Piper Cherokee 140 airplane Owner's Handbook

Below you will find brief information for Cherokee 140. The Cherokee 140 is a single-engine, four-seat airplane designed for general aviation purposes. It has a fixed-pitch propeller and a Lycoming engine rated at 140 horsepower. The Cherokee 140 is known for its ease of handling and its reliability, making it a popular choice for flight training and personal use.

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O!av

Kieserud

CHEROKEE

I

40 OWNER'S

HANDBOOK

753-584

Olav

K jesecud

CHEROKEE

140

PA.28.l 40

Owner's

Hondbook

Piper

Aircraft Cotporotion,

Vero

Beoch,

FlorUo u.5.

A.

NOTICI]

TIIIS

IIANDI}OOK

IS NO't

DESIGNIiD, NOR CAN

ANY

H^NDDOOK

SERVE,

SUBSTTTUTE

FOR ADEQU^TE coMpETENT FLIGHT

INSTRUCTION, OR KNOWLEDGE OF

^ND

CURRENT AIRWORTHINES§

DIRECTIVES, THE

APPLICABLE

FEDERAL AIR REGULATIONS, AND ADVISORY

CTRCULARS.

IS

NOT INTENDED

TO IIE A

GUIDI' OF

ITASIC

}'LIGHT

INSTRUCTION, NOR

TRAINING MANUAI,.

'l'ilrt il^NDD(x)K ls

Drist(.;Ntil):

I.

IIELID YOU OI'IiRA'I'E YOUR

CHIIROKIiI' WITII

I.'ETY

AND CONIIIDENCE.

2,

TO MORE FULLY yOU WITH THE

BASIC

^CQU^rNT

CHARACTERISTICS

OFTHE AIRPLANE.

3.

TO MORE FULLY EXPLAIN YOUR CHEROKEE'S

OPERÅTION

THAN IS PERMISSIBLE TO

SET FORTH IN

THE AIRPLANE

FLIGHT MANUAL.

IF

THERE

IS

ANY INCONSISTENCY BETIVEEN THIS

HANDBOOK AND

THE AIRPLANE FLIGHT MANUAL

APPROVED

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

GOVERN.

Revised text and illustrations shall be indicated by a black vertical line in the margin opposite the change,

A line opposite the page number will indicate that materi al was relocated.

Additional copies of this manual, Part

No. 753

584, may be obtained from your Piper Dealcr.

Published by

PUB

UCATIONS DEPARTMENT

Piper

Aircraft

Corporation

753

Issu«l:

Febnrary 1964

Revised:

March l. l99l

SECT|ON

SPECIFICATION

FEATURES

Performance

THE

PIPER CHEROKEE

SECTION sEcfloN

SPECIFICATION

FEATURES

PERFORMANCE

The gross

$reighr to 28-20939, o, l95O Pq.rnds ln the following perlårmance chÅrts appll,es ,o

S{rUf

Nos, uleas the airpleqe has been modilled t

Nos,

28-20940 snd llp hsvc bcen llcenircd from the fa

28-2OOOO

Perforrutrcq flgues

Ievel ere for strnderd alrplanes or ståld flhltudc.

Any dcvistldl from

Sta

GRO§S WEIGHTS

Telc-off

Ru (It,)

(flaps

14)

Tetc-off

Di.Btaræ

Over

50 ft.

Obsracle

(fr.)

(fl8ps up)

Best Rate of CUmb Spæd

(hph)

Rrte of CUmD

Absolute

(ft. per

Scrvtce Cetllug

(ft.)

Ceiltng mln.)

Top $ced

(mph)

ClutslnB

Sp€ed (75% power, sea level)

Optlmum Crulstng

Speed pSS potuer,

(mph)

7000

It., mph)

Opttmu$ Grulslng

Renge (55$ wer, sea

15, lsm

820

O0O f7,

OOO r r4t

(r44.)

'l r20 f30

(f23.)

(f33.)

I i r?00

660 r4,3OO

,U.

U* i t39

(r42.)

I tZt 1tU.1

f30

(f33.)

level)

.

100

(102+)

.l

r00

(r02r)

8.4

)

5r5, { hEs.

(r20,

hr8...)

+fO, n frru[ (680, 6 hrs.rr)

)

powrr,

10,

0m ft, )

560

600

7.e s.3

(780..)

(840..)

i

I i

s.o

535 (725.+)

570

(790.r)

'\iltren Fenders Instålled

"With

50 gal.

Resene

Fæl

730I

I 5

SECTION

SPECIFICATION

FEATURES:

(cont)

PERFORMANCE

THE

PIPER CHEROKEE

: lnetruciloul

Pover Crutsltrg

Range

(50%,pqwer, sea level)

Sta[ln-gSpeed (flaps doyn, mFh)

Landlng Roll (flaps down, fr.) aRosri

TErGr{Ts r9 50

2r50

640,1

6.s hrs.

(89s,

I t hrs. ti) d50, 6.5

48s hrs,

(910, t hrs. r.)

53s

WEIGHTS

Gross U,eight (lbq.

)

Empcy Wetght (Standard)

(Ibs.)

USEFUL LOAD (Standard)

(lbs.)

Empcy \Yeighr (AutoFlight)

(lbs.)

UsEFUl, LOAD (Åu.oFligtrr)

(lbs.)

POWER

PI.ANT

EEgtne

L}æomlng

Rated Horsepryer md

Speed

(rpm)

Bore (lo:hes)

Stroke (inches)

Displaæmetrt (cubic incheE)

CompEesslotr Ratib

Dry

Weighr (poutrds)

Oit

Sump Capaqity (qts.

)

Propeller

(Sensentch)

1950

,.180

770

1220

730 o-320-E2A

140 ei

2450

5. r25

3.875

319.8

7:\

272

M74DM

2150 l20l

949 t24l

909 o-x20-E2A

150 at

2700

5, t25

3.875

319.8

7i7

M74DM

"Wirh

50 gal, Resefle

Fuel

650630

THE

PIPER

CHEROKEE

SECTION

SPECIFICATION FEAIURES: (conr)

GROSS

WElerrrs

FUEI.

AND

OIL

Fuel Capaclty (gal.

Fuel

Capacity

)

Srandard

(Sal.)

Reserve

Oil

Capaclty (qts.

)

Fuel Aviation

Gradc (Minimum Octenc)

(Spccified Octane)

(Altanctc

Fuels) r950

2r50

36

50

.50

88 80187

80147

80.187

See pegc

BAGGAGE

Maximum

Baggage

(lbs.)

Baggaæ

Space

(cubic

ft.)

100

,,

200.*.

