Piper COMANCHE 260 Benutzerhandbuch

the

LOBFRLLE

()

Owner’s

Handbook

Piper

Aircraft

Corporation,

Lock

Haven,

Pa.

U.S.

Additional

copies

this

manual

may

purchased

writing

the

SERVICE

SPARES

DIVISION,

PIPER

AIRCRAFT

CORPORATION,

Lock

Haven,

Pennsylvania,

17745,

U.S.A.

Published

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

SPECIFICATIONS:

POWER

PLANT

PA-24-260

Engine

(Lycoming)

*0-540-E

**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

ft.

barrier

1540

Best

Rate

Climb

Speed

(MPH)

110

Best

Rate

Climb

(ft.

per

min.)

1500

Best

Angle

Climb

Speed

(MPH)

Service

Ceiling

(ft.)

20,

600

Absolute

Ceiling

(ft.)

22,000

Top

Speed

(MPH)

195

Cruising

Speed

(75%

power

sea

level)

(MPH)

173

Optimum

Cruising

Speed

(75%

power

7000

ft,)

(MPH)

185

Optimum

Cruising

Speed

(65%

power

10800

ft.

(MPH)

178

Stalling

Speed

(flaps

extended)

(MPH)

Stalling

Speed

(flaps

retracted)

(MPH)

Landing

Ground

Roll

(ft.)

920

Landing

Ground

Roll

(short

field)

(ft.)

650

Landing

Distance

over

Ft.barrier

(ft.)

1420

Fuel

Consumption

(2400

RPM

75%

power)

(gph)

14.1

Fuel

Consumption

(2400

RPM

65%

power)

(gph)

12.7

650120

SECTION

THE

PIPER

COMANCHE

SPECIFICATIONS:

(cont.)

PERFORMANCE

Cruising

Range

(75%

power

7000

ft.)

(

mi.)

1120#

Cruising

Range

(65%

power

10,

800

ft.)

(mi.)

1205#

Cruising

Range

(55%

power

15,400

ft.)

(mi.)

1265#

gal.

available

fuel

Published

figures

are

for

Standard

airplanes

flown

gross

weight

under

standard

conditions

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)

Fuel

Capacity

(gal.)

(With

Reserve)

Unuseable

Fuel

(Inboard

tanks

only)

Fuel

Aviation

Grade

(Min.

Octane)

91/96

04il

Capacity

(qts.)

BAGGAGE

Maximum

Baggage

(lbs.)

200

Baggage

Space

(cubic

ft.)

Baggage

Door

Size

(in.)

640901

THE

PIPER

COMANCHE

)

SECTION

SPECIFICATIONS:

{cont.)

DIMENSIONS

Wing

Span

(ft.)

35.98

Wing

Area

(sq.

ft.)

178

Length

(ft.)

24.99

Height

(ft.)

7.47

Wing

(lbs.

per

sq.

ft.)

16.3

Power

(lbs.

per

HP)

11.15

Propeller

Diameter

(in.)

LANDING

GEAR

Wheel

Base

(ft.)

6.55

Wheel

Tread

(ft.)

9.66

Tire

Pressure

(psi)

Nose

Main

Tire

Size

Nose

(four

ply

rating)

600

Main

(six

ply

rating) 600

660201

SECTION

THE

PIPER

COMANCHE

12'e"

640901

Engine

and

Propeller

Induction

System.

Structures

Landing

Gear

Control

System

Fuel

System

Electrical

System

SECTION

DESIGN

INFORMATION

Heating

and

Ventilating

System

Instrument

Panel.

Vacuum

System

Baggage

Compartment

Seats

Finish.

640901

.13

.18

THE

PIPER

COMANCHE

SECTION

DESIGN

INFORMATION

ENGINE

AND

PROPELLER

The

Comanche

260

powered

Lycoming

0-540-E,

carburetor

induction

engine

Lycoming

10-540-D,

fuel

injection

engine.

Both

engines

are

rated

260

2700

RPM,

with

compression

ratio

8,5to

and

require91

/96

minlmum

octane

aviation

fuel.

The

six

cylinder,

direct

drive

engines

are

equipped

with

geared

starter,

volt

ampere

alternator,

carburetor

fuel

injector,

vacuum

pump,

dia-

phragm

fuel

pump

and

shielded

ignition

system.

Engine

mountis

steeltubing

construction

and

incorporate

vibration

absorbing

dynafocal

mounts.

The

allaluminum

engine

cowl,

cantilever

structure

attached

the

firewall.

Side

panels

are

hinged

for

quick

access

the

engine

compartment.

The

exhaust

system

consists

dual

exhaust

stacks

and

mufflers

with

the

exhaust

gases being

directed

over-board

the

bottom

rear

the

cowling,

each

side

the

nose

gear.

Heat

for

the

cabin

interior

and

defrosting

taken

from

the

left

muffler

shroud.

efficient

aluminum

oil

cooler

mounted

the

left

front

engine

baffle.

Engine

oil

drainage

accomplished

quick

drain

installed

the

right

side

the

engine

sump.

The

propeller

the

Comanche

Hartzell

HC-

C2YK-1A/8467-7R

constant-

640901

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