Landing Gear Safety System - Beechcraft TRAVEL AIR 95 Shop Manual

100951S063XP
washers between
the
spring
and
rod
r. Check
the
landing gear safety
switch for
proper
end. A
maximum
of five
washers
may be added.
If
adjustment. Measure 3/4 inch down on
the
piston
more
tension
is needed,
replace
the
spring.
from the
bottom of
the
left shock strut cylinder and
mark
the
piston
with a
piece of
tape.
Raise
the
left
NOTE
wheel with
a small jack, compressing the
shock
strut,
until
the tape
is
even
with
the
lower
edge
of
If unable
to
obtain
adequate
spring
tension,
the
cylinder.
Adjust
the
switch
actuating arm at
check
for
worn bushings in
the
retract
the clevis so
the
switch
is
actuated
as
the
tape
linkage.
Wear
in
the
bushings
has
the
effect touches the
end of
the
cylinder.
of lengthening
the entire linkage,
causing
the
rod
end spring
to
compress and stack,
s. Run gear up and check
landing gear position
leaving
nothing
for spring
adjustments. indicator. To
adjust
the
position
indicator,
remove
New bushings will
shorten
the
linkage,
the
indicator
cover and bend
the
actuating
wire
to
again permitting adjustment of
the
spring, move
the
flag
or
bend
the
tab
on
the
clamp to
in-
crease or decrease
the
flag
travel.
Set
the
covering
n. With
the
gears extended adjust
the
nose wheel so in place, retract
the
gear
and
check
the indicator
that
45
to
65
pounds is required
to
cause
any
de-
position with
the
gear retracted.
flection
at
the
knee
joint.
With nose wheel fully
retracted, a force
of 18
to
25 pounds applied
at
the
t
.
Recheck
limit switch
adjustment
and remove
center line of
the
axle
downward,
shall be
required
aircraft from
jacks.
to
pull
the
gear away
from
the
up stop. To adjust
the
nose
gear
tension the
aft retract rod
is
extended
or
shortened.
In
the
event correct
tensions
can not LANDING GEAR SAFETY SYSTEM (OPTIONAL)
be obtained,
100951DDO64SM washers may be added
at
the
forward
end
of
the
spring in
the
retract
rod The optional
landing
gear safety system functions
in
the
nose wheel well (maximum of
three
washers).
through the
action of
a solenoid
in
the
landing gear
position
switch
in
conjunction
with a
three-position
o.
Unscrew
main gear
outboard door
attaching link
safety
system switch,
a
relay
and diode mounted
to
assure
the
door is
not damaged
when retracted.
on
the
front spar,
two
pressure
switches
mounted
Connect
outboard door linkage and retract gear on
the
inboard
side
of
the
left main landing gear
slowly,
checking
to
see
that
clearance
is maintained wheel well,
and
a
microswitch
located
adjacent
to
between
the
door and
gear.
After
checking
to
see each
existing
throttle
position warning
switch.
that the
door is not
too tight,
run
gear
down and
adjust linkage as
required.
Continue
this
procedure
Each pressure switch is connected into
the
pitot and
until a snug,
firm
fit is obtained when
the
door
is
static system.
The pressure switch in
the
gear-up
completely
closed.
circuit is actuated by
the
pressure
differential that
exists between
the
pitot and
static
air
system
and
p. Connect main gear
inboard door linkage,
retract
will close with increasing pressure
at approximately
gear
slowly and check for
clearance between
door
70 mph. The pressure
switch
in
the gear-down
cir-
linkage and root rib. Run gear
to
3/4
down position cuit will
close
with decreasing pressure
at 120 mph,
and adjust
to
maintain 1/4 inch minimum
clearance
between
gear
and inboard door with
the
slack
re-
When
the
landing
gear position switch is in
the
UP
moved from
the
door linkage.
Continue
this
proce-
position
and an
airspeed
of 70 mph has been attained,
dure
until door will close
tightly
in
both
up
and
down
the
pressure
switch
in
the gear-up circuit
closes
position. Adjust doors by varying
the
length of
the
and actuates
a
relay mounted
on
the
front spar,
thus
push-pull
linkage rods. Disconnect
the
rods at
the
completing
the
circuit
and
retracting
the
landing
clevis fitting
to
make
this
adjustment.
gear. A diode
locks the
relay
in
the closed
position
until
the
retraction cycle is completed.
For
the
pre-
NOTE
ceding
to
occur however
one
microswitch
adjacent
to
the throttle
position
warning switch
must
also be in
Install
the
main
landing
gear
door
push rod the
open
position. This
microswitch is actuated
by
attaching
bolt in
the
door linkage
bracket
the throttle
control
when
the throttle
is advanced
with
the
head
to the
rear. If installed
wrong, sufficiently for
the
manifold pressure gage
to
reg-
the
bolt
may
catch
on
the
fuselage skin and
ister approximately
19
inches Hg. Conversely,
if
root rib of the
wing,
causing damage
to the
both
throttles
are
retarded
beyond
the
position
landing
gear retract mechanism
or
pre-
corresponding
to
approximately 17 inches
Hg of
venting
the
gear
from
retracting. manifold pressure,
the
microswitches
will close. If
at
the
same time
the
microswitches
close
the
air-
speed has
dropped below 120 mph,
the
resultant
q.
Connect nose
door
linkage
and rig nose door.
pressure differential between
the
pitot and
static
Check
closely
to
see
that
right hand aft
hinge clears
systems will actuate
the
pressure switch
in
the
the tire.
Adjust
the
nose
gear
doors by
varying
the
gear-down
circuit. With both microswitches and
length
of
the
push-pull
linkage rods in
the
nose
pressure
switches closed,
the
current flow
through
wheel well. With
the
gear
retracted,
the
doors
the
solenoid will cause
the
landing
gear position
should have a slight
tension
on
them
from
the actua-
switch
to
drop
into
the
DOWN position,
thus
com-
tor
rods
to
keep
the
doors from
vibrating.
pleting
the
gear-down
circuit.
3-18