Piper cherokee WARRIOR User manual

-if"."rXn"-
AIRCRAFT MODIFICATIONS INC.
F.A.A. APPROVED
AIRPLAI{E SIIPPLB,IENTAL ELIGHT MANUAL
For
PIPER CIIEROKEEMODEL
PA-28-151
wirh
LYCOMING
0-320-D2A, -D28, -DzC, or -D3G
ENGINEINSTAILED
REcrsrmrroNNrnaER
N tP\^3:I
SERIAL NI]I,IBER
ftris Supplenental Flight ManuaL is F.A.A. approved material and must be
Ln Ehe airplane for all operations when Lycorning O-3?O-D?A, 0-320-D28, O-320-D2C
rr 0-320-D3G engine is installed in accordance with STC
SA2969SW. Ttre
lnformation contained herein supplernents or supersedes the lnformation
:n the form of placards, narkings, and approved rnanual material. For
limitations, procedures and perforrnance informatlon not contained in this
iuppleurental Flight Manual- consult the basic airplane placards, rnarkings
rnd approved manual-material.
F.A.A. APPROVED
FEDERAL
AVIATION ADMINISIRATION
Southwest Region
Fort l{orth, Te:<as 76LOL
DATE: October 21 1981
S.T.C. No. 5A29695[{
Pagelof2pages
Woco-Modison
CooperAirport
o
P.O.
Box5249
. Woco,
Texos
76708.847-752-8381

I
2. PROPFT.TER:
II. LIMITATIONS
1. NGINE LTMIIS:
2. PROPELLM.
LD{I15:
3. M{GINE INSTR.I]MENT
I4ARKINGS:
F.A.A. APPROVED
DATE: L|/LL/8L
{tF:jiii;:i:b
Lycmrlng 0-320-D2A
or
Lycoming 0-32O-D2B
or
Lyconing O-32O-D2C
or
Lycoming 0-320-D3G
Sensenich 74DM6-0-60
or
Sensenich 74DM6-0-58
Maximum
Continuous:
150 H.P. - 2550 RPM
Takeoff (Five (5) llinutes)
150 H.P. - 2700 RPM
Static RPM
at maximum
throttle setting:
Not over 2450, Not under 2350
Diameter: Maximrmr
= 74 inches
Minimurn = 72 inches
TACIIOMETERI
Green Arc
Yellow Arc
Red Radial
2200 - 2650 RPM
2650 - 2700 RPM
- 2700 RPM
AIRCRAFT MODIFICATIONS INC.
PIPER CIIEROKEE
MODEL
PA-28-151
SUPPLN,IE{TALFLIGIIT MANUAL
GENEMI.
1. ENGINE:
III. PROCEDIJRES
No Change
IV. PERFORMANCE
the perfonnance of Lhis airptane equipped with a Lycoming O-320-D2A,
O'32O-D2B' 0-320-D2C, or 0-320-D3G engine is equal to or better than
the original F.A.A. approved perfor:mance.
S.T.C. No. SA2969SW
Page2of2pages
Woco-Modison
Cooper
Airport
. P.O.
Box5249.
Woco,Texos
76708
. 817-752-8384

ttfrd Sottr!f gula
Eqertmrnt
0F
Crsruportation-fcdral
B0lation
lldminignation
Fupplgmsntsl
?[Upe€ntifirsts
(€ontinusfion
Fheet'ir
J(r"rrl'.* SA2969S!il Revision 2
Lfunitations and Conditions :
1. Fl.A Approved Airplane Supplenental Flight Manual dated April 5, L979,
for Lycming 0-320-D3G engine lnstallation with Sensenich 74DM6-O-58
propeller;0R
FAA Approved Alrplane Supplpoental Flight Manual dated ApriL 24, 1980,
for Lycoming 0-320-D3G engine installation with either Senenich
74DM6-0-58, or 74DM6-0-60propeller; OR
FAAApproved Airplane Supple'r'ental Flight Manual dated October 21, 1981,
for Lycoring 0-320-D2A, -D28, -DzC, or -D3G engine installation with
either Sensenich 74DM6-0-58, ot 74DM6-0-60 propeller is required.
2. Conpatibility of this nodification with other previously approved
uodifications must be deterained by the installer.
An1,allerattcrt
oJthis
ccrttfuaie
ispunishable by
afru oJnolcxcccdingt|,000, or imfrtscnmtrti ncl cxctcdtng
3 yars, or botli
FAA FoRM 8rrG2-t (tG69) This cettifuak nu2 bcnazstarcd in ucordantewith FAR 21.47
pecg 2 or 2erces

