
not
allow
more
than
.012
inch clearance
Remove
the
"O" ring from
the
center
bearing
and re-
between
the
strut collar and
the
nose gear brace
move
the
felt lubricating pad from inside
the
barrel.
assembly
bearing.
g.
Remove the
shimmy dampener
and pull
the
barrel
e.
Install
the
shimmy
dampener
using washers
between
out of
the
nose gear
brace assembly.
the
shimmy
dampener
and
the
brace as required
to
align
the
dampener
rod
end and
lug.
NOSE SHOCK STRUT WEAR
TOLERANCES
NOTE
(Airplane
Serial TD-403
and after)
When installing
the shimmy dampener
be sure
Listed below are manufacturing
tolerances
which
will
the
rod
end bolt is free
to
rotate,
aid in determining
the
extent of wear. Exactly how much
deviation from
these tolerances
which can be allowed
f.
Slide
the
snap
ring,
adapter and scraper over
the
must be determined
by
the
performance
of
the
strut.
top
of
the
piston.
Slide
the
piston
into the
barrel.
Work
the
scraper, adapter and snap ring
into
the
lower end of
Chrome plated portion
of absorber
the
barrel and connect
the torque
knees.
assembly
piston
(20)
O. D. (minimum) 1.7485
in.
g. Fill
the
strut
with 475 cc of MIL-H-5606
hydraulic
Upper
and
lower
brazed bearings in
fluid. If
no measuring
device is available collapse
the
the
barrel assembly L D. (maximum)
1. 752 in,
strut and fill it
to the
opening for
the
air
valve
assembly.
Bushing
(15) L
D.
(maximum) 0. 2505
in.
h.
Install
the
piston
ring
and "O" ring on the orifice
5-5