Piper CHEROKEE ARCHER II Pilot Operating Handbook page 45

SECTION
3
EMERGENCY PROCEDURES
PIPER
AIRCRAFT CORPORATION
PA.2&181, CHEROKEE ARCHER tr
3.I9
LOSS
OF FUEL PRESSURE
If
loss
of
fuel pressure occurs, turn
"ON"
the electric fuel pump and check that the fuel selector
is
on
a
full
tank.
If
the problem is not an empty tank, land
as
soon
as
practical and have the engine'driven fuel pump
and
fuel system checked.
3.21
HIGH OIL TEMPERATURE
An
abnormally high
oil temperature indication may
be caused
by
a
low oil
level, an
obstruction in the
oil
cooler, damaged
or improper
baffle
seals, a
defective
gauge,
or other
causes.
Land
as
soon
lts
practical at
an
appropriate airport and
have
the
cause
investigated.
A
steady, rapid rise
in
oil
temperature
is a
sign
of
trouble. Land
at
the nearest
airport and let
a
mechanic investigate the
problem. Watch the oil
pressure gauge
for
an
accompanying loss
of
pressure.
3.23
ALTERNATOR FAILURE
Loss
of
alternator
output is
detected through zero reading
on the
ammeter. Before executing the
following procedure, insure that the reading
is
zero and
not merely low by actuating
an
electrically powered
device,
Juin
as
the tanding light.
If
no
increase
in
the ammeter reading
is noted, alternator failure can
be
asumed.
The electrical load should be reduced
as
much
as
possible.
Check the alternator circuit breakers for
a
popped circuit.
The next step is
to
attempt to
reset
the overvoltage relay. This is accomplistred by moving the
"ALT"
switch
to "OFF" for
one second and then to
"ON."
If
the trouble
was caused
by
a
momentary overvoltage
condition (
16.5
volts
and
up) this procedure strould
return the
ammeter
to
a
normal reading
If
the ammeter continues to indicate
"O"
output, or
if
the alternator
will not
remain reset, turn
off
the
"ALT" switch, maintain minimum electrical load
and
land
as
soon
as
practical.
All
electrical load
is
being supplied
by the battery.
3.25
SPIN
RECOVERY
Intentional spins
are prohibited
in
this airplane.
If
a
spin is inadvertently entered, immediately move
the
throttle to idle and the ailerons to neutral.
Full rudder should then
be applied
opposite to the direction of rotation followed by control wheel
full
forward.
When
the rotation
stops,
neutralize the nrdder and
ease
back on the control wheel
as
required to
smoothly regain
a
level
flight attitude.
REFOf,,T:
V.}7t0
3-r0
:\
fiiSUED:
It
NE
18, 1976