Raytheon Beech Baron E55 - Landing Gear System

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Aircraft
Company
BARON
55
AND
58
SHOP
MANUAL
LANDING
GEAR
SYSTEM
CAUTION:
Under
no
circumstance should the
landing
gear
be
operated electrically
while
the hand
crank is
engaged.
In the
event
of such
an
operation,
a
tear
down and
magnetic
inspection
should
be
performed
for
damage
to
engagement
slot in
worm
gear
(Ref.
to
Figure
15,
Item
19).
1
LANDING GEAR SAFETY
SYSTEM
(OPTIONAL)
The
optional landing
gear
safety
system
functions
through
the action
of
a
solenoid
in the
landing
gear
position
switch
in
conjunction
with
a
three
position
safety
system
switch,
a
relay
and diode mounted
on
the
front
spar,
two
pressure
switches mounted
on
the inboard side of the left main
landing
gear
wheel well and
a
microswitch
located
adjacent
to
each
existing
throttle
position
warning
switch
(Ref.
Figure
5).
Each
pressure
switch is connected
into the
pitot
and static
system.
The
pressure
switch
in
the
gear
up
circuit
is
actuated
by
the
pressure
differential
that exists between
the
pitot
and
static
air
system
and
will
close
with
increasing
pressure
at
approximately
70
mph.
The
pressure
switch
in
the
gear
down circuit
will
close
with
decreasing
pressure
at
120
mph.
When the
landing
gear
position
switch is in the
UP
position
and
an
airspeed
of
70
mph
has been
attained,
the
pressure
switch
in the
gear
up
circuit
closes and
actuates
a
relay
mounted
on
the front
spar,
thus
completing
the
circuit and
retracting
the
landing
gear.
A
diode
locks the
relay
in
the closed
position
until
the
retraction
cycle
is
completed.
For the
preceding
to
occur
however
one
microswitch
adjacent
to
the throttle
position
waming
switch
must
also
be in the
open
position.
This
microswitch is actuated
by
the throttle control when the throttle
is advanced
sufficiently
for the manifold
pressure
gage
to
register
approximately
19
in.
Hg.
Conversely,
if
both
throttles
are
retarded
beyond
the
position corresponding
to
approximately
17
in.
Hg
of manifold
pressure,
the microswitches
will
close.
If
at
the
same
time the microswitches close
the
airspeed
has
dropped
below
120
mph,
the
resultant
pressure
differential
between the
pitot
and static
systems
will
actuate
the
pressure
switch in the
gear
down
circuit.
With
both
microswitches
and
pressure
switches
closed,
the
current
flow
through
the solenoid
will
cause
the
landing
gear
position
switch
to
drop
into the
DOWN
position,
thus
completing
the
gear
down circuit.
If the
landing
gear
position
switch is
placed
in the UP
position
while
the
landing
gear
safety
system
switch
is
in
the
ON
position,
the
landing
gear
will
retract
only
when the
following
conditions
are
mutually
fulfilled.
a.
The
airplane
must
have
attained
an
airspeed
of
at
least 70
mph.
b.
One throttle
setting
must
have been advanced
sufficiently
to
have
produced
a
manifold
pressure
of
approximately
19 in.
Hg.
By
the
same
token,
the
landing
gear
will
automatically
extend
under
the
following
conditions:
a.
The
airspeed
must
have
dropped
below
120
mph.
b.
Both throttles
must
have
been retarded
enough
for
manifold
pressure
to
have
dropped
below
approximately
17
in.
Hg.
The
safety
system
switch is
a
three
position
switch,
with
normally
ON
and
OFF
positions.
The switch
also
contains
a
momentary
or
test
position
for
checking
that the
system
is
functioning properly.
When
released
from
the
test
position,
the
switch
returns to
the
ON
position.
E22
SECTION
5Pagell