Raytheon Beech Baron E55 - Page 224

Raytheon
Aircraft
BEECH
BARON
55
AND
58
SHOP MANUAL
m.
With
the aileron control
system fully
rigged,
the
torque
required
to
move
the control
wheel
16"
right
and
left of
neutral
must not
be
over
15
inch-pounds.
IWAANINGI
WARNING
Check
the
ailerons for
correct
direction
of
movement.
When the control wheel
is
moved
to
the
left,
the
left
aileron
must
move
up
and the
right
aileron
must
move
down.
When
the
control wheel is moved
to
the
right,
the
right
aileron
must
move
up
and the left
aileron
must
move
down.
AILERON
TRIM
TAB RIGGING
NOTE
Beech
recommends
the
use
of
the aileron trim tab travel
gage
shown in the
GENERAL
INFORMATION section of this manual.
a.
Place
the
aileron
trim
tab
control in neutral.
b.
Remove
the
access
plate
to
the
trim tab
actuator.
c.
Place
the aileron
in neutral.
d.
Loosen
the cable and
remove
the
chain from
the trim tab
actuator
sprocket. By turning
the
sprocket,
move
the
trim
tab
actuator
to
both
extremes
of travel. Measure
both
settings
and
return
the
trim tab
actuator
to
the
midpoint
of
the
two
extremes
of
travel.
This
places
the
trim tab
actuator
in neutral.
e.
If
the
trim
tab
is
not
in
neutral,
adjust
the
length
of
the
tab
push-pull
rod
to
place
the
trim
tab
in
neutral.
f.
Center
the chain
on
the
sprocket
and
tighten
the
cable.
g.
Rig
the cable
tension
as
shown in
Figures
4-6 and
4-7.
h.
Adjust
the cable
stops
for
the
aileron
trim
tab to obtain
9"
to
11"
of surface
deflection
in each direction.
i.
Check
trim tab
travel.
Safety
wire
all turnbuckles
and
cable
stops.
NOTE
After
rigging
the
aileron
and aileron trim tab control
systems,
check
for
correct movement
of
the
control surfaces
with
respect
to
the controls. Since the aileron
trim
tab
is
a servo
tab,
the tab
moves
up
when the
aileron
moves
down. When the
trim
tab
control
is
moved
to
RIGHT
WING
UP,
the
tab
moves
down.
AILERON
TRIM
TAB
ACTUATOR
REMOVAL
a. Remove
the
access
plates
at
the
actuator.
b.
Loosen
the
cable and
remove
the chain from
the
actuator
sprocket.
c.
Disconnect
the
actuator
from
the trim tab
linkage.
d.
Remove
the bolts
attaching
the
actuator to
the
wing
structure.
Remove the
actuator.
4-16
E16