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THE
PIPER CHEROKEE
SECTION
II
sEcTtoN il
DESIGN INFORMATION
ENGINE
AND
PROPELI.ER
The
Lycoming
o-IZo.EzA
enginc
inselled
in
rhe
Cherokce
PA-28-140
is ratcd
ar
l4O
horsepowcr ar 2450
rpm
or
150 horsepower
"t
27OO
rpm..,This
cngine
has
a
compression
ratio
of
7
to
I
end
requires
8O/87
minimum
octanc
fucl. Rcfcr
to
Fuel
Rcquiremenrs on
page
30
when
using alrcrnarc
fuels. The
engiae
is
eguipped
with
a
gcared
startcr,
a
35
ampcre
alternator, dual
magnctos,
vacuum pump
drive,
a
diaphragm-rypc
fuel pump
and
a
float
carburetor.
Exhaust gases
are carried
through a
system constructed
of
heavy
gauge
stainless
steel which
incorporates
a
heater
shroud, to provide cabin
heat
and
carburetor
deicing.
The
propeller
used on the PA-28- I40
is
a
Sensenich M74DM
fixed-pitch
aluminum
alloy unit. Its
diameter
is
74
inches
with
a standard
pitch
of
60*
inches, All
performance
figures
are
based on
the
srandard
60* inch pitch
propeller.
Cowling on the
Cherokee
ts
designed
to
cool
the engine in
all
normal
flight conditions,
including protracted
climb, with-
out the use of
cowl
flaps or
cooling
ftanges.
The throttle is
of
the
push-pull
type
and
is
located
ir
the
lower center
of
the
instrument
panel.
A knurled
friction
lock
ls
provlded
toprevent
creepingof
the
throttle from
any
desired
position.
The
mixture control,
located
in
the
lower
right
hand
side
of
the
instrument panel,
is
a push-pull control llke
the
throttle.
The
full rich
posirion
is
obrained
when
the
control
is
full
forward,
whil.e the
full
aft
position provides
an
idle cur-off
*58 lnch plrch
propellers
when
gross weight
is
2I50.
+*When
gross weight
is
2150
770527
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