,'»

DIMENStONS

Wtng

Span

Wing Area

(ft.

)

(sq.

ft.)

trVing

LoadinS

Qbs.

Length

Height

(ft.)

(ft.) per sq.

ft.)

Power Loading

(lbs. per

HP)

30 r60

12.2

23.3

7.3

13.

IANDING

GEAR.

Wheel

Base

(fr.)

Wheel Tread (ft.

)

Tlre kessure (lbs.)

Nose

Main

6.2

10.0

6.2

r0.0

'rtExcept when family seat and sefety belts are lbs. ls permitæd.

installed

340

770527

30 r60 t3,4

23.3

7.3

r4.3

SECTIONI

THE

PIPER CHEROKEE

SECTION

DESIGN

INFORAAAT]ON

9 r0 r2

THE

PIPER

CHEROKEE

SECTION

sEcTtoN il

DESIGN

INFORMATION

ENGINE

AND

PROPELI.ER

The

Lycoming o-IZo.EzA enginc inselled

PA-28-140 is ratcd

"t

27OO rpm..,This cngine has a compression ratio requires 8O/87 ar l4O horsepowcr ar 2450 rpm or

150 horsepower minimum octanc fucl. Rcfcr

in

rhe

Cherokce of

7 to

I

end to

Fuel Rcquiremenrs on page 30 gcared when startcr, using alrcrnarc fuels. The engiae is eguipped with a a

35 ampcre alternator, dual magnctos, vacuum pump drive, a diaphragm-rypc fuel pump and a float carburetor.

Exhaust gases are carried through a system constructed heavy gauge stainless steel which incorporates shroud, to provide cabin heat and carburetor deicing.

a

heater

The propeller used on the PA-28- I40 fixed-pitch aluminum alloy unit. Its diameter is

74 inches with a standard pitch of

60* inches,

All

is a

Sensenich M74DM performance figures are based on the srandard 60* inch pitch propeller.

Cowling on the

Cherokee ts designed to cool the engine in all normal flight conditions, including protracted climb, without the use of cowl flaps or cooling ftanges.

The throttle is lower center of the push-pull type and is located

ir

the of the instrument panel.

A knurled friction lock ls provlded toprevent creepingof the throttle from any desired position.

The mixture control, located in the lower right hand side of the instrument panel,

is

a push-pull control llke the

throttle.

The full rich posirion is obrained when the control is full forward, whil.e the full aft position provides an idle cur-off

*58 lnch plrch

+*When propellers gross weight is when

2150 gross weight is

2I50.

770527

SECTION

THE

PIPER

CHEROKEE for stopping the engine. Intermediate posltlons are used for leåning the mlxture at ahitudes above sea-level,

The carburetor heat control, located to the left of the thronle, provides maximum

With carburetor heat when pul.led to carburetor heat off, all eugine

its

full aft position.

air

passes througtt a highefficiency atlon with dry-type

filter.

Therefore, prolonged ground opercarburetorheat"ON" should be avoided, particularly on unlmproved ftelds as the alr is not flltercd.

STRUCTURES

All structures are of alumlnum alloy conatnrctlon and are deslgned to ultlmate loed factors weU in excess of normal requirement§.

All

exterior surfaces are prtmed with etchlng prlmer and painted wlth acrylic enarnel.

box

The wlngs are attached to each elde serting the butt ends of the of the fuselage respective main spars into by a

Inspar carry through which is an integral part of the fuselage sfructure, provlding. ln effect, a contlnuoua main spar urith spllces at each slde of the fuselage. There are also fore and aft attachments at the

The wing rear spar and at an auxlliary

frmt

epar.

airfoil

section

is a

l,aminar flow type,

NACA

652-4fS wlth the maximum thicknessabout

40% ing edge.

This permlts the main spar aft carrythrough of the treadstructure to be located under the

rear

seat providlng floor space ahead of the rear seat.

unobstructed cabln

TANDING

GEAR

The thtee landing gears use a

Clevelaod

6O0 x

6 wheel' tbe main wheels belng provtded with brake drums and

Cleveland single disc hydraul.ic brake assemblies. The nose wheel and the

67m3r

!.- -. - r.'

I

THE

PIPER

CHEROKEE SECTION II main gear both use

600 x

6 four ply

tires.

All the tires have tubes.

The nose gear is steerable through a

30 degree arc each side of neutral by use of the rr.rdder pedals.

A spring device is lncoraorated in the rudderpedal torque tube assembly to aid in nrdder centering and to provide rudder steering mechanism also lncorporates

trim.

The nose gear

a

hydraulic shimmy dampener.

The oleo struts are of the air -oil type with normal extension being

3.25 inches for the nose gear and 4.50 inches for the main gear under normal static (emptyweigfu of airplane plus and oil)

Ioad.

full fueI

The brakes are actuated by a hand leverand master der, which cylinis located belowand behind the left centerof the instrument sub-panel.

The brake fluid reservoir is installed on the.top

Ieft front face of the

firavall.

The parking brake is incorporated on in the master cylinder and is actuated by pulting back the brake lever, depressirg theknob attached to the left side of the handle and then releasing the brake

lever.

To release theparking brake, puII backon the brakelever to dlsengage the catch mechanism and allow the handle to swing fonrard.

CONTROT sYsTEM

Dual controls cable system used beEween the controls and the surfaces.

The horizontal tab which also acts as a longitudinal control on tail is of the all movable slab type, with an anti

-servo the are provided as standard equipment with a cabin ceiltng"

The stå-bilator provides extra sta-bility than a

and conventi dlfferential

ilrning

mane

trim

tab, actuated by slze, drag, and a weiglt allerons areprovlded with eliminate adverse yaw in the amount of coordlnation

67 103 r

SECTION

THE PIPER

CHEROKEE requtred

The in normal turns.

flaps are manually operated, balanced for light operating forces and spriog loaded to turn to the up position-

A past-center lock incorporated in the actuating linkageholds the flap when

it

step on the cept when

is

in the up position so that

it

may be used as rlght side. The flap

will

not support a step load exin the full up position, so

it

must be completely rea tracted when useda§ a step,

The flaps have threeextended positions, 10,

25 and 40 degrees.

FUEL SYSIEM

Fuel is stored in two twenty-five gallon tanks whlch are secured and nut to the leading edge structure of each wing by screws plates. This allows easy removal for service

or

inspection.

The standard quantity of fuel is

36 gallons for the Cherokee

140.

Toobtain the standard quantity of fuel,

fill

the tanks tothe bottom of the

filler

neck indicator.

An auxiliary electric fuel pump lsprovided of failure of the engine driven pump.

