Raytheon Beech Baron E55 - Flight Controls

Raytheon
Aircraft
BEECH BARON
55
AND
58
SHOP
MANUAL
FLIGHT
CONTROLS
AND
SURFACES
CONTROL
SURFACES
IWARHING
i
WARNING
On
airplane
serials
TH-1389,
TH-1396 and after
and earlier
airplanes
with
new
spare
replace-
ment
parts,
observe the color
coding.
On
these
airplanes
the control
cables
bellcrank
and
other
components
are
color
coded. Do
not
connect
coded
parts
of
one
color
to
coded
parts
of
a
different
color. Ensure
that the
primary
and
secondary
controls
are
operating
in
the
proper
direction.
NOTE
On all
control
column
systems
and control
surface
systems,
the inside surface of
all
turnbuckles
must be
coated
with
grease
(11,
Consumable
Materials
Chart,
Section
2).
All
primary
flight
controls
are
conventional
cable-operated
surfaces,
and
are
manually
controlled
through
cable-
bellcrank
systems.
Each
system
includes
surface travel
stops
and
linkage adjustments.
The
optional
electric
eleva-
tor
trim and
wing flaps
are
driven
by
electric
motors.
The
ailerons,
elevators
and rudder
can
be
secured
with control locks
(gust
locks)
in the
pilot’s
compartment.
Refer
to
the GROUND
HANDLING
AND
SERVICING
section
of
this
manual
for
control lock
installation
procedures.
Airplane
serials
TC-1
and
after,
TE-1
and
after,
TH-I
through
TH-1388 and
TH-1390
through
TH-1395
are
equipped
with
either
a
standard
single
throw-over
control
arm,
or a
dual control
T
column.
On
TH-1389
and
TH-1396 and
after,
dual controls
are
installed
as
standard
equipment.
The
rudder
pedals
are
interconnected
by linkage
below the
floor. The
pedals
are
adjustable
to
two
positions by
pressing
a
spring-loaded
lever
on
the
side of the
pedal.
If brakes
are
not
installed
on
the
copilot’s
pedals,
the
same
lever
can
be
used
to
place
the
copilot’s
pedals
against
the
floor.
The
wing
flaps
are
operated by
an
electric
motor-driven
gearbox
on
the
forward
side
of
the
rear
spar
at
the
centerline
of
the
airplane.
The
gearbox
drives
two
flexible
drive
shafts,
each connected
to
an
acme-thread-type
jackscrew
at
the
flap.
The
flaps
are
controlled
by
a
lever
(switch)
on
the
instrument
subpanel.
The
lever
must
be
pulled
out
of
a
detent
to
change
positions.
The
flap
position
transmitter,
if
installed,
is located
near
the
left
flap
actuator.
On
airplanes
with
the
single
throw-over
control
or
the T
control,
the
flap position
is
indicated
by
an
instrument
to
the left of the
flap
control
lever.
On TH-
f
389
and
TH-1396 and
after,
the
flap position
is
indicated
by
three
lights
to
the left of the
flap
control
lever.
The
lights
indicate
down,
approach
and in-transit
positions.
All
lights
are
out
when
the
flaps
are
up.
Trim
tabs
are
installed
on
each
elevator,
the rudder and
the
left
aileron.
The
tabs
are
manually
controlled
through
cable-drum
systems,
using
jackscrew
actuators.
Tab
position
indicators
are
provided
on or
near
the
tab
controls.
The
optional
electric elevator
trim
tab is controlled
by
a
switch
in the
outboard handle
of the
pilot’s
control
wheel.
Positive
stops
on
the
primary flight
control
surfaces limit
their
travel.
Travel
stops
secured
to
the
tab
control
cables
limit
trim tab
movement.
The
correct
routing
of cables
as
shown in the
applicable
rigging
illustrations
will
prevent
crossing
the
cables
and
causing
incorrect
movement
after
the cables have
been
removed
and
reinstalled.
Control
movement
and direction
should
be
checked after maintenance.
Refer
to
the
applicable
rigging
procedures
for details
regarding
chain and cable
tension,
control
wheel
movement
and
force,
downspring
force
and
system
friction.
E16
4-1