Piper Cherokee 140 User guide

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, ^S A SUBSTTTUTE FOR ADEQU^TE ^ND
coMpETENT FLIGHT INSTRUCTION, OR KNOWLEDGE OF THE
CURRENT AIRWORTHINES§ DIRECTIVES, THE APPLICABLE
FEDERAL AIR REGULATIONS, AND ADVISORY CTRCULARS. IT
IS NOT INTENDED TO IIE A GUIDI' OF ITASIC }'LIGHT
INSTRUCTION, NOR A TRAINING MANUAI,.
'l'ilrt il^NDD(x)K ls Drist(.;Ntil):
I. TO IIELID YOU OI'IiRA'I'E YOUR CHIIROKIiI' WITII
SA I.'ETY AND CONIIIDENCE.
2, TO MORE FULLY ^CQU^rNT yOU WITH THE BASIC
PERFORMANCE AND HANDLING 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 5U
Issu«l: Febnrary 1964
Revised: March l. l99l

SECT|ON I
SPECIFICATION FEATURES
Performance .
Weights
Power Planc.
FueI and Oil
Baggage
Dimens ions.
Landing Gear .

THE PIPER CHEROKEE SECTION
sEcfloN I
SPECIFICATION FEATURES
PERFORMANCE
Tetc-off Di.Btaræ Over 50 ft. Obsracle (fr.) (fl8ps up) lsm I r?00
Best Rate of CUmb Spæd (hph) 85 I Ss
Rrte of CUmD (ft. per mln.) I 820 i 660
Scrvtce Cetllug (ft.) 15, O0O r4,3OO
Absolute Ceiltng f7, OOO ,U. U*
Top $ced (mph) r r4t (r44.) i t39 (r42.)
ClutslnB Sp€ed (75% power, sea level) (mph) 'l r20 (f23.) ' tZt 1tU.1
Optlmum Crulstng Speed pSS potuer, 7000 It., mph) f30 (f33.) I f30 (f33.)
The gross $reighr o, l95O Pq.rnds ln the following perlårmance chÅrts appll,es ,o S{rUf Nos, 28-2OOOO
to 28-20939, uleas the airpleqe has been modilled t
Nos, 28-20940 snd llp hsvc bcen llcenircd from the fa
Perforrutrcq flgues ere for strnderd alrplanes
Ievel or ståld flhltudc. Any dcvistldl from Sta
GRO§S WEIGHTS
Telc-off Ru (It,) (flaps 14)
wer, sea level) 100 (102+) .l r00 (r02r)
. 7.e i 8.4
s.3 I s.o
) 5r5, { hEs. (r20, 6 hr8...) +fO, n frru[ (680, 6 hrs.rr)
) 560 (780..) i 535 (725.+)
Opttmu$ Grulslng Renge (55$ powrr, 10, 0m ft, ) 600 (840..) I 570 (790.r)
'\iltren Fenders Instålled
"With 50 gal. Resene Fæl
730I I 5

SECTION ITHE PIPER CHEROKEE
SPECIFICATION FEATURES: (cont)
PERFORMANCE
I
: lnetruciloul Pover Crutsltrg Range
(50%,pqwer, sea level)
Sta[ln-gSpeed (flaps doyn, mFh)
Landlng Roll (flaps down, fr.)
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)
"Wirh 50 gal, Resefle Fuel
aRosri TErGr{Ts
I
640,1 6.s hrs. (89s,
I
t hrs. ti) d50, 6.5 hrs, (910, t hrs. r.)
52 54
48s 53s
r9 50 2r50
650630
o-320-E2A
140 ei 2450
5. r25
3.875
319.8
7:\
272
I
M74DM
2150
l20l
949
t24l
909
o-x20-E2A
150 at 2700
5, t25
3.875
319.8
7i7
8
M74DM
1950
,.180
770
1220
730
1

THE PIPER CHEROKEE SECTION I
SPECIFICATION FEAIURES: (conr)
GROSS WElerrrs
FUEI. AND OIL
Fuel Capaclty (gal. ) Srandard
Fuel Capacity (Sal.) Reserve
Oil Capaclty (qts. )
Fuel Aviation Gradc (Minimum Octenc)
(Spccified Octane)
(Altanctc Fuels)
BAGGAGE
Maximum Baggage (lbs.)
Baggaæ Space (cubic ft.)
DIMENStONS
Wtng Span (ft. )
Wing Area (sq. ft.)
trVing LoadinS Qbs. per sq. ft.)
Length (ft.)
Height (ft.)
Power Loading (lbs. per HP)
IANDING GEAR.
Wheel Base (fr.)
Wheel Tread (ft. )
Tlre kessure (lbs.)
36 36
50 .50
88
80187 80187
80147 80.187
See pegc 3O
200.*.
,'»
r950
30
r60
12.2
23.3
7.3
13. 9
2r50
100
,,
Nose
Main
6.2
10.0
24
24
30
r60
t3,4
23.3
7.3
r4.3
6.2
r0.0
24
24
'rtExcept when family seat and sefety belts are installed 340
lbs. ls permitæd.
770527

SECTIONI THE PIPER CHEROKEE

SECTION I
DESIGN INFORAAAT]ON
Engine and Propeller
Stnrctures
Landing Gear
Conrol System
Fuel System
Electrlcal system
Heating and Ventilating System
Cabin Feahrres
5
6
6
7
8
9
r0
r2