CHEROKEE
WARRIOR
GENERAL SPECIFICATIONS
PERFOR.MANCE
Published figures are for standard airplanesflown at gross weight under standard
conditionsat sealevel,unlessotherwisestated.Performancefor a specificairplanemay vary
from published figures dependingupon the equipment installed,the condition of engine,
airplaneand equipment, atmosphericconditions and piloting technique.Each performance
figure below is subject to the sameconditions ason the corresponding
performance
chart from
which it istakenin the PerformanceChartsSection.
TakeoffGroundRun
(minimum)(ft)
Takeoff
Distance
Over5GftObstacle
(25
o
flaps)
(ft)
Best
Rate
of ClimbSpeed
(mph)
Rate
ofClimb
(ft per
min)
ServiceCeiling
(ft)
Absolute
Ceiling
(ft)
TopSpeed
(mph)
OptimumCruisingSpeed
(75%
power,
optimumaltitude,
leanedto
best
power)
(mph)
Cruising
Range
(75%
power,
optimum
altitude,leanedtobesteconomy.
noreserves)
(mi)
OptimumCruisingRange
(55%
power.
optimumaltitude,leaned
to
besteconomy,noreserves)
(mi)
Stalling
Speed
(flaps
down)
(mph)
StallingSpeed
(flaps
up)
(mph)
Landing
Roll
(flaps
down)
(ft)
LandingRollOver50-ft
Banier
(flaps
down)
(ft)
l
065
1760
87
649
12,700
14,960
I
35*
I33*
720*
785
*
58
64.5
s95
lll5
WEIGHTS
Gross
Woight
(lbs)
Standard
Empty
Wciglrt
(lbs)
Maximum
Useful
Load
(lbs)
*WithOptional
WheelFairings
installed.
GENERALSPECIFICATIONS
REVISED:JULY 14.1975
2325
133
I
994
-JL-*-
l-l

CHEROKEE
WARRIOR
POWERPLANT
Engine
(Lycoming)
RatedHorsepower
Rated
Speed
(rpm)
Bore
(inches)
Stroke
(
inches)
Displacement
(
cubic
inches)
Compression
Ratio
Dry Weight
(pounds)
Propeller
McCauley
Sensenich
FUEL AND OIL
Fuel
Capacity
(U.S.
gal)
(standard)
Fuel
Caprcitf'
(U.S.
gal)
Usable
OilCapacity
(qts)
Fuel.AviationGrade
MinimumOctane
SpecifiedOctane
Altemate
Fuels
DIMENSIONS
Wing
Span
(ft)
Wing
Area
(sqft)
Length
(ft)
Heieht
(ft)
Wing
Loading
(lbs
per
sq
ft)
Power
Loading
(lbs
perhp)
Propeller
Diameter
(in.)
McCauley
Sensenich
TurningRadius
BAC'GAGE
MaximumBaggage
(lbs)
Baggage
Space
(cubicft)
Baggage
Door Size
(in.)
LANDING GEAR
Wheel
Base
(ft)
Wheel
Tread
(ft)
TirePressure
(psi) Nose
Main
o-320-E3D
rs
2700
5.125
3.875
319.8
7:l
276
rcr60/EGM76s3
74DMGG58
50
48
8
8o/87
80/87
RefertoFuel Requirements,
Section
l0 - PageIG9
35
170.0
23.8
7.3
13.7
15.5
76
74
t
3.0
Nose
(4 plyrating)
Main
(4 plyrating)
200
24
20x22
6.7
10.0
30
24
5.00
x 5
6.00x 6
GEITIERAL
SPECIFICATIONS
REVISED:
APRIL16,1976
t-2
TireSize