The for use in case electric pump should be on for all take-offs and landings.

The fuel strainer, which is equipped with a quick drain, is located on the front

Iower

left

corner

of the

firewall.

This strainer should be dralned regularly to check for rvater or sediment accumulation.

To drain the lines from the tanks,

650630

THE

PIPER

CHEROKEE

SECTION

II the tank selector valve must be switched to each tank in turn, with the electric pump on, and the gascolatordrainvalve opened.

Each tank has an individual qulck drain located at the bottom, inboard, rear corner.

Fuel quantity and pressure are indicated ongauges located in the engine gauge cluster on the right side of the instrument panel,

ELECTRICAT

SYSTEM

The

Power)

Cherokeeisequippedwith thepiper

F.T.p. (Full

Time

Electrical

System,

ICs 12 volt alternatorprovides electrical power formance at all engine speeds and results in improved perfor radlo and electrical equipment and longerbattery life.

In additionto a 25 ampere-hour thealternator, the electrical system includes baEery, a voltage regulator and a master switch

relay.

baggage

The battery compartment and

floor.

relay are

Access for mounted beneath service or the inspection is obtained by raising the hinged baggage compartment panel. The battery box is designed to accommodate floor a

Larger capacity battery for extreme cold weather operation.

Electrical switches, fuses and fuse the spares lower are located on

left

side of the instrument panel.

Standard electrical acce s

sories, in additiontothose already

Iisted, include a starter, stall warning indicator, cigar lighter and ammeter. gation

lights,

Mvi-

anti-collision light, landing

Iight, instrumenr lighting and a cabin dome light are offered as optional acces-

6s0630

SECTION tr

THE

PIPER

CHEROKEE sorles.

Circult provlslons are made to handle optlonal communlcatlons and navlgational equipment.

In conventlonal generator systems, the ammeter indicates battery discharge.

In the Piper FullTime Powerelectrlcal system, the ammeter displays the load in amperes placed on the system at any given time.

Wtth all electricalequlpment except the master switch in the

"OFF" positionr the ammeter dicate the amount ofcharging current demandedby the

will

inbattery.

This amount

will

vary and depends on the percentage of full clørge on the battery charged, the at tåe

time.

When the banery becomes current dlsplaeed on the ammeter

will

reduce to a mlnimum value of about two amperes.

As each unit of electrical equlpment ls swltched on the amount of current ir draws will be shown on the ammeter.

The maximum cqltlnuous load for nlght flight with all equipment on amperes, Thts

is

approximately thirty thlrty ampere s plus approximately two amperes for the futly charged flight condittoos.

batterywill appear conriouously under these

Because matnteoance

of

the mechanical simpliclty

of

the alternator, should prove to be a minor factor as compared to prevlous systems.

Should service be local

Piper dealer.

requlred, contact your

HEATING

AND

VENTII.ATING

SYSTEM

Heat vided trols for the cabln lnterlor and the defroster system is proby a heater muff attached fof these systems are locatedon the lower right hand side of the instrument

to

the exbaust system.

Conpanel.

A third confrol in this area regulates a large fresh near the air vent located on the left hand stde of the cabin pllot's feet.

In addition, two side vents are provided one at each seat location. Th"y may be tndependentlyregulated as desired by the seat occupant.

6s0630

THE

PIPER

CHEROKEE

glev

Kleserud

SECTION

II

Frcrh

Alr

ConEol

D.Iro.rrt codlrcl

!. lbrtlr

@lsirrl a.

ILlro.alr

AJt Omet l.

Frc.b

Alr lnler

6 tG.llr [rEt

SECTION

THE

PIPER

CHEROKEE

CABIN

FEATURES the

The instrument

Panel commodate of the

Cherokee is deslgned to acthe customary advanced fllght instruments ard normally requlred power plant in§truments.

Ttrc all

Artificlal

Horlzorl

Directiooal

Gyro and ttre

Turn and Bank instruments are vacuum operated through use on the of a vacuum pump installed englne.

A natural separation of the flight group and rhe power group

ls

provlded by placing the communicattons and radio navigational equipment tn the center of the panel.

The front seats are adiustable fore and aft for pllot comfort and ease of enrry and avallabl,e whlch

exlt.

A famlly provldes two additional seat installation ls seats.

Each family seat ls capable of carrylng a full size adult which glves the Ctrerokee

140, 4-place capabilttY.

1.

Compass

2.

Airspeed lndicator

3.

Directional Gyro Indicator

4.

Gyro Horizon Indicator

5.

Radio ADF

6.

Radio VHF

7.

Tachometer

FAMILY

SEATS

8,

Vacuum Gauge

9.

Instrument Cluster

10.

Turn and Bank

Indicator

11.

Clock

12.

Stall Warning Light

13.

Altimeter

14.

Rate of Climb Indicator t2

6s0630

THE

PIPER

CHEROKEE

SECTION

II a?-

650630

L2a

.

-

'

,

SECTION

ttl

OPERATING

INSTRUCTTONS

Prcflight

Starting

W:um-up

GroundCheck

Takc-off

Climb.

Stalls

.

Cnrfuing

Marreuvcrr

Approechandlanding

Mooring

WeightandBalancc

...

.....14

..I5

.. ..

...

.....r7

;

,,,f9

. . .

-

. . .

19a

.. .l9t

730tt5

THE PIPER

CHEROKEE

SECTION

TII

sEcTloN

OPERATING INSTRUCTIONS

PREFLIGHT

The airplane should be given a thorough visual inspection

prior

to each

flight.

Particular attention should be given to

*re followirg items in the illustration belov:

I. a.

Master switch

"ON. "

b.

Check fuel quantlty indlcators

(two tanks)

c.

Master switch and ignition

"OFF.

a.

Check

for

o<ternal damage, operational lnterference

66t20t

SECTION

III

THE

PIPER

CHEROKEE of control surfaces or hiqges.

b.

Insure that wings and conrrol surfaces

are

free of snow, ice

3. or frost,

a.

Visually check fuel supply, secure caps.

b.

Drain fuel tank sumps.

c.

Check that fuel system vents are open.

a.

Check landing gear shock struts for proper inflation.

b.

Check tires for cuts, wear and proper inflatlon.

c.

Drain fuel rystem sump

(left side of eircraft)

a.

[nspect windshteld for cleanliness.

b.

Check the propeller and spinnet

for

defects or nicks.

c,

Check for obvious fuel or oil leaks.

d.

Check

oil

level, 8 quarts maximum. (Insure dipstick is properly seated.)

e,

Inspect cowling and inspection covers

for

security

f.

Check nose wheel tire for inflatlon, wear,

g.

