Piper CHEROKEE 180 1972 Benutzerhandbuch

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Piper Air,rc:sft CorpQration, Vero .Beach, Flqrid ,a

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761 513

720.615

CHEROKEE 180 SECTION I

SECTION I

SPECIFI_CATIQNS.

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)

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

25 °flap) (ft)

Best Rate of Climb Speed (mph)

Rate of Climb (ft per min)

Service Ceiling (ft)

Absolute Ceiling (ft)

Top Speed (mph)·

Optimum Cruise Speed (TAS) (75% power,

optimum altitude, leaned to best power) (mph)

Cruising Range (75% power, optimum altitude

leaned to best economy, no reserves or climb

allowance) (mi)

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

leaned to best economy, no reserves or climb

allowance (mi)

Stalling Speed CAS (flaps down) (mph) .

Stalling Speed CAS (flaps up) (mph) ' ...

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

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

720

1625

8f .

725

14,150

16,500

148

141

686

706

635*

1185*

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

distance versus density altitude chart.

SPECIFICATIONS (cont.)

WEIGHTS

Gross Weight (lbs)

Empty Weight (Standard) (lbs)

USEFUL LOAD (Standard) (lbs)

POWER PLANT

Engine (Lycoming)

Rated Horsepower ·

Rated Speed (rpm)

Bore (in.)

Stroke (in.)

Displacement (cu in.)

Compression Ratio

Dry Weight (lbs)

Propeller

FUEL AND OIL

Fuel Capacity (U.S. gal) U.sable

Oil Caracity (qts)

Fue_l,Aviation Grade (min octane)

BAGGAGE

Maximum Baggage (lbs)

Baggage Space (cu ft)

Baggage Door Size (in.)

* Weight varies with each aircraft

CHEROKEE '180

2450

1384*

1066*

O-360-A4A

180

2700

5.125

4.375

361.0

8.5 :l

285

76EM8S5-0-60

100/130

200

20 X 22

C:HEROKEE-180

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l) SPECIFICATIONS (cont.)

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DIMENSIONS

Wing Span (ft)

Wing Area (sq ft)

Wing Loading (lbs per sq ft)

Length (ft) _

Height (ft)

Power Loading (lbs per hp)

LANDING GEAR

Wheel Base (ft)

Wheel Tread (ft)

Tire Pressure (psi)

Tire Size

Nose

Main

Nose (4 ply rating)

Main (4 ply rating)

SECTION:1•

170

14.4

24.0

7.8

13.6

6.7

10 .

6.00 X 6 ; .

6.00 X 6

SECTION I

+-----12' 10.SO"---

30"

CHEROKEE 180 .

.-.------------32' 2.50"-------- - --

t--'------ - 24' 00"-------~

[ -----i 7' 9.60"

----o,r-1--....:::::::C:o:·-~ =-~ J =[~_J~~-__1STWAT~IC~GR~OIIN~D~llN!.'--E_ __ J

CHEROKEE·l80 SECTIONll

SECTION II

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. A heater 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 a spar 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.

SECTION II CHEROKEE 180

The wing airfoil section is a laminar flow type, NACA6Sz-415 with

the maximum thickness about 40% aft of the leading edge. This permits

the main spar carry-through structure to be located under the rear ·seat

providing unobstructed cabin floor space ahead of the rear seat.

LANDING GEAR

The three landing gears use a Cleveland 6.00 x 6 wheel, the main

wheels being provided with Cleveland single disc hydraulic brake

assemblies, No. 30-55. All wheels use 6.00 x 6 four ply tires with tubes.

The nose gear is steerable through a 44 degree arc by use of the

rudder pedals. A spring device is incorporated in the rudder pedal

torque tube assembly to aid in rudder ·centering and to provide rudder

trim . The nose gear steering mechanism also incorporates a hydraulic

shimmy dampener. ·

The three struts are of the air-oil type, with the normal extension

being 3.25 inches for the nose gear and 4.50 inches for the main gear.

The standard brake system for the Cherokee consists of a hand

lever and master cylinder which is located below and behind the left

center of the instrument sub~panel. The brake fluid reservoir is installed

on the top left front face of the firewall. The parking brake is

incorporated in the mas~er cylinder and is actuated by pulling back on

the brake lever, depressing the knob attached to the handle and

releasing the brake lever. To release the parking brake, pull back on the

lever to disengage the catch mechanism and allow the handle to swing

forward.

Optional toe brakes are .available to supplement the standard hand

lever and parking brake system.

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CHEROKEE180 SECTI0-1\ffl

CONTROL SYSTEMS

Dual controls are provided .as standard equipment with a cable

system used between the controls and the surfaces. The horizontal tail

is of the Flying Tail type (stabilator), with a trim tab mounted on the

trailing edge of the stabilator to reduce the control system forces. This

tab is actuated by a control wheel on the floor between the front seats.

The stabilator provides extra stability and controllab ility with less size,

drag and weight than conventional tail surfaces. The ailerons are

provided with a differential action which tends to reduce adverse yaw

in turning maneuvers, and which also reduces the amount of

coordination required in normal turns . A rudder trim adjustment is

mounted on the right side of the pedestal below the throttle quadrant

and permits directional tri.qi as needed in flight.

The flaps are manually operated , balanced for light operating

forces and spring-loaded to return to the up position . A past~center lock

incorporated in the actuating linkage holds the flap when it is in the up

position so that it may be used as astep on the right side. The flap will

not support a step load except when in the full up position, so it must

be completely retracted when used as a step . The flaps have three

extended positions: 10, 25 and 40 degrees .

FUEL SYSTEM

Fuel is stored in two twenty-five gallon (24 gal. usable)· tanks

which are secured to the leading edge structure of each wing by screws

and nut plates. This ·allows easy removal for service or inspection .

The fuel selector control is located on th e left side-panel, forward

of the pilot's seat . The button on the selector must be depressed and

held while the handle is moved to the OFF position. The button

releases automatically when the handle is moved back into the ON

position.

An auxiliary electric fuel pump is provided in case of failure of the

engine driven pump . The electric pump should be on for all take-offs

and landings, and when switching tanks . The pu_mp switch is located in

the switch panel above the throttle quadrant.

CHEROKEE 180 SECTION JI

Each tank has an individual quick drain loacated at the bottom,

inboard rear corner, and should be drained to check for water before

each flight. The fuel strainer, which is also equipped with a quick drain,

is located on the front lower left corner of the firewall. This strainer

should be drained regularly to check .for water or sediment

accumulation. To drain the lines from the tanks. the tank selector valve

must be switched to each tank in turn, with the electric pump on, and

the gascolator drain valve opened.

Fuel quantity and. pressure are indicated on gauges located m a

cluster on the left side of the instrument panel.

ELECTRICAL SYSTEM

The electrical system includes a 12 volt 60 amp alternator, battery,

voltage regulator, overvoltage relay and master switch relay. The

battery is mounted in a stainless steel box immediately aft of the

baggage compartment. The regulator and overvoltage relay are located

on the forward left side.of the fuselage behind the instrumenfl>anel.

Electrical switches are located on the right center instrument panel,

andthe circuit breakers are located on the lower right instrument panel.

A rheostat-switch on the left side of the switch panel controls the

navigation lights and the dome instrument light. It also dims the dome

light. The similar switch on the right side controls and dims the panel

lights.

Circuit Breaker Pone I

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