CHEROKEE
WARRIOR
I
?
36
GENERALSPECIFICATIONS
ISSUED:JULY17.1973 1-3

DESCRIPIIlIlI
AIRPU]IEA]ID
SYSIETS
TheAirplane 2-l
Airframe 2-l
Engine
and
Propeller 2-2
LandingGear 2-4
Flight
Controls 2-6
Frrel
System 2-7
Electrical
System 2-9
Vacuum
System 2-13
InstnrmentPanel
. 2-13
Pitot-Static
System 2-15
Heating
and
Ventilating 2-15
Cabin
Features 2-18
BaggageArea 2-18
StallWarning... 2-18
Finish 2-18
Emergency
LocatorTransmitter 2-19
Piper
ExternalPower 2-19
J
2-i

CHEROKEE
WARRIOR
DESCRIPTION
AIRPLANE AND SYSTEMS
THE AIRPLANE
The CherokeeWarrior is a single-engine,fixed gear
monoplaneof all metalconstruction
with low semi-taperedwings.
The fuselage
provides
a spacious,four-place
interior with optional featuresto ensure
individual comfort during short or extendedcross-countryflight.
The Cherokee
Warrior can serveasa rental or crossrountry airplaneandalsoasa training
and utility airplane. Performanceand loading characteristicscombine with economical
operationto makethe Warrioraversatile
airplanein the businessor personal
aviationfields.
AIRFRAME
The primary structure,with the exceptionof the steeltubeengine
mount, steel landing
gear struts and isolated areas, is of aluminum alloy construction. Tough fiberglass and
thermoplasficare usedextensivelyin the extremities - the wing tips, the engine
cowling, etc.-
andin nonstructural
components
throughouttheairplane.
The fuselage
is a conventional semi-monocoque
structure.On the right sideof the airplane
is a large cabindoor for ease
of entrance
andexit anda largebaggage
door to provideeffortless
loading
into the 24 cubicfoot compartment.Maintenance
hasbeenreduced
to a minimum with
advanced
fuselage
design.
The wing is a conventional
semi-tapered
designincorporatinga laminar flow, NACA
652415, airfoil section.The cantileverwings are attachedto each side of the fuselageby
insertion of the butt endsof the main sparsinto a sparbox carry-throughwhich isanintegral
part of the fuselage
structure.Thesparbox carry-through
structure,
located
undertherear
seat,
provides
in effectacontinuousmain
spar
with splicesat eachsideof thefuselage.
Therearealso
fore and aft attachments
at the rearand at an auxiliaryfront spar.Thistypeof wingstructure
provides
unobstructed cabin spacefor the rearpassengers
andallowsfor alighter wing structure
to improve
theusefulloadof theairplane.
Both aileronsand flaps are of modern,
all metalconstruction for smoothcontrol of the
aircraft. The aileronsaretaperedto accommodatethe semi-tapered wings.
In the fully retracted
position, the right flap locks to provide a step for cabin entry. The flaps havethree extended
positions:
10,25, and 40 degrees.
A horizontal stabilator,vertical fin, and a rudder make up the empennage.They utilize a
lightweight metal construction with fiberglass
tips.
AIRPIJ\NE AND SYSTEMS
REVISED:
JULY 14.1975 2-l