Check nose wheel shock

strut for

proper inflation.

a,

Stow tow bar and control locks,

if

used,

b.

Check baggage for proper storage and security.

c.

Close and secure

the

baggage compartment door.

. a

.

Upon entering aircraft ascertain that all primary flight controls operate properly,

b.

Close and secure the cabin door.

c.

Check that required papers are

in

order and

in

the aircraft.

d,

Fastcn seat belts and shouldcr harncss.

STARTING ENGINE

After completlon of the preflight inspection:

.

Lock the wheel brakes.

2.

Set the carburetor heat control

in

the

full

"COLD" position.

3.

Select the desired tank with the fuel valve.

4.

Move the mixture to the

full

"RICH" positton.

5.

Open the throttle

I/8

t/4

inch.

6.

Turn the electric fuel pump "ON. "

14

7t01t5

THE

PIPER

CHEROKEE

SECTION

III

In cold weather (below 40 degrees

F.) prime rhe engine with onetothree full strokes of the priming pump. cold, stårting

If extremely

will

be aided by pulling the propeller through by hand the

(switch

"OFF') four ro five revolutions.

If

rhe temperature is above 40 degrees the engine may be primed by rhree or four short quick strokes of the throttle.

After priming, turn the electric master sv/itch on, engage starter and allow the engine to turn approximately one full revolution, then turn the ignition swltch to the position.

"Left" magneto

When

Check the the engine is firing evenly, turn the magneto switch to the "Both" position and advance rhe thrortle

ro

800 RpM,

oil

pressure gauge

for a

pressure indication.

If oil

pressure

is

not indicated within

thirty

seconds, stop the engine and determine the trouble.

If

the engine

fails to

start

at

the

first

attempt, another attempt should be made wirhout possible thar the engine switch

off,

open approximately the

priming. is

overprimed,

Turn the magneto

throttle

If

this fails,

ir

is slowly, and rorate ten revolutions with the

the

engine

starrer.

Reprime the engine with one half the amounr used turn the magneto switch to "Left, procedure.

in

the

inirial

artempt,

"

and repear the starting

If

the engine again fails

to start,

refer to the

"Lycoming

OperatingHandbook,

Section

VII,

Engine

Troubles. "

WARM.UP

As soon as the engine checked. starts, the

oil

pressure should be

If

no pressure

is

indicated within

rhirry

seconds, stop the engine and determlne the trouble,

In cold weather it

will

take a few seconds Ionger to get an oil pressure indication.

Warm-up the engine ar

800 ro

I200

RPM.

pleted, providing that the rhrottle may be opened fully wirhout back

Take-off may be made as soon as ground check

firing or

skipping, and wirhout reduction

in is

comengine oil pres§ure, l5

SECTION

III

THE

PIPER CHEROKEE

GROUND

CHECK

Check the magnetos at 2o0o RPM by switching then back from Both to Right to

Both before switching to

Left. Differential drop should not exceed 50 RPM while the total drop on either magneto should not exceed 175 RPM.

Check vacuum gauge, indicator should read

t.1"

Hg at

2oo0

RPM.

Check both the oil temperature and pr6sure. Thc temperature may be low for some time if the engine isbeingrun forthefirst timeof the day, but as long as the pressure is within limits the engine is ready for take-off.

Carburctor heat should also be checked prior to take'off to be sure that the control is operating properly and to clcar any icc which may have formed during taxiing. Avoid prolonged ground operation with carburetor heat ON as the air is unfiltered.

Mixture should be set full rich, except a minimum amornt of leaning is permitted for smooth enginc operation when taking off at high elevation.

TAKE.OFF

Just before take-off the

l.

Controls free

Flaps "UP"

Tab set

Mixture

"RICH" following items should be checkcd:

Elecuic fuel pump "ON"

Engine gauges normal

Carburetor heat

"OFF"

Dcor latched

lo.

Altimeter set

11.

Fasten belts/harness

Fucl on proper tank

The take-off technique is conventional should be set slighdy for the

Cherokee. The tab aft of neutrd, with the exect setting determined by the loading of the aircraft.

Allow the airplane to accelerate to

50 to

60 miles per hour, then ease back on the wheel enough to let the airplane raising fly itself off the ground. Premature raising of the nose, or

it

to an excessive angle, will result in a delayed take-off, After take-off let the aircraft accelerate

to

the desired climb specd by lowering the nose slightly.

770527

THE

PIPER

CHEROKEE

SECTION

III

Shon Field, Obstacle

Clearance

Lower the flaps to

(second notch), accelerere to

55-60 miles per hour and ease back on the control wheel to roate.

After breaking ground, accelerate to the best angle of climb specd, 74 miles per hour.

Slowly retrect the flaps when the obstacle has been cleared and continue climb at 85 miles per hour,

Shon Field, No

Obstacles:

Lower the flaps to

(second notch) accelerate to 55{0 miles per hour.

Ease back on the control wheel to rotate and accelerate to best rate of clirnb speed,

85 miJes per hour. Slowly rctract the fleps while climbing out.

Soft Field, No Obstacle;

Lower the flaps to

25 o

(second notch), accelerate aircraft and pull nose gear from the ground assoon as possible, lift offat lowest possible airspccd. Accclcrate just above the ground to best race of climb speed,

85 miles per hour. Climb out white slowly retracting the flaps.

Soft Field, Obstacle

Clearance: gcar

Lowcr flaps to

25 o

(second notch), accelerate aircraft, pull nose off as soon as possbile and

lift

off at lowest possiblc airspced.

Accclerate jusr above the ground to best angle of climb speed, 74 miles per hour to climb past obstaclc clearance height, continue climb whilc accelcrating to best rate of climb spced, 85 miles per hour and slowly retract the flaps,

CLIMB

The best rate of cli.mb at gross weight

will

be obtained at miles per hour. The best angle of climb may be obtained at miles per

hour.

At lighter rhan gross weight these speeds are reduced somewhar. For climbing enroute a speed

of

l0O miles per hour ls recommended.

This ward speed and lncreased wlll producebetter forvlslbtlity over the nose durtng the climb.

30ll

5 t7

SECTION

III

THE

PIPER CHEROKEE

STALTS stalt characteristics of tfie cherokee are conventional. Visual stall warning is provided by a red light located on the left side of the instruÅnt panel which is turned on automatically betwcen

5- and

1O miles per hour above stall spced. Gross weight stalling speed with.power

off and full flaps is 52 miles pcr hour at 1950 pounds and 54 miles per hour at 215o pounds.

