Piper Cherokee 140 - Page 15

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