CHEROKEE
WARRIOR
ENGINE AND PROPELLER
The PA-28-l5| is powered by a Lycoming O-320-E3D four cylinder. direct drive,
horizontally
opposed
engine
ratedat 150HPat 2700RPM.It isequipped
with a starter, a60
amp l4 volt alternator,
a shielded
igrrition,dual
magnetos,
vacuuln
pumpdrive,a fuelpump,
anda wetted pol-vtrrethane
foam induction air filter. A recommended
overhaul
period
of 2000
hours
isbased
on Lycomingservice
erperience.
Operation
beyond
therecommended
timeis
the
decision
of theoperator.Since
Lycoming
from timeto timerevises
the
recommended
overhaul
period.
thc'owner
shouldcheck
with hisdealer
for thelatest
overltauI
period
on his
engine
as
wellasany
additional
LycomingServicc
Information.
The engine
compartment
is easilyaccessible
for inspection
through
top-hinged
side
panels
on either
side
of theenginecowlings.
Theenginecowlings
arecantilever
strltcturesattached
at
the fire wall. The engine
mountsareconstructed
ol steeltubing,
anddynafocal
mounts
are
provided
toreduce
vibration.
The.exhaust
system
is constructed
of stainless
steeland
incorporates
asingle
mufflerwith
heater shroudsto supply heated
air for the cabin. the defroster
systentand the carburetor
deicing
system.
An oil cooler
is locatedon the left rear
of thc'enginemounted
to thc engine
baffling.
Enginecooling
air, which is picked
up in the nosesection
of theenginecowling
and
carried
through the baffling. is utilized on the left sidefor the oil cooler.A winterizationplate is
provided
to restrict
airduring
winter
operation.
(See
Winterization
in Harrdling
andServicing.)
Engineair enters
on either
sideof the propeller
tltrouglt
openings
itt
thc'nose
cowling
and
is carrred
through
the engine
baffling
around
tlte engine
and oil cooler.
Air for the muffler
shroud
isalso
pickc'd
up from the
nosecowlingandcarried
through
alargc
duct
to theshroud.
Carburetor
indrrction
air entersa chin scoop
on thelowerright cowling
andispassed
through
a
wetted polyurethane
filter to the carburetor
air box. Heatedair enters
the carburetor
air box
throughahoseconnected
to theheater
shroud.
A Mgcar.rley
lCl60/8GM7653 or aSensenich
74DM6-0-58
fixed pitch propeller
isinstalled
as
standard
equipment.
The McCauley
propeller
hasa diameter
of 76
inches
with apitch
of 53
inches
and the Sensenich
hasa 74 inch diameter
with a 58 inch pitch.The pitch of both
propellers
isdetermined
at75% of the diameter.
Both
propellerunitsareof an
aluminum
alloy
construction.
Thepilot should
read
andfollow theprocedures
recommended
in theLycoming
Operator's
Manualfor this engine
in orderto obtain maximumengine
efficiency
andtime between
engine
overhauls.
AIRPLANEAND SYSTEMS
ISSUED:
JULY
17,1973
)-)

CHEROKEEWARRIOR
Throttle
Quadrant
andConsole
AIRPLANE
AND SYSTEMS
ISSUED:
JULY 17,1973 2-3

CHEROKEE
WARRIOR
LANDING GEAR
The fixed gear
PA-28-
I5I is equipped
with is a Cleveland
5.00
x 5 wheelon thenose
gear
and a Cleveland
6.00 x 6 wheelorr eachmain gear.
Cleveland
single
disc
hydraulic
brake
assemblies
are
provided
on thc'main
gear.
Thenose
gear
hasa 5.00
x 5 four plytire,
whilethe
main wheelassemblies
have6.00x 6 four ply tires.
At gross
weight.
themain
gear
tires
require
a
pressure
of 24psi,
and
thenose
gear
tirerequires
apressure
of 30 psi.
The nose
gearis steerable
througha 30 degreearceach
side
of center
by the useof the
rudder pedals
ind toe brakes.
A spring deviceis incorporated
for rudder centering
and to
provide rudder trim. A bungeeassembly
on the nose
gear
steering
mechanism
reduces
ground
iteering effort and dampens
shocks
and bumpsduring taxiing.The steering
mechanism
also
incorporates
ashimmy
damPener.
The threestruts
areof the air-oil
typewith thenormalstatic
loadextension
being3'25
inches
for thenose
gear
and
4.50incltes
for themain
gear.
The brakes
are
actuated
by tocbrakc
pedals
whichareattached
to therudder
pedals
or by
a hand lever
and master
cylinder
located
below
andbehind
the center
of theinstrument
sub
panel.
Hydraulic
cylinders
arelocated
above
eaclt
pedal
and
adjacelrt
to the hand
brakelever.
Thebrake
fluid resenoir
isinstalletl
on thetop left front faceof thefire wall.Theparking
brake
is incorporated
in the master
cylirrder
and
isactuated
by pulling
back
on tltebrake
lever
and
depressing
theknob attached
to the'leftside
of tlte
handle.
To release
the parking
brake,
pull
batt on the brake lever to disengage
the catch mechanism
and allow the handleto swing
forward.
AIRPLANE
ANDSYSTEMS
ISSUED:
JULY17.1973
24