With flaps up this sPeed is increased 9 miles per hour.

lntentional sPins are prohibited in the normal

For approved maneuver§ and entry speeds refer category airplane' to the Flight Manual'

CRUISING

The cnrising speed of thå Chetokee is determincd by many factos including powei setdng, altitude, temPcraturg loading, and equipment installed on the airPlane.

The normal cruising power engine. Tnre airspeedr, is

75% of the rated horsepower-of the wi,ict may be obtained at

*eriors altitudes and polwer rettings, can be determined from the chans in "Section

IV" of this handbook.

lead

Usc leaned

of

consumption the amount

the

mixture control deiosits wfren thc

"it"-it. in

cmising significantly, especially at higher flight reduces fuel dtiodes, and rcduces fuels are used. The mixture should whcn

75o/o power or less is being used,

If

be any doubt exists-T-t9 of power being used, the mixture should be

RICH position in the FULL for all opirations.

Æways enrich the mixture before

The decreases engine are severe, slowly and do not cruisc only

,se of

efficiency. carburetor heat during cruising flight unles icing conditions in the carburetor with thc heat on. Apply full carbuetor heat for a few seconds at intervals determined by icing seventy,

In- order to keep the airplane in best lateral trim during cruising flight, the fuel should be used elternately from each main tank'

It

is rJommended that one main tank be used for one hour after take.off; the other main tank used until nearly exhausted, then return to the first main tank.

770527

tl.l:.v

Kiesersd

THE

PIPER

CHEROKEE

MANEUVERS sEcTroN llr up

The alrpl,ane ls approved for certain aerobatic måneuvers to a gross welght of

1950

lbs.,

theapprovedweight and center of provided gravity

it

is loaded within

limits.

(See Airplane

Fli.ght

Manual) The elghts and chandelles.

maneuvers are spins, steep turns, lazy

APPROACH

AND

TANDING

The airplane should be trlmmed to an approach speed of about 85 mlles per hour with flaps up.

The flaps can be lowered at speeds up to

ll5

miles per hour, if deslred, and lf approach speed is reduced

3 miles per hour for each additlonal notch of

flap.

Carburetor heat should not be applled unless there ls an indicatlonof carburetor

iclng

slnce the use of carburetor heat causes a reduction go-around. ln power which may be critical in case of

Full throttle operationwlth heaton is likelytocause a detonation.

the

The amount cording of flap used during landings and the speed of aircraft at contact with

the

runway should be varied acto the landlng surface and existing condltions, both windwise and loadwise.

It is generally good practlce tocontact the grotrnd at the minimum possible safe speed consistent with existing conditlons.

Norrnalln the best technlque speedand approach for short and slow landings is to use full flap andenough powertomaintain thedesired fltght path.

Mixture should

air-

befullrich, fuel on the fullest tank, carburetor heat off, and electric fuel pump on.

Reduce the speed during the flareoutand contact the ground close to the stalling speed

(55to65 MPIfl. After gtound contact hold the nose wheel off as long as possible. As the airplane slols down, drop tlre nose and apply the brakes.

There wlll be less chance of skidding the tires lf the flaps are retracted before

7301

I s r9

SECTION UI

THE

PIPER CHEROKEE applying the brakes. Braking ls mosteffectivewhen back pressure isapplted tothe control wheel, pufttngmost of the atrcraft wetght

Iarly on the maln wheels.

ln

strong cross-winds,

In high wlnd condttlons,

Particu-

lt

may be desirable to approach the ground at htgher than normal speeds with partial or no flaps.

To stop the engine after landing, pull the mixure control full back to idlc crt-off. trYhen dternatc fuels arc used, the engine should be run up to

12OO

RPM for one minute prior to shutdown to clesn out any unburned fuel. Æter the engine stops turn magneto and mætcr switches off.

MOORING

The Cherokee should be moved on ttre ground with the aid of the nose wheel tourhar tn the baggage providedwith each plane and secured compartment. Tie downs may be secutedto rings provided under each wing, and to lhe tall skid,

The aileron and stabtlator controls should be secured by looping the safety belt through the control wheel and pulling lt tight.

The rudder is held in positlon by

lts

connections to the nose wheel steering, and normally does not have to be secured. The flaps are locked when in the full up positlon, and should be left retracted.

WEIGHT

AND

BAIANCE

It is the responsibility of the owner and pilot to determine that the airplane remains within theallowable weight v§ certer of gravity envelopewhllein flight.

For weight and balance data see the Airplane Flight Manual and

Weiglrt and

Balance

Form supplied with each alrplane.

L9a 770527

1 sEcTroN

PERFORMANCE

CHARTS

Takeoff

DistancevsDensityAltinrde

.. ...

,

Rate of

Climb vs

Dcnsity

Altitude

. . .

.

TrucAirspccdvsDensityAltitude(l9Solbsgrosswt)

, . .

,.

Altitudc

AltitudeConversionChart.

.

23a-

.

23b

,,.....24

...,.,.25

,

25a

.

2Jb

.,..,..26

7rotts

THE

PIPER

CHEROKEE

SECTIONIV

PIPER

CHEROKEE

PA-29-140

[AME.@FF

DOSIIANGE vs"llt

ALIIITUDE_]

I,*lrrL"']

ns.

§r0ss mf,rf

trtrttr

rlllr

0f clmr ri0uE

,000

II. It

t I I lll

I ivl

,l lo

,000

^-0

8000

E tmo e

3C00 a e

2000 t

I

§

§1

I t000

t,

I

500

00t 1500 2000 1500 3000 tlol lt0l

TllE

-

oft

l[§nrct

ttET

730r15

SECTION

THE

PIPER

CHEROKEE

14000 ttll

H rzooo f

,.t

E roooo tr z.

f sooo

UJ ct

6000

16000

PIPER

CHEROKEE

PA-28-140 tttttr

RATE OF CLIMI

DENSITY ALTITI

I l95O LBS. GROSS

-

2150 LBS

GROSS ttl

4000

2000 o

\ loo 200 too.loo

500

6()0 700 800 90() looo

RATE OF

CLIMB-FEET

PER MINUTE

730rr5

r2000 toooo

80()0

6000

4000

200() o

THE

PIPER

CHEROKEE

PIPER

CHEROKEE

PA-29-140

TRUE

AIRSPEED

DENSITY ALTITUDE

SECTION IV

FULL

THROTTLE

730llt

SECTION

THE PIPER

CHEROKEE t4000

12000

F trJ

H pooo l o

E

Eooo

! tl.t

a eooo

4000

2000 o

I

L:q

el

ie/

I I

I

loo ilo 120 130 t40 150

t60 rRUE

AIRSPEEO, M.PH.

