Piper CHEROKEE 180 Benutzerhandbuch

CHEROKEE 180

PA-28-180

owner's Handbook

Piper Aircraft Corporation, Vero Beach, Florida

U.5. A.

NOTICE

THIS HANDBOOK IS NOT DESIGNED, NOR CAN ANY

HANDBOOK SERVE, AS A SUBSTITUTE FOR ADEQÚATE AND

COMPETENT FLIGHT INSTRÚCTION, OR KNOWLEDGE OF THE

CURRENT AIRWORTHINESS DIRECTIVES, THE APPLICABLE

FEDERAL AIR REGULATIONS, AND ADVISORY CIRCULARS. IT

IS NOT INTENDED TO «BE A GUIDE OF BASIC FLIGHT

INSTRUCTION, NOR A TRAINING MANUAL.

THE HANDBOOK IS DESIGNED:

1. TO HELP YOU OPERATE YOUR CHEROKEE WITH

SAFETY AND CONFIDENCE.

2. TO MORE FULLY ACQUAINT YOU WITH THE BASIC

PERFORMANCE AND HANDLING CHARACTERISTICS

OF THE AIRPLANE.

3. TO MORE FULLY EXPLAIN YOUR CHEROKEE'S

OPERATION THAN IS PERMISSIBLE TO SET FORTH IN

TI-iE AIRPLANE FLIGHT MANUAL.

IF THERE IS ANY INCONSIS'i'ENCY BETWEEN THIS

HANDBOOK AND THE AIRPLANE PLIGHT MANUAL APPROVED

BY THE F.A.A., THE FLIGHT MANUAL SHALL GOVERN.

Revised text and illustrations shall be indicated by a

black vertical lirm in the margin opposite the change.

Additional copies of this manual, Part No. 761 513,

may be obtained from your Piper Dealer.

Published by

PUBLICATIONS DEPARTMENT

Piper Aircraft Corporation

761 513

Issued: June 1972

Revised: January 1973

SECTION 1

SPECIFICATIONS

Performance .................... .......... 1

Weights ............ ...... ......... 2

PowerPlant.................... ......... 2

FuelandOil ................... ........... 2

Baggage ................... ... ......... 2

Dimensions ................................ 3

LandingGear............. .. ... ......... 3

CHEROKEE 180 SECTION I

SECTION I

SPECIFICATIONS

PERFORMANCE

Performance figures are for airplanes equipped for cross-country

transportation and flown at gross weight under standard conditions at

sea level or stated altitude. Any changes in equipment may result in

changes in performance.

Take-off Ground Run (S.L. Std., maximum effort, 25 °

flap) (ft) 720

Take-off over 50-ft Barrier S.L. Std., (maximum effort,

25°flap) (ft) 1625

Best Rate of Climb Speed (mph) 85

Rate of Climb (ft per min) 725

Service Ceiling (ft) 14,150

Absolute Ceiling (ft) 16,500

Top Speed (mph) 148

Optimum Cruise Speed (TAS) (75% power,

optimum altitude, leaned to best power) (mph) 141

Cruising Range (75% power, optimum altitude

leaned to best economy, no reserves or climb

allowance) (mi) 686

Optimum Cruising Range (55% power, 10,000 ft,

leaned to best economy, no reserves or climb

allowance (mi) 706

Stalling Speed CAS (flaps down) (mph) 61

-Stalling Speed CAS (flaps up) (mph) 68

Landing Roll S.L. Std., (flaps down) (ft) 635*

Landing Roll over 50-ft Barrier S.L. Std., (ft) 1185*

*This value applies only for the conditions indicated on the landing

distance versus density altitude chart.

761 513 1

720615

SECTION ICHEROKEE 180

SPECIFICATIONS (cont.)

WEIGHTS

Gross Weight (lbs) 2450

Empty Weight (Standard) (lbs) 1384*

USEFUL LOAD (Standard) (lbs) 1066*

POWER PLANT

Engine (Lycoming) O-360-A4A

Rated Horsepower 180

Rated Speed (rpm) 2700

Bore (in.) 5.125

Stroke (in.) 4.375

Displacement (cu in.) 361.0

Compression Ratio 8.5:1

Dry Weight (lbs) 285

Propeller 76EM8S5-0-60

FUEL AND OIL

Fuel Capacity (U.S. gal) Usable 48

Oil Capacity (qts) 8

Fuel, Aviation Grade (min octane) 100/130

BAGGAGE

Maximum Baggage (lbs) 200

Baggage Space (cu ft) 24

Baggage Door Size (in.) 20 x22

*Weight varies with each aircraft

2761513

720615

CHEROKEE 180 SECTION I

SPECIFICATIONS (cont.)

DIMENSIONS

Wing Span (ft) 32

Wing Area (sq ft) 170

Wing Loading (lbs per sq ft) 14.4

Length (ft) 24.0

Height (ft) 7.8

Power Loading (lbs per hp) 13.6

LANDING GEAR

Wheel Base (ft) 6.7

Wheel Tread (ft) 10

Tire Pressure (psi) Nose 24

Main 24

Tire Size Nose (4 ply rating) 6.00 x6

Main (4 ply rating) 6.00 x6

761 513 3

720615

SECTION ICHEROKEE 180

50"

2.50"

10'

-24' 09"

T.ß0"

---8' 8.4"

4761513

720615

SECTION 11

DESIGN INFORMATION

EngineandPropeller ............ .. ......... 5

Structures.......... ..... .... .......... 5

LandingGear ........... ... ............ 6

ControlSystems ......... .... ........ 7

FuelSystem ........ ....... 7

Electrical System . . . ... . . . . .. . .. . . . . . 9

Heating and Ventilating System .... . . . ...... . .. . .13

CabinFeatures .......... . . ........ 13

Optional Equipment .... . . . . . ..... . . . 16

CHEROKEE 180 SECTION 11

SECTION 11

DESIGN INFORMATION

ENGINE AND PROPELLER

The Cherokee 180 is powered by a Lycoming O-360-A4A four

cylinder, direct drive, horizontally opposed engine rated at 180 HP at

2700 RPM. It is furnished with a starter, 60 ampere 12 volt alternator,

shielded ignition, vacuum pump drive, fuel pump, and a dry,

automotive type carburetor air filter.

The exhaust system is of the cross-over type to reduce back

pressure and improve performance, It is made entirely from stainless

steel and is equipped with dual mufflers. Aheater shroud around the

mufflers is provided to supply heat for the cabin and windshield

defrosting.

The Sensenich 76EM8S5-0-60 fixed-pitch propeller is made from a

one-piece alloy forging.

STRUCTURES

All structures are of aluminum alloy construction and are designed

to ultimate load factors well in excess of normal requirements. All

exterior surfaces are primed with etching primer and painted with

acrylic lacquer.

The wings are attached to each side of the fuselage by inserting the

butt ends of the respective main spars into aspar box carry-through

which is an integral part of the fuselage structure, providing in effect a

continuous main spar with splices at each side of the fuselage. There are

also fore and aft attachments at the rear spar and at an auxiliary front

spar.

761 513 5

720615

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