Piper COMANCHE 260 User guide

the
LOBFRLLE ()
Owner’s
Handbook
N
Piper
Aircraft
Corporation,
Lock
Haven,
Pa.
U.S.
A.

Additional copies of this manual may be purchased
by writing to the SERVICE SPARES DIVISION,
PIPER AIRCRAFT CORPORATION, Lock Haven,
Pennsylvania, 17745, U.S.A.
Published By
PUBLICATIONS DEPARTMENT
Piper Aircraft Corporation
753 685
Issued: September 1964
Revised: January 1965
Revised: February 1966

Power Plant .
Performance .
Weights
Fuel .
Baggage
Dimensions .
Landing Gear
640901
SECTION |
SPECIFICATIONS

THE
PIPER
COMANCHE
SECTION
I
SPECIFICATIONS:
POWER
PLANT
PA-24-260
Engine
(Lycoming)
*0-540-E
or
**10-540-D
Rated
Horsepower
260
Rated Speed
(rpm)
2700
Bore
(inches)
5.125
Stroke
(inches)
4.375
Displacement
(cubic
inches)
541.5
Compression
Ratio
8.5:1
Dry
Weight
(pounds)
*397/%*402
PERFORMANCE
Take-off
Ground
Run
(ft.)
1090
Take-off
Ground
Run
(ft.)
(short
field)
660
Take-off
Run
over
50
ft.
barrier
1540
Best
Rate
of
Climb
Speed
(MPH)
110
Best
Rate
of
Climb
(ft.
per
min.)
1500
Best
Angle
of
Climb
Speed
(MPH)
85
Service
Ceiling
(ft.)
20,
600
Absolute
Ceiling
(ft.)
22,000
Top
Speed
(MPH)
195
Cruising
Speed
(75%
power
at
sea
level)
(MPH)
173
Optimum
Cruising
Speed
(75%
power
at
7000
ft,)
(MPH)
185
Optimum
Cruising
Speed
(65%
power
at
10800
ft.
(MPH)
178
Stalling
Speed
(flaps
extended)
(MPH)
61
Stalling
Speed
(flaps
retracted)
(MPH)
70
Landing
Ground
Roll
(ft.)
920
Landing
Ground
Roll
(short
field)
(ft.)
650
Landing
Distance
over
50
Ft.barrier
(ft.)
1420
Fuel
Consumption
(2400
RPM
75%
power)
(gph)
14.1
Fuel
Consumption
(2400
RPM
65%
power)
(gph)
12.7
650120
1

SECTION 1 THE PIPER COMANCHE
SPECIFICATIONS: (cont.)
PERFORMANCE
Cruising Range (75% power at 7000 ft.) ( mi.) 1120#
Cruising Range (65% power at 10, 800 ft.) (mi.) 1205#
Cruising Range (55% power at 15,400 ft.) (mi.) 1265#
# B6 gal. available fuel
Published figures are for Standard airplanes flown at gross
weight
under
standard
conditions
at
sea
level
unless
otherwise
stated.,
WEIGHTS
Gross Weight (lbs.) 2900
Empty Weight (Standard) (lbs.) 1700
USEFUL
LOAD
(Standard)
(lbs.)
1200
Empty Weight (Professional 422) (lbs.) 1793
USEFUL LOAD (Professional 422) (1bs.) 1107
FUEL
Fuel
Capacity
(gal.)
(Standard)
60
Fuel
Capacity
(gal.)
(With
Reserve)
90
Unuseable
Fuel
(Inboard
tanks
only)
4
Fuel Aviation Grade (Min. Octane) 91/96
04il
Capacity
(qts.)
12
BAGGAGE
Maximum Baggage (lbs.) 200
Baggage
Space
(cubic
ft.)
20
Baggage Door Size (in.) 20 x 20
2 640901

THE PIPER COMANCHE ) SECTION I
SPECIFICATIONS: {cont.)
DIMENSIONS
Wing Span (ft.) ~ 35.98
Wing Area (sq. ft.) 178
Length (ft.) 24.99
Height (ft.) 7.47
Wing Loading (lbs. per sq. ft.) 16.3
Power Loading (lbs. per HP) 11.15
Propeller Diameter (in.) .
LANDING GEAR
Wheel Base (ft.) 6.55
Wheel Tread (ft.) 9.66
Tire Pressure (psi) Nose 27
Main 42
Tire Size Nose (four ply rating) 600 x 6
Main (six ply rating) 600 x 6
660201 3

SECTION I THE PIPER COMANCHE
12'e"
4 640901

Engine and Propeller
Induction System.
Structures .
Landing Gear .
Control System
Fuel System
Electrical System
SECTION I
DESIGN INFORMATION
Heating and Ventilating System
Instrument Panel.
Vacuum System .
Baggage Compartment .
Seats .
Finish.
640901
.
. 10
10
.13
15
. 16
Y
.18
18
. 18

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