CHEROKEE
WARRIOR
Main
WheelAssembly
AIRPLANEAND SYSTEMS
ISSLJED:
IULY 17,1973 2-5

CHEROKEE
WARRIOR
Console
FLIGHT CONTROLS
Dual flight controls are
providedon the Warriorasstandard
equipment.The flight controls
actuate
thecontrolsurfaces
throughacablesystem.
The horizontalsurface
(stabilator)
is of the flying tail design
with a trim tabmountedon
the trailingedge.This tab servesthe dualfunction of providing
trim control and
pitch control
forces.
The trim tab is
actuatedby atrim controlwheel
located
on thecontrolconsole between
the front seats.Forward rotation of the wheel gives
nose
down trim and
aft rotation
gives
nose
up trim. The stabilator provides
extra stability and controllability with lessarea,dragand
weight
thanconvcrrtional
tail
surfaccs.
The rudderis conventional
in design
and incorporatesa ruddertrim. The trim mechanism
is aspringloaded
recentering
device.The trim controlislocated
on theright sideof thepedestal
below the throttle quadrant.Tuming the trim control clockwise
gives
nose
right trim and
counterclockwise
rotationgives
noseleft trim.
Ailerons areprovidedwith a differentialdeflection.
This featurereduces
adverse
yaw in
turning maneuvers.
thus reducing
the amount of coordinationrequired.
An aileron
centering
spring incorporated in the aileron control systemon early models centen the aileron by
returning
thecontrolwheel
to neutral.
AIRPLANEAI\D SYSTEMS
REVISED:
JULY 14.1975
24

CHEROKEE
WARRIOR
Manually controlled flaps areprovided on the PA-28-151.The flapsare balanced
forlight
operating forces and spring loaded to return to the retracted(up) position. A control handle,
which is located between the two front seats
on the control console,
extendsthe flaps by the
useof a control cable.To extend the flaps,the handleispulled up to the desiredflap settingof
lO, 25 or 40 degrees.
To retract,depressthe button on the end of the handleand lower the
control. When extendingor retractingflaps,thereis a pitch change
in the airplane.
This pitch
changecan be conected either by stabilatortrim or increasedcontrol wheelforce.
Whenthe
flaps are in the retracted(up) position the right flap, provided with an over-center
lock
mechanism,actsasastep.
NOTE
The right flap will supportaload only in thefully retracted
(up)
position.When the flap is to be usedas a step,
makesurethe
flaps
are
in theretracted
(up) position.
FUEL SYSTEM
Fuel is stored in two twenty-five gallon(24 gallons usable)
fuel tanks,
givingthe airplanea
total capacityof fifty U.S.
gallons
(48 gallons
usable).Thetanks
aresecuredto theleadingedge
of eachwingwith screwsand
nut plates. Thisallowseasyremoval
for serviceor inspection.
On serialnumbers
7415001through7515449each
fuel tank hastwo outlets,oneforward
and one aft, to ensurean evenfuel flow. Fuel is pumped from the tanks through the forward
and aft tank outlets to fuel manifolds in the inboard sectionof either wing. Each
manifold isa
smallcollector with an inlet hosefrom eachof the tank outlets, andanoutlet hoseto the fuel
selector
valve.
On serial
numbers
7615001
and up thereisonly oneoutlet on each
tankand
no
fuel manifolds areused.
The fuel tank selectorcontrol is located on the left sidepanel forward of the pilot's seat.
The button on the selectorcovermust be depressedandheld whilethehandleismoved
to the
OFF position. The button releasesautomatically
when the handleis movedback to the ON
position.
An auxiliary electric fuel pump is provided in case
of the failure of the engine driven
pump. The electric
pump should
beON for all takeoffs
and
landingsand
when
switching
tanks.
The fuel pump switch islocatedin the switchpanelabove
the throttle quadrant.
'l'lrc
fueldruins
shotrltl
bc o;rcnctl
daily
prior
to firstflightto chcck
fr>r
watcrorsedimcnt.
h,aclrtank hasan individual
drainat the bottom, inboardrearcorner,andeach
fuel manifold
(on earlymodelsonly) is
equipped
with adrain.Theoutletsare
locatedon the undersideof the
wings.
A gascolator,
located
on thelowerleft front of the firewall,
hasadrain
whichisaccessible
from outside the nosesection.The gascolator
should alsobe drained before the first flight of
theday.
(See
theHandlingandServicingSectionfor thecomplete
fueldraining
procedure.)
Fuel quantity and fuel pressure
gauges
aremounted in a gauge
clusterlocated on the left
sideof the instrument
panel
to theright of thecontrolwheel.
An optional enginepriming systemis available
to facilitate starting.The primer pump is
locatedto the immediateleft of the throttle quadrant.
AIRPLANE AND SYSTEII{S
REVISED:JULY 14,1975 2-7