65(b30

PIPER

CHEROKEE

PA-28-t40 tltttll

TRUE

AIRSPEED

DENSITY

ALT]TUDE

---

2I5O

LB§

GROS§ rlltt w1

}(

SECTIONTV

THE

PIPER

CHEROKEE

t4000

L-

PIPER

CHEROKEE

PA-28-140

tttttrt

RANGE

OENSITY ALTITUDE

1950

L8S.

GROSS rlrt

GAL.FUEL

(slondod)

-

GAL.FUEL

(rith reserve)_

12000 o

F l!

- roooo b eooo

f;

eooo

'åe aQo

ål

I I ilt

Ht

tt/l-/

I ilt lt i

ti

tl t

4000

2000

I

I I t I

)

500 600 700 eoo 900 looo

llo0

RANGE.

MILES

7rott5

23a

SECTION

IV

T'HE

PIPER

CHEROKEE

PIPER

CHEROKEE

PA-29-140

t4000 t2000

F lrJ

H roooo f o

5

sooo

I

6000

4000

2000 o

36 GAL.

FUEL(shndordl

-

GAL. FUEL

(wilh rcscrvel

åe o

;€ a

I iS to

-A

t:

500 600 700 800 900 rooo

iloo

RA^IGE, MILES

730115

THE

PIPER

CHEROKEE

SECTION

-o

PIPER

CHEROKEE

PA-28-140

-VS

POWER

ALTITUDE t950

LBS. GROSS

WT.

t4000

F lrj lrJ

L t

F t2000 l-

TOOOO f

F d

Booo

I l.V

*'/l*

|

_<r

_)_

* rsl

(, lo-

E)_

-å o

(, q.

(r'

§

Q s*.

U) fr

6000

4000

,A

2000

^§r,r^s7

*-lrl_l

*'/[

I-)

2000 2lo0

2200 2300

2400

2500

2600

2700

ENGINE

SPEED

R,PM

ENGINE

SPEEO

R.P.M.

730115

SECTIONIV

THE

PIPER

CHEROKEE

PIPER

CHEROKEE

PA-28-140 rtt

POWER

AUT|TUDE

ttr

r50

.8S.

GRO ss li r4000

F

tzooo

UJ trl

5

roooo

<

8000

F al,

z

B

eooo

I I

.r1

"+ ls/

* a u a'

Q'r lJ/

4000

2000 e^r§rcft lo

N o

2000

2loo

22c0 2300

?4c,0 2500

2600

27c/c

ENGINE SPEED-RPM.

730115

SECTION

THE

PIPER

CHEROKEE

7000 trJ lrl

L l

t

6000

<

5000

3r, z

4ooo

PIPER CHEROKEE

-i

-l

FL,

'No

APs

WND

4oo

PA-28-140

LANDING

DISTANCE

DEN'ITYXLT.'UDE

POTI'ER

OFF

PAVED LEVEL DRY

IIAXIMUM

BRAK]NG

SHOBT

FIE] t95o

LBS. GRosS

wr. I

offl*'j

J t

RL tr

INTIOAY

FFORT'

I tr

-it

I

l ol

-<f

6t

J-

Fl_

:hr

3000

l-l

'rfi

2000

I roo0 o

200 400 600 800 looo

1200

1400

LANOING OISTANCE, FEET

730115

25a

THE

PTPER

CHEROKEE sEcrIoN

lv

talll

E-

--uto, a

:l

! ruu

E

rnr

a

3l|0 a0[0 tl0t

alllltlt2lt8

PA-2E-140

PIPER

CHEROKEE

llllll

GLOEE

EDSTANCE

vs

AUTOIIUDE

rrrlll

IIII fl$m

|l lr.r, trortr[r

ilr -Ms lllt

atrt

urc[

ruI§

2sb

7ror,5

THE

PIPER

CHEROKEE

PIPER

CHEROKEE

PA-28-140

lllllllllll

AL]IIIIUDE

GQ)INVEIiI§||a)IN gIfiJ4\IB]I fit§

GIrm oEttilltt

$u,[0 lE uso

ot§n

[TluDr

n

rnof, EI§IltS rID

Pntssu[E r0r ust

IHmrIUnt rllluffi

GffiDlIlo§ ilTlrErmilrlff

Gilm§.

SECTIONIV

1{000

20000 r§l

;18000

c t

12000 t00t

,d»r

U»

.t0 .10

+ia

\1t

T

-i ir!

\[E»

b!-

.!il--

L

20 13 80 l!

ITTPMIIURT

. 'F

100

3011 5

sEcfloN

GENERAT MAINTENANCE

Tire

lnflation

Battery.Scwice

Brakc

Scrvicc

Landing

Gear

Scrvice

Fuel

Requiremens

Carc of Air

Filtcr

CarcofWindshiddandWindour

.....,

Scriel

Nunbcr

Plrtc

.

Lcvcling end

Rigging

,,

27

770527

TTIE

PIPER

EIIOKI-.]IJ

SIjCT'I()N

sEcfloN

GENERAT MATNTENANCE

TIRE INFTATION the

F'or rtraxinrurl service fronr the tires

()n thc Chcrokcc, kt.cp

tlres

inflatetl t() the proper pressurc

of

24 pr»untls for thc nrain gear an<l

24 pountls for thc. nose

whccl.

lnterchlngc thc tires on the nrain wheels, if necessary, to pr«rtluce, even \t,cilr.

AII wheels an<l tires and are balancccl bcfore original lrrstullation, the relationship of thc tire, tube and whccl shoukl bc ur:rintained, if at all poo-sible.

Out of balancc wheels con causc (,xtrenle vibration on nents, take-off.

In the installation o[ new cotup(r-

it

nray be necessary to rebalance thc' whce,lwith thc tire s nrounted.

BATTERY

SERVICE

The under l2 volt hattery is locate'd in a stain.lcrss stcel containe,r the baggage conrFlrtment floor.

Thc containersllould l)e d rained occasional

I y by opening t he nrbber ca p on t lrc d rain

I ul)c.

Check the batte ry fo r propcr tluid levc'l

(bek»v tlrc baf flc platcs

Use a hydrometer to determine thedensity of the battcry fluid.

If

the battery is discharged, clrarge

lt

llcfore takc-off as tlrrce volts areneeded toexcitcthe alternator.

Rcchurgcstarting at

a

4 anrp rate and finishing witlt

a

2 amp rate.

Quick charges are not recommended.

BRAKE

SERVICE

Tlre brake system is filled

with

MIL-ll-5606

(petrolcunr

6ri0s0 t 27

SECTION

THE PIPER

CHEROKEE base) hydraulic brake

fluid.

