Raytheon Beech Baron E55 - Page 495

aeed~craft
BARON
55
AND
58
SHOP
MANUAL
PRESSURE
SYSTEM
IN-LINE
FILTER
c.
Repeat
the
adjustment
in
step
b
on
the
opposite
INSPECTION
(TE-452
AND
AFTER,
TH-1
side
of
the
airplane.
AND
AFTER,
TC-2003
AND
AFTER)
d. Locate the
gyro
instrument
adjustable
orifice
or
On
airplane
serials
TE-452
thru TE-936
and
TH-1
thru
regulator
valve
(if
installed)
on
the
LH side of
the air-
TH-372,
remove
both
in-line
filters
from the
system
plane
forward
of
the instrument
panel,
near
the
top
of
and
check
for
obstruction
by
comparing
the
resistance
the
upholstery
panel
and
adjust
as
follows:
to
flow
with
a
new
filter.
Use
a
dry, low-pressure
air
1.
Loosen the check
nut
and
rotate
the
orifice
source
(max.
of 10
psi)
to
accomplish
this
test.
If
the
body
(adjusting
screw on
the
regulator)
to obtain
a
resistance
to
air
flow in
a
filter
removed from
the air-
reading
of
5.0 +.1
-.2 in.
Hg
on
the
gyro pressure
indi-
plane
exceeds that
of
a
new
filter
by
more
than
one
cater
with
both
engines
operating
at
2300
rpm.
psi,
the
filter
should
be
replaced.
On
airplane
serials
2.
Tighten
the
check nut
and
recheck the
gyro
TE-937
and
after;
TH-373
and
after;
TC-2003
and
pressure
indicator
to
read
in
the
green
are
with both
after,
the
filter
should
be
replaced
annually,
every
300
engines operating
at
1500
rpm.
hours
of service
time
or
sooner
depending
upon
oper-
ating
conditions.
The filter
must
not
be
subjected
to
e.
After
adjusting
the
orifice
(regulator),
the
pressure
solvents
and
must
be
replaced
if this
occurs.
on
the
test
gages
at
the
pressure
regulators
in
the
nacelles
should
be
rechecked
with
each
engine
oper-
PRESSURE
SYSTEM
ADJUSTMENT
ating
individually
at
2300
rpm.
If
the
pressure
on
these
(TE-452
AND
Af-ltH,
JH-
I
AND
AFTER,
gages
has been affected
by
the
adjustment
of
the ori-
fice
(regulator),
the
regulators
in
the
nacelles
should
TC-2003
AND
AFTER)
be
readjusted
to 5.0 t.5
psi.
Adjustment
of the
pressure
system
components
in
a
f.
With
both
engines
operating
at
2300
rpm,
the dif-
specified
sequence
is
given
independently
for each
ference between
the
pressure gages
at
the
pressure
configuration
available.
The
following
system
head-
regulators
in the
nacelles
should
not
exceed
.5
psi.
ings
will facilitate
adjustments
on a
particular airplane.
NOTE
Adjustments
may
be
accomplished
as
follows:
If
the
requirements
of this
adjustment
BASIC
PRESSURE
SYSTEM
(INSTRUMENTS
procedure
cannot
be
obtained,
the
com-
p\ete
system (including
the check valves
ONLY)
on
the
manifold)
should
be
checked
for
(Flgure
11-9)
leaks
and/or
restrictions;
then
any
dis-
crepancy
should
be
repaired
and
the
NOTE
system
readjusted.
Airplane
serials
TE-452
thru
TE-767
are
g.
Remove
the
test
gages
from
the
airplane.
equipped
with
a
gyro
instrument
adjust-
able orifice.
Airplanes
TC-2003
thru
BASIC
PRESSURE
SYSTEM
WITH
8-4,
8-5,
OR
TC-2102,
TE-763
thru
TE-1133,
and
8-7
AUTOPILOT
INSTALLATION
TH-1 thru
TH-935
are
equipped
with
a
(Figure
gyro
instrument
regulator
valve.
NOTE
a.
Install
a
test
gage
(0
10
psi)
at
the "out"
side
of
each
pressure
regulator.
Airplane
serials
TE-452
thru
TE-767
are
equipped
with
a
gym
instrument
adjust-
b.
Operate
one
engine
at
2300
rpm
and
adjust
the
able
orifice.
Airplanes
TC-2003
thru
pressure
regulator
for
that
engine
to
obtain
a
reading
TC-2102,
TE-788 thru
TE-1133,
and
of 5.0
+.5
psi
on
the
test
gage.
TH-1 thru TH-935
are
equipped
with
a
gyro
instrument
regulator
valve.
NOTE
a.
Install
a
test
gage
(0-10 psi)
at
the
"out"
side of
Rotate
the
pressure
regulator
adjusting
each
pressure
regulator.
screw
clockwise
to
increase
pressure
and
counterclockwise
to
decrease
pres-
b.
Install
a
test
gage
(0-10 psi)
in
the
turn
coordina-
sure.
tor
supply
line. Refer
to
Figure
11-10.
815
11-15