CHEROKEE
WARRIOR
EIIGIIIT
FUEt
PUTIP
l/"" SIRATnER
FUEI
IAIII(
SELICIOR
YATYI RIGHIMAI]IIAI{I(
TUTI.
OUAIITITY
GAUGTS
Fuel
System
Schematic
(Ser.
Nos.
7415001through
7515449)
AIRPLANE
AND SYSTEMS
REVISED:
JULY 14,1975
2-8

CHEROKEE
WARRIOR
THRl]TITT
MIIIURT
tlfGflft
tutt PUfiP
--='
fl.tclnlc
tufl.
PUilP
--
r.ttlt^ilrlAlil( futl rrillstttcl0R
Yrtvl. RIGHITAI]iTAITI(
TUIL{lUAilIIIYGAUGTS
FuelSystemSchematic
(Ser.
Nos.7615001andup)
AIRPLANE AND SYSTEMS
ISSLJED:JULY 14,1975 2-8a
)

CHEROKEE
WARRIOR
Fuel Selector
ELECTRICAL SYSTEM
The Cherokee
Warrioris equipped
with a simple
but highlyefficient
electrical
systemthat
can
be
easily
operated.
The electrical system includes a l4 volt 60 ampere alternator, voltage regulator,
overvoltage
relay,battery contactor
and a standardl2 volt 25 amperehour or an optional l2
volt 35 ampere hour battery. The battery is mounted in a thermoplastic box located
immediately
aft of the main
sparon theright side
of thefuselage
belowtherear
passengers
seat.
Thevoltage
regulator
and overvoltage
relayarelocatedon the forward leftsideof thefuselage
behind
the instrument
panel.
Electrical switches are located on the right center instrument panel, and the circuit
breakers
arelocatedon the lowerright instrumentpanel.
A rheostat
switch on the left sideof
the switch panel
cotrtrols
the optionalnavigation
lights
andtheradiolights.
A similar
switch
on
therightside of theswitch
panel
controls
and
dimsthe
optional
panel
lights.
Themaster
switch,
anti-collisionlight, landinglight and fuel pump are alsolocatedon the switch panel
and are
controlledby rockertvpeswitches.
WARNING
Strobelights
should
not
beoperating* hen
l)r.ing
througho\ercast
andcloudssince
reflected
light
can
producc-
spacial
distlricntation.
Do notoperate
strobe
lights
incloseprorinritr
to grouncr
.
tjrrrrng
takeoll'andlanding.
AIRPLANE
ANDSYSTEMS
REVISIID:
APRIL
6.1979 2-9

