Raytheon Beech Baron E55 - Page 369

Raytheon
AiKraft
Company
BARON
55
AND 58
SHOP
MANUAL
THROTTLE
WARNING
HORN
AND
LIGHT SYSTEM ADJUSTMENT
(TH-1543,
TH-1545
AND
AFTER)
The
system
is
designed
for the
landing
gear
warning
horn
to
sound
intermittently
and
for
the red
gear-up
annunciator
light
to
flash
with the
landing
gear
retracted
and either
or
both throttles retarded
to
obtain
approximately
13
1
in.
I
of
Hg
in
manifold
pressure.
The
warning
horn
and
light
are
also actuated
when
the
flaps
are
fully
down
and
the
landing
gear
is
retracted.
System
adjustment
is
as
follows:
a.
With the
airplane
in
flight
andthe
landing
gear
retracted,
retard the
throttles
to
obtain 13
1
in.
of
Hg
in
manifold
pressure.
NOTE: Make all
subsequent
checks
at
the
same
altitude and
airspeed.
b.
Mark the
position
of the throttle
controls
on
the
pedestal.
c.
After the
airplane
has
landed
and
the
engines
have been
shut
down,
match
the
position
of each throttle
control
to
the
marks
made
on
the
pedestal.
d. Loosen the
retaining
nuts
and
adjust
each
cam
on
the end
of
its
respective
actuator
rod
for the throttle
waming
switch
just
forward
of
the
pedestal
so
that
the switch closes
(indicated
by
a
click)
at
the
point
where
the throttle
control
position
matches the
marks
made
in
Step
b.
(Ref.
Figure
16
for switch
identification).
Tighten
the
retaining
nuts
securing
the
cam
in this
position.
e.
Check
the
switches
for
proper
operation
in
flight
as
described
at
the
beginning
of
this section.
LANDING
GEAR-UP
INTERRUPT
CIRCUIT
(TH-1543,
TH-1545
AND
AFTER)
These
airplanes
are
equipped
with
switches
actuated
by
throttle
position
to
interrupt
the
landing
gear-up
circuit
to
prevent
the
landing
gear
from
retracting
when the throttles
are
retarded
below
15
+2
-1
in.
of
Hg
in
landing
gear
frcm
renacting
when
the
throttles
are
retarded
below 1512
-t
in. ol
Hg
in manildd
I
GEAR-UP INTERRUPT
CIRCUIT
ADJUSTMENT
(TH-1543,
TH-1545
AND
AFTER)
a.
With
the
airplane
in
flight
at
a
speed
between
100
to
110
knots,
place
the
propeller
controls
fully
forward
to
high
rpm,
then
slowly
retard the
throttle controls
to
obtain 15
+2
-1
in. of
Hg
in
manifold
pressure.
b.
Mark
the
position
of
the
throttle
controls
on
the
pedestal.
c.
After
the
airplane
has
landed
and
the
engines
have been shut
down,
position
the throttle
controls
to
match
the
marks
made
on
the
pedestal
in
the
preceding
step.
d. Loosen the
retaining
nuts
and
adjust
each
cam
on
the
end
of
the
actuator
rod
for
each
retract-prevent
switch
just
forward
of the
pedestal
so
that
the
switch
closes
(indicated
by
a
click)
at
the
point
where the
throttle
control
position
matches the
marks made
on
the
pedestal
(Ref. Figure
16
for
switch
identification).
Tighten
the
nuts
securing
the
cam
in
this
position.
e.
Check
the
switches
for
proper
operation
in
flight
as
follows:
1.
With
the
landing
gear
down,
retard
both throttle controls
to
a
position
below
the switch
setting.
2.
Place
the
landing
gear
in
the
UP
position;
the
landing
gear
should
not
retract.
3.
Advance either
throttle
control
slowly
and
note
the
manifold
pressure
at
which
the
landing
gear
retracts.
The
landing
gear
should
retract
with
only
one
throttle
control
advanced
if
the
system
is
functioning
properly.
NOTE:
The
system
circuit
includes
a
latching relay
that
enables
the
landing
gear
to
fully
retract
once
retraction is
initiated.
Retarding
the throttle
control should
not
stop
the
gear
in
mid-travel.
E22
SECTION
5Page
75