This should be checked at evert-

I00 hour inspection and replenished when necessary by filIurg the brake resenroir on the firewall to the indicated

level. If

the system as a whole has to be refilled with fluid, this should be done by end of the filling with the fluid under pressure from the brake system.

This

will

elimlnate air from the system as

it

is being filled.

No adjustment

Cherokee,

of

brake clearances

is

necessary on the

If

after extended sewice the brake blocks become worn excessively, they are easilyreplaced with new segments.

TANDING

GEAR

SERVICE axle

Main wheels are easlly removed by taking off the hub cap, nut, and the two bolts holding the brake segment in place, after wNch the wheel slips easlly from the axle.

Tires are removed from the wheels by first deflating the

tire,

removing thethreethroughbolts, and separating thewheel halves.

Landing gearoleo stnlts should be checked for proper srrut exposures and when under fluid leaks.

The required extensions for the strut normal static load (ernpty weight of airplane plus tuII tuel and oil) is

3. 25 inches for the nose gear and 4. S0 incbes for the main gear.

Should the strut exposure be belor,v that required,

it

should be determined whether alr or oil is required by

first

raisirg the alrplane on

jacks.

Depress the valve core to allowair toescape from thestrut housing chamber,

Remove the

filler

plug and slowly raise the strut to full compression.

U the strut has sufficient fluid the

itwill

be visibleupto the bottom of

filler

plug hole and

will

then only require proper inflation.

Should should be attach a fluid be below the borrom of the clear plastic hose to the

filler

plug hole, oil added,

Replace the plug with valve valve stem of

core

the remqved, and submerge the other end in a container

of

(MIL-H-5606). Fully compress and extend the

filler

plug hydraulic fluid strut several

670424

THE

PIPER CHEROKEE sEcTtoNv

LEFT TANX

FUEL SELECTOR

VALVE

RIOI{T

TAilK

FUEL OUANTITY GAUCES

SECTION

THE PIPER

CHEROKEE times thus drawlng fluid from the container and expelllngair from the strut chamber. To allow fluid to enter the botrom chamber of the main gear stnrt housing, the torque link assem

bly must be disconnected to let the strut be extended a minimum of l0

When inches,

(The nose gear torque strut fully and againcheck fluid llnks nected.)

Do not allow the stmt to extend more than l2 inches.

air bubbles cease toflow through the hose, compress the

level

need

Reinstall not the be disconvalve core and

filler

plug, and the main gear torque links if disconnected.

Wit

With fluid in thestrut housingat thecorrect level, artach a strut pump to the air valve and with the airplane on the ground, inflate the oleo strut to the correct heiglrt.

In jacking the

Cherokee for landing gear or other service, jack kit (available through the

PiperAircreft Sewice

Depart ment) should be and a used. This kit conslsts of two hydraulic jacks tail stand. At least

350 pounds of ballast should be placed on the base of the hydraulic tail stand beforejacking up rheairplane.

The jacks should be placed under the jack points on the bottom of the wing and the airpl,anejacked up until the is at the the right height to attach the

tail

stand. After tail stard, and adding the ballast, rhe jacking tinued until the airplane is at the height desired.

tail skid attaching may be con-

FUEI

REQUIREMENTS

The minimum aviation grade

Since the use fuel for

åe

pA-28-f4O is g0/87.

of low€r grades can cause serious engine drmage in a short pcriod of time, rhe engine warranEy is invalidated by the use of lowcr oclanes.

Whcnoer

8O/E7 is not av&ilable, rhe low6r lcad 100 grade should be used. (Sec Fuel Grade Comparison Chan,

Latest issue next page.) Refer to the of

Lycoming Service

Insrnrcrion No.

1070 for addirional information,

The continuous us€, more than

Z1oh of thc opcraring time, of thc higher leadcd fuels can result combustion chamber and in increased eogine deposits, both in the in the engine oil.

It

may require increased

770527

THE

PIPER

CHEROKEE

SECTION

V spsrk plug meintcna.nc! and morc frcqucnt oit changcs. The frcquency of sperk plug maintenancc and oil drain pcriods will bc governeC bv thc amount of lead pcr gallon and thc rypc of.opcration. Opcration at

full rich

mixrure rcquires inorc frcqucnt mainrenance pcriods; thcrcforc,

it

is important ro use propcr approved mixturc leaning proccdures.

Rcfcrcncc the latcst issuc of

Lycorning Scrvicc

Lcttcr No. Llg5 for carc, opcration,rnd mlintcnanc. of dhc airplanc whcn using tlre highcr lcaded fud.

A summary

of

thc current grades as well as thc previous fuel dcsignatioru arc shown in rhc following chan:

FUEL CRADE COMPARISON CTIART

Pnviou

Commrr<i:l

Fucl

Grd6 (^ST[LD9lo)

(lrerlc

8(Vff7

9lle6 rm/tJo

Iil/l4l

Cul r b luc ta(!n

purplc

Har,

TEL ml/U S gzl ot z0 i l.o

4.6

Curtnr ('bmmcacial

I;ucl Gr:dc!

(ASTM-)9lG7r)

( r.d(

'l00LL l([

(:oldr rcd blu<

8(ccn

,Uax TEL ml/U,S.8rl.

o.5

2.0

't. o

Cu..m( Mili(lry

Fucl Gndcr

(^tll--G-JJ72li)

^mandmcnr

No t

(itrdc

Co or

Mu. Tl:L ml/U.S. gd tolil rad 0.5

100/uo t t5l

1+t gr«n purpl.

J.o

4.6

:..n1#,'?,-Jå:ffi

';"J;:i:i'åt'l:';ifr [1;'I,;:f up ro .a mUU.S. BlUon rrc approvtd

Io. ut. in rll engin<,

::5;l-#:'iliJili;l?h;",

I crdfiarcd for u* wirh

Frdc loo/l rO tuel.

OIL

REQUIREMENTS

The capaciry

of

the

0-320 scries engine is

8

qurrts, and the minimum safc quantity is 2 quarts

[t is rccommcndcd that t]re oil be changcd crrcry 50 hours and sooner. under unfavorablc operating

-conditions. Interrels bctween

100% oil changcs can be incrcased as much as on cngines cquipped with full flow carridge typc oil filters, prorridcd the elemerrt is rcplaccd cach 50 hours specificd octane fuel of opcration and the is used.

Should fucl other than the specified o«ane rating for the powcr plant bc uscd, rcfcr to the latcst issuc of

Lycoming Servicc

No.

