Raytheon Beech Baron E55 - Page 311

Raytheon
Aircraft
Company
BARON
55
AND
58
SHOP
MANUAL
CAUTION:
Prior
to
jacking
the
airplane,
ensure
that
an
unbalanced
condition
does
not
exist.
Fuel should
be
distributed
evenly
in both
wings
to
prevent
an
unbalanced
condition which could
cause
the
airplane
to
be
unstable
while
on
jacks.
Whenever
the
landing
gear
mechanism
or
doors
are
removed
or
disconnected,
retract
the
gear
and check
the
rigging.
The
following
procedure
for
rigging
the
landing
gear
was
written
on
the
assumption
that the
entire
landing
gear
is
out
of
rig.
CAUTION:
Battery
voltage
is
not
sufficient
to
properly
cycle
the
landing
gear
during rigging.
A
28.25
0.25 vde
power
supply
should be utilired
for
landing
gear
rigging.
If
an
extemal
power
receptacle
is
not
available
on
the
airplane,
jumper
cables
may
be used between the
battery
and
power
supply.
Be
sure
of
the
polarity
before
making
the connection.
Excessive
operation
of
the
landing
gear
motor
without
proper
cooling
may
cause
damage
to
the
motor.
Allow
a
short
cooling
time
after
each
extension
and retraction
cycle.
CAUTION:
Over
tightening
the
nut
on
the bolt that
connects
the
drag leg
to
the
shock
strut
can
bind
the
strut
or
distort the
strut
attaching
points. Torque
the
nut
to
25
to
75
in.-lbs.
a.
Place
the
airplane
on
jacks
as
indicated
in
Section
2.
b.
Lengthen
the
main and
nose
gear
retract
rods
sufficiently
to
eliminate
the
danger
of
the
V brace
on
the
main
gear
damaging
the
skin
when
the
gear
is retracted and
to
prevent
excessive
tensions
on
the
nose
gear
retract
rods.
Damage
to
vital
parts
may
result
if
abnormal loads
are
applied
to
the
retract
system.
By
lengthening
the
retract
system.
By lengthening
the
retract
rod.
c.
Insert
the
retract
arm/retract
rod attach bolt
pointing
aft.
d.
Disconnect the
up
lock
cables
at
the
brackets,
leaving
the
springs
attached.
If
the
springs
are
disconnected,
upon
the retraction
of
the
gear
the
up
lock
arm
may
damage
the
top
wing
skin.
Place
the
up
lock
block
in
the
lower
position.
e.
Lengthenthe
nosegearretractrod.
f. Disconnect the
nose
wheel door
linkage
at
the
attaching
point
on
the door
and
remove
links
by
unscrewing
at
the
upper
ball
joint.
g.
Remove
bolts
attaching
the main
gear
outboard
door
links
to
main
strut.
Remove
inboard door
actuator
rod
by
unscrewing
from inboard rod
ends
and
removing
bolt
in
door
bracket.
h.
Screw
stop
bolts
in
(V
brace
assembly,
main
gear)
until
approximately
four
or
five threads
are
showing.
CAUTION:
When
running
the
gear
electrically
before
the
switches
are
reset,
or
for the first time
after
resetting
the
switches,
run
ii
with
extreme
caution
to
make
sure
the switches
open
the
electrical circuits
before
the
sector
gear
hits the
internal
stops
in the
gearbox.
The
sector
gear
should
not
be
touching
the
stop
when
the
motor
stops.
Serious
damage
may
result
if
the
internal
stops
are
hit
by
the
sector
gear.
When
checking
the
dynamic
brake
system,
actuate
one
of
the
limit
switches
and
the
motor
should
stop
immediately.
i.
Using
the
landing
gear
control
circuit
breaker
(placarded
LDG GR
POS)
as
a
momentary
switch,
run
the
gear
about
2/3
up.
Bump
the
gear
the
remaining
distance
to
the
limit
switch
by
the
momentary
operation
on
the
circuit
breaker.
Check
the
hand
crank
for
1/8 to
1/4
turn
(5/8
to
3/4
turn
on
airplanes using
new or
white
actuators)
between
the retracted
position
and the internal
stop
of
the
actuator.
E22
SECTION 5
Jun
30/04Page
t7