Section
II
DESCRIPTION
AND
OPERATING
DETAILS
The following paragraphs
describe
the
systems
and equipment
whose
fimction
and operation is not
obvious
when sitting in the aircraft. This
section
also
covers
in
somewhat
greater detail
some
of the items listed
in
Check
List form in
Section
I that require further explanation.
FUEL
SYSTEM.
Fuel is supplied to the
engine
from two tanks, one in
each
wing. With
the fuel
selector
valve on BOTH, the total
usable
fuel for all flight condi-
tions is 38
gallons
for the standard tanks and 48
gallons
for the optional
long
range
tanks.
Fuel from
each
wir^ tank flows by gravity to a
selector
valve. De-
pending upon the setting of the
selector
valve, fuel from the left,
right,
or both tanks flows through a fuel strainer and carburetor to the
engine
induction
system.
The fuel
selector
valve should be in the BOTH position for take-off,
climb, landing, and
maneuvers
that involve
prolonged
slips or skids.
Operation from either LEFT or RIGHT tank is
reserved
for cruising
flight.
NOTE
With
low fuel (l/8th tank or
less),
a
prolonged
steep
de-
scent
(1500
feet
or
more)
with
partial
power,
full
flaps,
and 80 MPH or greater should be
avoided
due to the
pos-
sibility
of the fuel tank outlets being
uncovered,
causing
temporary fuel starvation. If starvation
occurs,
leveling
the
nose
should
restore
power
within
20
seconds.
NOTE
When the fuel
selector
valve handle is in the BOTH po-
sition
in cruising
flight,
unequal fuel flow from
each
2-1
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