CHEROKEE
WARRIOR
A hinged
door
protects
and
gives
easvaccess
tothecircuitbreaker
panel.
Eachcircuit
breaker
on
the
panel
is
of
the
pushtoresettype
andisclearlv
marked
as
toitsfunction
and
amperage.Circuit
prorisions
have
been
included
to handlea fullcomplementof
communicationand
navigational
equlpment.
Standard
electricalaccessories
include a starter.an electric fuel pump. an audible stall
warning
indicator,
fuel
gauges,
ammeter.
and
annunciator
panel*.
T|e alnunciator
panel*
includes
alternator
and
low
oil pressure indicator
lights.
When
the
optional
gyro s)'stem
is installed.
the urnunciator
partel
also
includesa low vacuum
indicator
light. Theannunciator
panel
lightsare
provided
only asa warning
to thepilot that asystemmay
not be
operating
properly,
andthat heshouldcheckand
monitor theapplicablesystem
gauge
to
determine
wltenor if any
necessaryaction
is
required.
The system
alsoprovides
for such optional electrical
accessoriesasadditionallights
and
gallges,
a
heated
pitot head,
attdcommunication
and
navigational
equipment.
The master switch is a split rocker switch. One sideof the switch is the battery side
("BAT") andthe otheris the
alternator
side
("ALT"). Henceforth,the
words
"masterswitch"
Irsedin this
manual
will mean
both "BAT" and
"ALT" switches andtheyareto bedepressed
simultaneously
to OFF orON as
directed.
Primary electricalpower is provided by the 14 volt 60 amp alternator.The alternator
system
offersmany advantages
overthe generator
system
both in operationand maintenance.
T|e main
advantage
isfull electrical
power
output at lowerengine
RPM.Thisprovides improved
radio and electrical
equipment
operation
andincreased
battery
life by reducingbatteryload.
Thiswill make
coldweather
starting
easier.
Secondary
electrical
power
is
provided
by thestandard
or optiotral
battery.
Unlike previous generatorsystems,
the ammeter as installed does not show battery
discharge:
rather.
it indicates
the electrical
load on tlte alternatorin amperes.
With all the
electrical
equipment
off and
themasterswitch
on. theammeter
will indicatethe
charging
rate
of tlte
battery.
Aseach
electrical
unitisswitched
ott.
theammeter
will indicatethetotalampere
clrawof all the urrits
including
the batter1,.
For exantple.
the maximum
continuousloadfor
1ig|t flight with radios
on is abont30 amperes.
This 30 ampere
value
plus
approximately2
amperes
for a fully charged
battery
will appearcotrtiltuously
under
thesetlightconditions.
The
amopnt of current showlr
on the ammeter
will tell inrmediately
if tlte alternatcr systemis
operating
normally.
asthe amount
of current
showrr
should
equal
thetotalamperagedrawnb1'
the
electrical
equipmetrt
whichisoperating.
If 1c outpgt is indicated
on the ammeter
dttring
fligltt.redttce
the electricalload b1'
turlilg off allunnecessary
electrical
eqtripment.
C'lreck
boththe 5 amperefieldbreaker
andtlte
60 ampere
outpr,rt
breaker
andreset
if open.
If neithc'r
circuit
breaker
is
open.tttrnthe
"AL'I"
srvitch
off for I second
to resettheovervoltage
relav.
If thc amntetercontinues
to indicate
no
output.
maintain
mhimum electncal
loadand
termirtate
the
flight
assooll
as
practical.
Maintenance
ou the alternator
shouldprove to be a minor factor. Shouldservice
be
required.
contact
the
local
Piper
Dealer.
*Serial
nos.7515001
and
up
AIRPLANE
AND
SYSTEMS
REVISED:
APR|l.
6.1979
2-t
0

CHEROKEEWARRIOR
STARTER
A ACCESSORIES ALTERNATOR
FIELD
{STARTER
SOLENOID
Y,CABIN
LIGHT
MA9TER
SOLENOID
---_l
EXTERNAL
POWER
RECEPTACLE
RELAYEN€RGIZING
CIRCUIT
AMMT
TFR ( )HASIER
5Wt
ICH
t- t- - |
19 l
t--
! ALTEENATOR
. SOURCE-POWER
Alternator
andStarter
Schematic
(Ser.
Nos.741
5001
through
7415731)
NRPI.ANE AND SYSTEMS
REVISED:JLJhtE
14.197
42-tl