CHEROKEE
WARRIOR
Manually
controlled
flaps are
provided
on the
PA-28-151. The
flapsare balanced
forlight
operating forces and spring loaded to return to the retracted
(up)
position.
A control
handle,
which
is located between the two front
seats
on the control console,
extends
the
flaps by the
use
of a control cable. To extend the flaps, the
handle is
pulled
up to the desired flap setting
of
lO,
25 or 40
degrees.
To retract, depress the button on
the
end
of the
handle and lower the
control.
When
extending or retracting flaps, there
is
a
pitch
change
in
the
airplane.
This
pitch
change can be conected
either by stabilator trim or increased control
wheel force.
When
the
flaps
are in the retracted
(up)
position
the
right
flap,
provided
with an over-center
lock
mechanism, acts as a step.
NOTE
The
right
flap will support a
load
only in the
fully retracted
(up)
position.
When
the flap
is to be used as a step,
make sure the
flaps
are
in the retracted
(up)
position.
FUEL SYSTEM
Fuel
is stored in two
twenty-five
gallon
(24
gallons
usable)
fuel tanks,
giving
the airplane a
total
capacity of
fifty
U.S.
gallons
(48
gallons
usable). The tanks
are secured to the leading edge
of each wing with screws and
nut
plates.
This allows easy removal
for
service or
inspection.
On serial numbers
7415001 through
7515449
each
fuel tank has two
outlets, one forward
and one
aft,
to ensure an even
fuel flow. Fuel is
pumped
from the tanks through
the
forward
and aft tank outlets
to
fuel manifolds
in the
inboard section of
either
wing.
Each
manifold is a
small collector
with
an inlet
hose from each
of
the tank outlets,
and an outlet
hose to the
fuel
selector
valve.
On serial
numbers
7615001
and
up there is only
one outlet on each
tank and
no
fuel manifolds are used.
The fuel tank selector control is located on the left side
panel
forward of the
pilot's
seat.
The button on the selector cover must be depressed and
held while the handle is moved
to the
OFF
position.
The button releases automatically
when the handle is
moved back to the
ON
position.
An auxiliary
electric fuel
pump
is
provided
in case
of the
failure of
the
engine
driven
pump.
The
electric
pump
should
be ON for all takeoffs
and
landings and
when
switching
tanks.
The fuel
pump
switch
is
located in the switch
panel
above
the throttle
quadrant.
'l'lrc
fuel druins
shotrltl
bc o;rcnctl
daily
prior
to
first flight to chcck
fr>r
watcr or sedimcnt.
h,aclr tank has an
individual
drain
at the
bottom, inboard
rear corner, and each
fuel
manifold
(on
early
models only) is
equipped
with
a drain. The
outlets are
located on the
underside of the
wings.
A
gascolator,
located
on
the lower left front of the
fire
wall,
has a drain
which is accessible
from outside the
nose section. The
gascolator
should also
be drained
before the
first flight of
the day.
(See
the
Handling and Servicing Section for the complete
fuel draining
procedure.)
Fuel
quantity
and
fuel
pressure
gauges
are
mounted
in a
gauge
cluster located
on
the left
side of the
instrument
panel
to the right of the control
wheel.
An
optional
engine
priming
system
is available
to facilitate
starting.
The
primer
pump
is
located to the
immediate left of
the throttle
quadrant.
AIRPLANE
AND
SYSTEII{S
REVISED: JULY
14,1975
2-7
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