tank may occur
if
the wings
are
not maintained exactly
level. Resulting wing heaviness can be alleviated
gradually
by
turning the
selector
valve handle to the
tank
in
the "heavy" wing.
NOTE
It
is
not practical to measure the time
required
to con-
sume all of the fuel in
one
tank, and,
after
switching
to the opposite
t3:nk,
expect an equal duration from the
remaining fuel. The
airspace
in both fuel tanks
is
in-
terconnected by a vent line (figure 2-2) and, therefore,
some sloshing
of
fuel between tanks
ca~
be expected ·
when the tanks
are
nearly full and the wings
are
not level.
For
fuel system servicing information,
refer
to Servicing Require-
ments
on
the inside back cover.
•
<"
r •
~
FUEL
TANK SUMP
QUICK-DRAIN
VALVES.
Each fuel tank sump
is
equipped with a fuel quick-drain valve to
facili-
tate draining
and/or
examination
of
fuel for contamination and
grade.
The
valve extends through the lower
surfac~
of the wing just outboard of the
cabin door. A sampler
cup
stored in the
aircraft
is
used to examine the
fuel.
Insert
the probe in the sampler cup into the
center
of the quick-drain
valve and push. Fuel will drain
fJ,"om
the tank sump into the
sampler
cup
until
pressure
on
the valve
is
rele"ased. .
LONG
RANGE
FUEL
TANKS.
-
Special wings with long _
z:ange
fuel tanks
are
_ available to replace the
standard wings and fuel tanks for·
greater
endtirance and range.
When
these tanks
are
installed, the total usable fuel for all flight conditions
is
48
gallons.
ELECTRICAL
SYSTEM.
Electrical energy is supplied
by
a 14-volt
direct-current
s t
db
· · d · '
ys
em
powe:e y an engme- riven alternator (see figure 2-3). A 12- vol
tery is located
on
the left-hand forward portion
of
the f t
ba~-
supplied
to
all electrical circuits through a
sprt
b b irewall
..
Power is .
1
us
ar,
one side con-
2-3 .
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