Raytheon Beech Baron E55 - Page 385

’i~echcraft
BARON
55
AND
58
SHOP MANUAL
NOTE
position
in
order
to
provide
the
most accurate
read-
After
each mixture
adjustment,
clear
the
ing.j
Return
the fuel
from
the
Flow Rater
back to
the
engine
by running
up
to
approximately
airplane
fuel
system
through
the
wing
filler
port.
2000
rpm
before
making
the
next
mix-
NOTE
ture
check.
Use
an
external
power
supply
capable
of
FULL THROTTLE FUEL
PRESSURE
providing
28.25
.25
volts
for
the
source
ADJUSTMENT,
IO-550-C ENGINE
of
electrical
power.
(Effectivity:
TH-1389,
TH-1396
and
after)
c.
Turn
the
airplane
AUX
FUEL
PUMP
to
HI.
d.
Adjust
the
Flow
Rater
(using
the
adjustable
valve)
a.
Install
a
pressure
gage
in
the
line between
the
to
the
test
readings
in
Chart
6-3 and record the air-
engine
fuel flow
transducer
and the
manifold valve.
plane
fuel
flow
(gph)
from
the fuel flow
indicator
on
a
NOTE
copy
of Chart
6-3.
The
pressure
gage
should
be
vented
to
NOTE
the
atmosphere
and
mounted
at
approxi-
The
throttle
and
mixture
levers
must
be
mately
the
same
level
as
the
manifold
valve,
fully
forward. Use
the
adjustable
valve
shown
to
adjust
the fuel
flow
as
neces-
b.
Run
the
engine
until normal
operating
tempera-
sary.
Refer
to
Figure
6-8.
tures
are
attained.
e.
Once
an error
in
the
airplane
fuel flow hardware
c.
With
the mixture control
in
the
full
rich
position,
has
been
determined. Correct
the
system
as
in the
advance
the
throttle
control
to
full throttle
and
maxi-
following
example:
mum
static
rpm.
Check
the metered
fuel
pressure.
EXAMPLE:
d.
Refer
to
Chart
6-2
to
determine
of the
correct
metered
fuel
pressure.
If
a
fuel
pressure
adjustment
is
At
80
pph
flow
rate
with the
fuel
temperature
at
40"
F,
required,
turn
the
fuel
bypass
adjustment
screw as
an
airplane
fuel
flow indicator
reads 13.0
gph.
Using
a
necessary
to
obtain
the
correct
metered
fuel
pressure.
fuel
density
of
5.9,
Chart
6-3 shows the
indicator
Turn
the
bypass
adjustment
screw
clockwise to
should
be
reading
13.5
gph.
Therefor,
the instrument
increase
pressure
or
counterclockwise to
decrease
error
is
0.5
gph
low.
When
the
airplane
indicator
is
pressure.
Refer
to
Figure
6-7.
reading
t3.0
gph,
add
0.5
gph
for
system
correction.
NOTE
NOTE
This fuel
flow indicator check should
be
The
fuel
pump
adjustment
procedure
is
a
starting point
for fuel
pressure
adjust-
made
at
all
ten
flow
rates
as
the
system
ment
at
full throttle.
"FUEL
FLOW SYS-
error
may vary
as
the
flow
rate
changes.
TEM
CALISRAT\ON
AND
CORREC-
f.
Repeat
the
preceding steps
for the
opposite
eng-
TION" MUST also be
completed.
ine
fuel flow
system.
FUEL FLOW SYSTEM
CALISRATION
AND
NOTE
CORRECTION
(Effectivity:
TN-1389,
The FULL THROTTLE FUEL PRES-
TH-
1396
and
after)
SURE
ADJUSTMENT,
IO-550-C
(Figure
6-8
TH-1389
and
TH-1396
and
after)
proce-
dure
MUST
be
completed
before
pro-
A
fuel flow
system
calibration
and
correction
should be
ceeding.
obtained from the
following procedure:
g.
Flight
check
for
proper
engine
fuel
schedule.
a.
Remove
the
upper
engine
cowling
assembly.
Establish
a
climb
at
110
hias
(knots
indicated
air
b.
Install
a
Fisher
Porter
Flow
Rater
or
equivalent
speed).
flow
meter
at
a
point
between
the
fuel
flow transducer
Throttle.........................................,.Fully
Forward
and
the
engine
fuel
distributor
valve.
(The
Fisher Por-
ter
Flow
Rater
must
be
installed
in
a
straight
vertical
Prop......................................................2500
rpm
6-12
515