Raytheon Beech Baron E55 - Fuel System

FUEL SYSTEM
ment.
The
fuel
selector
valve
for each
engine
is
located
below
this
panel
and
during
normal
operation,
fuel
is
con-
Sbrvice
all
fuel
systems
with aviation
gasoline,
100
LL
sumed
from
each
wing
system
as
indicated
by
the
fuel
setec-
(Blue)
preferred
or
100
(Green)
octane
minimum
grade,
tor
handles.
Two
fuel
quantity
indicators
on
the
instrument
panel
indicates
the
amount
of
fuel
in
each
wing
system.
Fuel
crossfeed
operation
is
used
during
emergency
condition!,
in
TC-l
THRU
TC-1607AND
TE-1 ;THRU
TE-942,
EX-
level
flight
only.
CEPT
TE-938
8
snap-type
drains
(4
per
wing)
are
provided.
One
drain
in
Airplane
serials
TC-I
thru
TC-1607
and
TE-l thru
TE-94?,
each
wing
is
provided
for
the
inboard
wing
leading edge
fuel
except
TE-93X
are
equipped
with
a
non-interconnected
fuel
cell
sump;
fuel
strainer:
wing
box
section
fuel
cell
sump:
fuel
system.The
main and
auxiliary
cells
in each
wing
provide
system
low
point
tin
wing).
the
airplane
with
a
total fuel
capacity
of either
I
]Z
gallons
(106
gallons
usable)
or
142
gallons
(136
gallons
usable).
These
systems
have
either
2.F
or
40
gallon
baffled
or
unbaf-
TE-938,
TE-943
THRU
TE-1083
EXCEPT
TE-
1081
fled
inboard
wing leading
edge
main
fuel
cells with
a
finger
strainer
in
each inboard
wing leading
edge,
and
a
31
gallon
Airplane
serials
TE-93X.
TE-91.3
thru
TE-IOK?.
rxcrtpl
PF
auxiliary
fuel
cell with
finger
strainer
in
each
wing
box
1081
are
equipped
with
interconnected
fuel
celh
~n
each
section.
Thus,
there
is
a
total
of
either
53
or
68
gallons
usable
wing
to
provide
the
airplane
with
a
total fuel
capacity
c~f
in
each
wing
for
a
total of
either
106
or
136
gallons
usable
either
142
gallons
1136
gallons
usable)
or
17’
gallons
I
IM,
with all
fuel
cells
full.
One
flush-type
filter
cap
is
in each
gallons
usable).
Except
for the
engine
fuel
lines
forward of
inboard
wing
leading
edge
and
one
flush-type
filler
cap
is
the
firewalls,
the
142
gallon
total
capacity
system
is
the
\ame
located in
the
outboard
end
of
each
wing
box
section
cell.
as
described
under
the
heading
TC-\h08
THROUGH
TC-
2002,
EXCEPT
TC-1970
in this
section.
A
fuel
selector
panel
in
the
cabin
fuselage,
in
front
of the
spar
cover
between
the
front
seats,
is
placarded
OFF-AUX-
The
17?
gallon
system
utilizes
cells described
in
the
11~
MAIN-CROSSFEED for
fuel
management.
The
fuel selec-
gallon
system
and
an
additional
fuel cell
in
each
outhoarcl
tor
valve
for
each
engine
is
located
below
this
panel
and
wing leading
edge.
This
cell
has
a
bottom
mounted
fuel Irvrl
during
normal
operation
fuel
is
consumed
from
the
fuel cells
transmitter
located in
the
inboard
end
of
the cell,
The
celh
in each
wing
as
indicated
by
the
fuel
selector
handles.
Two
are
interconnected
to
provide
83
gallons
usable in each
~vlng
fuel
quantity
indicators
on
the
instrument
panel
indicate
the
system
or
a
total
of
16h
gallons
usable
with
left
and
right
amount
of
fuel
in
either
the main
or
auxiliary
fuel
cells
for
wing
systems
full. One
flush-type
filler
cap
is in
the
oulhoard
their
respective
wings.
A
two
position
fuel
cell selector
end
of
each
outboard
wing
leading
edge
cell.
switch
on
the
pilots sub-panel
determines
the
fuel
cells, main
or
auxiliary,
to
which
the
fuel
quantity
indicators
are con-
The
function
for
fuel
management
and the
fuel
4elector
nected.
Fuel
may
be
used
as
desired
during
level
flight,
panel,
fuel
selector
valves
and
fuel
quantity
indfclltor\
are
in
however,
since
fuel
from
auxiliary
cells
must
be
used in
level
the
same
location
as
described
for
the
142
gallon
total
capac-
flight
only,
sufficient
reserve
must
be
retained
in
the main
itY
system
under
the
heading
TC-
I
601(
THROUCJH TC-Z(W)~.
fuel
cells
for
take-off,
climb
and
landing.
Fuel
crossfeed
EXCEPT
TC-
1970.
operation
is
used
in these
systems
during
emergency
condi-
tions in
level
flight
only.
NOTE
X
snap-type
drains
(4
per
wing)
are
provided.
One
drain
in
each
wing
is
provided
for
the
inboard
wing
leading
edge
fuel
Fuel
crossfeed
operations
are
used
in
these
~y\
cell
sump:
fuel
strainer
drain:
auxiliary
fuel cell
sump:
fuel
tems
during
emergency
conditions
in
level
flight
system
low
point
in
each
side of
cabin
fuselage
bottom.
only.
TC-
1608
THRU
TC-2002,
EXCEPT
TC-
1970
X
snap-type
drains
(4
per
wing)
are
provided.
One
drain
in
each
wing
is
provided
for
the
inboard
wing leading
edge
fuel
Airplane
serials TC-1608
thru
TC-2002,
except
TC-
1970,
are
cell
sump;
fuel
strainer;
wing
box
section
fuel
cell
sump:
fuel
equipped
with
an
interconnected fuel
system.
The tanks
are
system
low
point
tin
wing).
interconnected
within each
wing
and
provide
the
airplane
with
a
total
fuel
capacity
of
142
gallons
(136
gallons
usable),
This
system
has
an
inboard
wing
leading
edge
unbaffled fuel
TH-
I
THRU
TH-384
cell with
fuel
reservoir,
finger
strainer and
fuel
outlet
nipple
through
the
wing
root
rib that
is interconnected
to
a
wing
box
Airplane
serials
TH-\ thru
TH-78~
;~re
ttquipped
w,th
inlt’r-
section
fuel cell
for
68
gallons
usable in
each
wing
system
or
connect
cells
in
each
wing
to
provide
the
airplane
with
a
total
a
total
of
136
gallons
usable
with
left
and
right
wing
systems
fuel
capacity
of
either
142
gallons
(136
gallons
usable) or
172
full.
One
flush
type
filler
cap
is
located
in
the
out´•board
end
gallons
(16h
gallons
usable).
The 142
gallon
total
capacity
of
the
wing
box section cell.
A
fuel
selector
panel,
located
in
system
has
an
inboard
wing
leading
edge
baffled
fuel
cell
the
cabin
fuselage
in the
front
spar
cover
between
the
front
with
sump
strainer
and
fuel
outlet
nipple through
the inboard
seats,
is
placarded
OFF-ON-CROSSFEED
for
fuel
manage-
end
of
the
wing
main
spar.
This cell is interconnected
to a
8-1