Piper COMANCHE 260 User Manual

THE
PIPER
COMANCHE
SECTION
I
SECTION I
DESIGN INFORMATION
ENGINE AND PROPELLER
The
Comanche
260
is
powered
by
a
Lycoming
0-540-E,
carburetor
induction
engine
or
a
Lycoming
10-540-D,
fuel
injection
engine.
Both
engines
are
rated
at
260
HP
at
2700
RPM,
with
a
compression
ratio
of
8,5to
1
and
require91
/96
minlmum
octane
aviation
fuel.
The
six
cylinder,
direct
drive
engines
are
equipped
with
a
geared
starter,
12
volt
75
ampere
alternator,
carburetor
or
fuel
injector,
vacuum
pump,
dia-
phragm
fuel
pump
and
shielded
ignition
system.
Engine
mountis
of
steeltubing
construction
and
incorporate
vibration
absorbing
dynafocal
mounts.
The
allaluminum
engine
cowl,
is
a
cantilever
structure
attached
at
the
firewall.
Side
panels
are
hinged
for
quick
access
to
the
engine
compartment.
The
exhaust
system
consists
of
dual
exhaust
stacks
and
mufflers
with
the
exhaust
gases
being
directed
over-board
at
the
bottom
rear
of
the
cowling,
on
each
side
of
the
nose
gear.
Heat
for the
cabin
interior
and
defrosting
is
taken
from
the
left
muffler
shroud.
An efficient
aluminum
oil
cooler
is mounted
on the
left
front
engine
baffle.
Engine
oil drainage
is accomplished
by
a
quick
drain
installed
in
the
right
side
of
the engine
sump.
The
propeller
on the
Comanche
is
a Hartzell
HC-
C2YK-1A/8467-7R
constant-
640901
S

Piper COMANCHE 260 Specifications

General

Brand	Piper
Model	COMANCHE 260
Category	Aircrafts
Language	English