THE PIPER CHEROKEE SECTION II
sEcTtoN il
DESIGN INFORMATION
ENGINE AND PROPELI.ER
The Lycoming o-IZo.EzA enginc inselled in rhe Cherokce
PA-28-140 is ratcd ar l4O horsepowcr ar 2450 rpm or 150 horsepower
"t 27OO rpm..,This cngine has a compression ratio of 7 to I end
requires 8O/87 minimum octanc fucl. Rcfcr to Fuel Rcquiremenrs on
page 30 when using alrcrnarc fuels. The engiae is eguipped with a
gcared startcr, 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
of heavy gauge stainless steel which incorporates a heater
shroud, to provide cabin heat and carburetor deicing.
The propeller used on the PA-28- I40 is a Sensenich M74DM
fixed-pitch aluminum alloy unit. Its diameter is 74 inches with
a standard pitch of 60* inches, All 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, with-
out the use of cowl flaps or cooling ftanges.
The throttle is of the push-pull type and is located ir the
lower center 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 propellers when gross weight is 2I50.
+*When gross weight is 2150
770527

SECTION II THE PIPER CHEROKEE
for stopping the engine. Intermediate posltlons are used for
leåning the mlxture at ahitudes above sea-level, The carbu-
retor heat control, located to the left of the thronle, provides
maximum carburetor heat when pul.led to its full aft position.
With carburetor heat off, all eugine air passes througtt a high-
efficiency dry-type filter. Therefore, prolonged ground oper-
atlon with carburetorheat"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 re-
quirement§. All exterior surfaces are prtmed with etchlng
prlmer and painted wlth acrylic enarnel.
The wlngs are attached to each elde of the fuselage by In-
serting the butt ends of the respective main spars into a spar
box carry through which is an integral part of the fuselage sfruc-
ture, provlding. ln effect, a contlnuoua main spar urith spllces
at each slde of the fuselage. There are also fore and aft at-
tachments at the rear spar and at an auxlliary frmt epar.
The wing airfoil section is a l,aminar flow type, NACA
652-4fS wlth the maximum thicknessabout 40% aft of the tread-
ing edge. This permlts the main spar carrythrough structure to
be located under the rear seat providlng unobstructed cabln
floor space ahead of the rear seat.
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.'
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 trim. The nose gear
steering mechanism also lncorporates 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 full fueI
and oil) Ioad.
The brakes are actuated by a hand leverand master cylin-
der, which is located belowand behind the left centerof the in-
strument sub-panel. The brake fluid reservoir is installed on
the.top Ieft front face of the firavall. The parking brake is in-
corporated in the master cylinder and is actuated by pulting back
on 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 are provided as standard equipment with a
cable system used beEween the controls and the surfaces. The
horizontal tail is of the all movable slab type, with an anti -servo
tab which also acts as a longitudinal trim tab, actuated by a
control on the cabin ceiltng" The stå-bilator provides extra
sta-bility and ss slze, drag, and weiglt
than conventi allerons areprovlded with
a dlfferential eliminate adverse yaw in
ilrning mane the amount of coordlnation
I
67 103 r

SECTION II THE PIPER CHEROKEE
requtred in normal turns.
The flaps are manually operated, balanced for light oper-
ating forces and spriog loaded to turn to the up position- A
past-center lock incorporated in the actuating linkageholds the
flap when it is in the up position so that it may be used as a
step on the rlght side. The flap will not support a step load ex-
cept when in the full up position, so it must be completely re-
tracted when useda§ a step, The flaps have threeextended po-
sitions, 10, 25 and 40 degrees.
FUEL SYSIEM
Fuel is stored in two twenty-five gallon tanks whlch are
secured to the leading edge structure of each wing by screws
and nut plates. This allows easy removal for service or in-
spection.
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 for use in case
of failure of the engine driven pump. The 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 draln-
ed 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 open-
ed. Each tank has an individual qulck drain located at the bot-
tom, 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 Cherokeeisequippedwith thepiper F.T.p. (Full Time
Power) Electrical System, ICs 12 volt alternatorprovides elec-
trical power at all engine speeds and results in improved per-
formance for radlo and electrical equipment and longerbattery
life. In additionto thealternator, the electrical system includes
a 25 ampere-hour baEery, a voltage regulator and a master
switch relay. The battery and relay are mounted beneath the
baggage compartment floor. Access for service or inspection
is obtained by raising the hinged baggage compartment floor
panel. The battery box is designed to accommodate a Larger
capacity battery for extreme cold weather operation.
Electrical switches, fuses
and fuse spares are located on
the lower left side of the in-
strument panel.
Standard electrical acce s -
sories, in additiontothose al-
ready Iisted, include a starter,
stall warning indicator, cigar
lighter and ammeter. Mvi-
gation lights, 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 commun-
lcatlons and navlgational equipment.
In conventlonal generator systems, the ammeter indicates
battery discharge. In the Piper FullTime Powerelectrlcal sys-
tem, 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 will in-
dicate the amount ofcharging current demandedby the battery.
This amount will vary and depends on the percentage of full
clørge on the battery at tåe time. When the banery becomes
charged, the current dlsplaeed on the ammeter will reduce to
a mlnimum value of about two amperes. As each unit of elec-
trical 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 is approximately thirty
amperes, Thts thlrty ampere s plus approximately two amperes
for the futly charged batterywill appear conriouously under these
flight condittoos.
Because of the mechanical simpliclty of the alternator,
matnteoance should prove to be a minor factor as compared
to prevlous systems. Should service be requlred, contact your
local Piper dealer.
HEATING AND VENTII.ATING SYSTEM
Heat for the cabln lnterlor and the defroster system is pro-
vided by a heater muff attached to the exbaust system. Con-
trols fof these systems are locatedon the lower right hand side
of the instrument panel. A third confrol in this area regulates
a large fresh air vent located on the left hand stde of the cabin
near the 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.
IO 6s0630