1014

Letter No. L185 and Lycoming Service

Irutruction

for

additional information and recommcndcd scrvice

770527

SECTION V

THE

PIPER

CHEROKEE proccdures. Thc following grades ere temPcratures: recommended for tJrc specificd

Tcmpcratwcs above

60oF

Tempcratures bctwcen 30oF to

90oF

Temperatuies between 0oF to

TOoF

Temperatures bclow 10oF

SAE

SAE 30

SAE 20

Either mineral oil or anti-dispcrsånl oil may bc uscd, but the two typcs of oil may never bc mixcd.

CARE

OF

AIR

FILTER

The ca rbu retor a

I r filte r must be cl caned may be necessary to clean the at least once every fifty hours.

Under extremelyadverse conditionsof operatiott

it filterdaily.

Extra filters areinexpensive and a spare should be kept on hand and used a:; a rapid replacement.

ped

The filter manu(acturer recommends thar the filterbe tapgently to remove dirt particles.

Do not blow out

\ryith compressed air.

CARE

OF

WINDSHIELD

AND

WTNDOWS

A cerrain amount of care win<low.s clcun and

is

ncedcd to keep the plexiglass untnarrctl.

'l'hc following procctlurc is rccollt rtrc nrlctl:

l.

Flush witlr clean wate r and tlislodge excess

dirt,

mud, etc

,

with your lund.

2.

Wash with mild soap sponge, do not nrb.

and

water.

Use

a

soft cloth or

770527

THE PIPER GHEROKEE

SECTION

3. Remove oil, grease or sealrng compolrnos wrth a sofr cloth and kerosene.

Afler cleaning apply a thin coat of hard polishing wax

Rub lightly with a soft cloth.

A severe scratch or mar may be removed by using jeweler's rouge to rub out the scratch, smoothing, and then applying wax.

SERTAL

NUMBERPLATE

the

The serial nurnber plate is located near the stabilator on left side of the airplane

Refer to this number for service or warranty matters.

LEVELING

AND

RIGGING

Leveling the Cherokee for puposes of weighing or rigging is accomplished as follows: l.

Partially withdraw two machine screws locaM irnmdiately below the left front side window.

Thæe screws are leveling points and the airplane is longitudinally level when a lwel placed on the heads of thæe screws indicates level.

2. To put the airplane in a longitudinally level position on scales, first block the main gear ol.eos in the firlly extended position, then deflate the nose wheel tire rrntil the proper attitude is obtained.

For rigging only, the airplane ruay be placed on jacks for leveling.

To level the airplane laterally, place a lwel across the baggage compartment floor along the rearbulkhead.

Rigging: Æthough the fixed flight surfaces on the Cherokee cannot be adjusted for rigging purposæ, it may be necessary upon occasion to check the position of these surfaces.

The mo.vable surfaces all have adjustable stops, as well as adjustable turnbuckles on the cables or push-pull tubes, so that their range

770527

f-ts

:i e<gEE

THEPIPERCHEROKEE

SECTION V

of

Lravel can be altered.

The positions and angular travels of the various surfaccs are as follows:

1.

Wings:

7o dihedral,2" washoul

2.

Søbilator Travel: l8': up,

2o down, tolerance

*

lo.

3

Fin should be vcrtical and in line wih center of fuselage

4.

Ailcron Travcl: 30" up, 15" down, rolcrancc+ 2".

5.

Flap

'fravcl:

0", 25', 40o, tolerance + 2"-

6.

Ruddcr Travcl: 27" right and ldft, lolcnrn«r +

2o.

-

Surbilator Tab Travcl: 3"up,

l?

&lwn, tolcmncc

f

-l

Cablc tensions

Rudden,l0 t5 for thervarious controls arc as follows:

lbs,

Stabilars:40

+5 lbs.

Ailerons:4Ot5

lbs.

StabilaorTrim:

tl

lb.

9 1030

(,r,

\,

I',UJ,IlqA:IlOll CiråJ!'J

IOrr

Prpunc[.runoruuiz]\-atl.t{ro

'f ltE PtI'riR cl{liR oKUrl

I il;----_l l"l*"

I a lil'

I olrll

I o l*"

I

*ollli

rriro

Olav

Klesercd

INDEX

SECTTON

I

SpecificationFeaturcsr

Performance

Itowcr

I'Lutt

FuelandOil

...

Dimensions

Landing

Gear

.

....,..

......

Pag.

I

SECTION

Design

Informations

Sructures

Landing

Conuol

Gear

Systcm

FuelSystem

ElectricalSystem

......

........9

HeetingandVcntilatingSystem .....

CabinFeanrres

.,...

SECTION

III

Opcratinglnstrucions:

Starting

Warnrup

GroundCheck

Takeoff

Climb.

Stslls.....

.

Cnrising

Mananvers

Approachandlanding

Mooring

Weight and

Bdance

.

......

.,..1+

..,f5

,...

.

..

....17

.....18

....18

.......19

.....

...19a

.

l9e

770527

INDEX

(cont.)

SECTION

lV

Pagc

Takeoff

Rate

DistanccvsDcruityAltitude

. . - . .

.

20 of

Climb vs Densiry

Altitude

. .

.

True Airspced vs

Density

Altitude

(f95Olbsgrossweight)

.....-.22

True Airspeed vs

Dcnsiry Aldtudc

(2150 lbs. gross weight)

Range vs

Density Altitude

(1950 lbs, gross wt)

Rangc w

Density Altirudc

(2150 lb6, gross r+r)

Power vs

Ntitude (1950 lbs. gross weight)

Powcr rrs

Altitudc

(2150Ibs. gross wcight)

232

23b

Glidc Distance vs

Altitude

Convcrsion

Chan

252

25b

SECTION

'GeneralMaintcnancc

, . ,

Tirelnflation

BettcryServicc

BrekeServicc

LandingGcarService

FuclRequircments

OilRcquirements..

Carc of Windshickl antl

Ssill

Wilr«lowc

Nunrbcrtrhtc..

.

....27

.....27

.. ....28

.:.....

,.....31

. . .

.

.....33

770527

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Key features

Fixed-pitch propeller
Lycoming engine
Four-seat capacity
Ease of handling
Reliability

Frequently asked questions

The minimum aviation grade fuel for the Cherokee 140 is 80/87, but lower grades can cause serious engine damage so use 100LL if necessary.

The oil capacity of the O-320 series engine is 8 quarts, the minimum safe quantity is 2 quarts.

It is recommended that the oil be changed every 50 hours and sooner under unfavorable operating conditions. Intervals between oil changes can be increased as much as 100% on engines equipped with full flow cartridge type oil filters, provided the element is replaced each 50 hours of operation and the specified octane fuel is used.