Specifications
CHEROKEE
SIX
-
3OO
5.
tf
the
"Air
Cond. Door Open" light
does not respond
as
specified
above,
an air
conditioner
system
or
indicator
bulb
malfunction
is
indicated,
and
further
investigation
should
be conducted
prior
to
flight.
The above operational
check
may
be
performed
during fliglrt
if
an
in
flight failure
is
suspected.
AIR
CONDITIONER EFFECTS
ON AIRPLAT.IE
PERFORMANCE
Operation
of the air conditioner will cause slight decreases
in
cruise
speed
and range.
Power
from
the
engine
is required to run the
compressor,
and the condenser
door,
when extended,
causes
a slight increase
in
drag.
When
the air conditioner
is turned off there
is normally
no
measurable
difference in
climb,
cruise or
range
performance
of the airplane.
NOTE
To
insure maximum climb
perfornance
the
air conditioner
must
be
furned off manually
before takeoff
to
disengage
the
compressor and
retract
the condenser
door. Also the
air
conditioner
must
be turned
off
manually
before the
landing
approach
in
preparation
for a
possible
go-around.
i
Although
the cruise
speed
and range
are
only
slightly
affected
by
the
air
conditioner
.operatiou,
these
changes
should be considered in
preflight
planning.
To
be
conservative, the
,following
figures
assume
that
the
compressor
is
operating
continuously
while
the
airplane is
iairborne.
This
will be
the case only
in
extremely hot
weather.
The decrease
in true
airspeed
is
approximately
5 mph
at
all
power
settings.
The decrease in
range may
be
as
much as 35
statute
miles for the 84
gallon
capacity.
The
climb
performance
is
not
compromised
measurably
with the air conditioner
operating
since
the
compressor
is
declutched
and the
condenser
door
is
retracted,
both
automatically,
when
a
full
throttle position
is
selected.
When the
full throttle
position
is
not
used
or
in the
event of
a malfunction
which
would cause the
compressor
to
operate and the
condenser
door
to
be
extended,
a decrease
in rate
of
climb
of as
much
as
100
fpm can
be
expected. Should a
malfunction
occur
which
prevents
condenser
door
retraction
when the
compressor is turned olT,
a decrease
in
rate
of climb
of
as much
as 50 fpm
can
be
expected.
EMERGENCY
LOCATOR
TRANSMITI:ER*
The
Emergency Locator Transmitter
(ELT)
when
installed,
is located
in
the
aft
portion
of
the
fuselage
just
below the
stabilator leading edge and is
accessible
through
a
plate
on
the right
side
of the
fuselage.
(On
aircraft
manufactured
prior
to
mid-1975,
this
plate
is retained by
three
steel Phillips
head screws.
On aircraft
manufactured from
mid-1975
and on,
this
plate is
attached
with
three slotted-head nylon
screv/s for ease
of
removal;
these
screws may be readily
removed
with
a
variety
of common items
such
as a dime, a
key,
a knife
blade,
etc. If there
are
no
tools
available in
an
emergency the
screw heads
may
be
broken
off by any means.)
The
ELT
is an
emergency
locator
transmitter which
meets
the requirements
of
FAR
91.52. The unit
operates on
a
self-contained battery. The
replacement
date
as required
by
FAA regulations
is
marked
on
the
transmitter
label.
*Optional
equipment
OPERATING
IN
STRUCTIONS
REVISED:
DECEII{BER
15.
1978
l.
2.
7-tl