Section
II
b
~=========~~~~~:::::::-
_______________________
,,
...
...,_
DESCRIPTION
AND
OPERATING
DETAILS
. . .
The following paragraphs describe the systems and equipment whose
function
and
operation
is
not obvious
when
sitting in the aircrat;t. This
section also covers in somewhat
greater
detail some
of
the items listed
in
Checklist 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
conditions
is
38
gallons for the standard tanks.
"'
: .
..__
Fuel from each wing tank
flows
}?y
·gravity
to
·a seJector valve. De-
pending
upon
the setting
of
the
select~r
~alve,
fuel from the left, right,
or both tanks
f~ows
through a fuel
st
_rainer and carburetor to the
~ngine
mduction system. . . . .
. The fuel
sele~tor
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
ta~
or
less), a prolonged steep de-
scen~
_
(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
s·econds.
NOTE
When
the fuel selector valve handle_
is
in the
BOTH
po
.:
: ·
sition in cruising flight, unequal fuel
flow
f.rom each
2-1
;..
r
--
·
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