Piper Cherokee SIX 300 Quick setup guide

TE
CHEROKEE
SIX
3OO
INFORMATION
MANUAL
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il

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a1h"{o CHEROKEE
SIX3OO
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af j- INFORMATION
--/ MANUAL
Cherokee
Six 3OO
PA-32-300
HANDBOOKPARTNO.
761
-559

A complete or partial replacement of this manual, Part No.
7
61 559, may beobtained
only from Piper
Customer
Services.
Publishedby
PUBLICATIONS
DEPARTMENT
Piper
AircraftCorporation
761
5s9
Issued:
July1973
u

APPLICABILITY
The
aircraft
serial
numbereligibility
bracket
for application
of this
manual
is
32-7aa0001
rhrough
32-7640130.
Thespecific
application
of this
manual
islimited to thePiper
PA-32-300
modelairplane
designatedby
serialnumber
andregistration
numberon
thebackofthetitle
page
of this
manual.
This
manualcannotbe
usedfor operational
purposes
unlesskeptin acurrent
status.
REVISIONS
Theinformationcompiledin the
Pilot'sOperatingManual
will bekeptcurrent
by revisions
distributed
to the
airplane
owners.
Revision
material will consist of information necessary
to updatethe text of the present
manual
and/orto add
informationto coveraddedairplaneequipment.
I. Revisions
Revisionswill be distributedwhenevernecessary as completepagereplacementsor
additionsand strall
beinsertedinto themanualin accordance
with theinstructions
given
below:
l. Revision
pages
will replace
onlypages
with thesamepage
number.
2. Insert
all additional
pages
in proper
numerical
orderwithin eachsection.
3. Pagenumbersfollowedby a smalllettershall beinsertedin direct
sequence
withthe
same
common
numbered
page.
II. Identificationof Revised
Material
Revised
text and
illustrations
shall
beindicatedby ablackvertical
linealongtheleft hand
margrn
of the page,
oppositerevised,
addedor deleted
material.
A line oppositethe page
number or sectiontitle and printing date, will indicatethat.the text or illustrationwas
unchangedbut materialwasrelocatedto adifferent page
or that anentire
page
was
added.
Black
lines
will indicateonly current revisions
with changesandadditions to ordeletions
of existing text and illustrations.
Changesin capitalization,spelling,
punctuation
or thephysical
locationof material
onapage
will notbeidentified
by symbols.
III. OriginalPagesIssued
Theoriginal
pages
issuedfor thismanual
prior to revision
are
given
below:
l-l through 14,2-1 through 2-19,3-l through
3-18,
4-l through +7,5-1 through5-30,
7-l through7-12,8-lthrough8-2,9-l through
9-12,
lGl through10-15.
ltr

TABLE
(lF
C(II{TEI{TS
GE}IERAISPECIFICATIO}IS
DESCRIPTI(I}I
.AIRPLAIIEA}ID
SYSTEMS
AIRPLA]IE
FUGHIMAIIUAI
T.A.A.
APPR(IYED
EilIERGE}ICY
PROCEDffiES
I.A.A.
APPROYEII
EMERGENCY
PROCEDURES
ITHGHT
A}ID
BAtAilCE
L(lADtitG
lilsTRucn(Iils
OPERATINO
INSTRIICTIONS
(lPilATING
TIPS
PERF(IRMAIICE
CHARTS
HAilDLI}IG
A}IDSERYICING

GEltERAt
SPECtHCATt0ItS
Performance l-l
Weights l-2
Power
Plant . 1-2
Fueland
Oil . . l-2
BaggageArea l-2
Dimensions l-3
Landing
Gear l-3
3-View l-4

CHEROKEE
SIX.3OO
GENERALSPECIFICATIONS
PERFORMANCE
Publishedftguresare for standard
airplanes
flown at gross
weight under standard
:c;rditions
at sea
levelunless
otherwisestated.Performance
for a specificairplane
mayvary
;rom published
figures
depending
upon the equipment
installed,
the conditions
of engines,
airplane
and equipment,atmosphericconditions and piloting technique.
Each
performance
figure
below
issubject to thesame conditionsas
onthecorresponding
performance
chart
from
which
it istaken
in the
Performance
Charts
Section.
GROSS
I{EIGHTS 3400 2900
TakeoffGroundRun,l0 o
flaps,
sea
level
(ft) 1050 7
50
TakeoffDistanceOver
5Gft Obstacle,
l0 o
flaps,
sealevel
(ft) I500 I200
BestRate
ofClimbSpeed
(mpnl 105 100
Rateof Climb
(ft per
min) 1050 1350
Best
Angle
of Climb
Speed
(mph) 95
Max
Speed,sealevel
(mph) l?4* 175*
Max
Speed
Optimum
Altitude,8,300
ft,757o
power(TAS)
(mph) 168* l7l*
Service
Ceiline
(ft) 16,250 20,000
Absolute
Ceiling
(ft) 18,000 21.500
CruiseSpeed
atBestPowerMixture
(mph)
657o
Power,
I1,500ft
55%
power,
15,000
ft
RangeatBest
Power
Mixture
(mi1**
7
5%
power,
8,000
ft
657o
power,
I 1,500
ft
55%
power,
15,000ft
Cruise
Speed
atBest
Economy
Mixture
(mph)
757o
power,
8,000
ft
657o
power,
I 1,400 ft
5570
power,
15,000ft
Range
atBest
Economy
Mixture
(mi;**
7
5%
power,
8,000ft
657o
power,
I 1,400
ft
55%
power,
15,000
ft
StallingSpeed,flaps
down,
(CAS)
(mph)
Stalling
Speed,flaps
up,
(CAS)
(mph)
LandingRoll,flaps
down,sea
level
(ft)
LandingDistance
Over5&ft Obstacle,
sea
level
(ft)
*The speedstatediswith optionalwheel
fairings
installed.
Subtract
3mph
not installed.
**No reserve.
GEMRAL SPECIFICATIONS
ISSUED:JULY 12,1973
t63
155 t67
163
780 779
845 850
905 935
t66 169
159 165
149 t57
850 865
945 980
1030 1080
63 s8
7r 66
630 540
1000 850
if wheel fairings are
1-1

CHEROKEE
SIX.3OO
GROSS
WEIGHTS
WEIGHTS
Standard
Empty
Weieht
(lbs)
Maximum
Useful
Load
(lbs)
POWER
PLANT
Engine.Lycoming
Rated
Horsepower
Rated
Speed
(rpm)
Bore
(inches)
Stroke
(inches)
Displacement
(cubic
inches)
Compression
Ratio
Dry Weight
(pounds)
'' Propeller (Standard)
(Optional)*
PropellerDiameter
(inches)
(Standard)
(Optional)
FUEL AND OIL
FuelCapacity
(inboard)(U.S.
gal)
WithStandard Auxiliary(U.S.
gal)
Oil Capacity
(U.S.
qts)
Fuel,
AviationGrade
(minoctane)
BAGGAGE
MaximumBaggage
(lbs)
BaggageSpace
(cubicft)
Baggage
DoorSize
(in.)
*Serial
nos.
7440001
3400 2900
t824
1516
(Serial
nos.7440O0 1through7
6
4Q06
5
and 764.046:7
through
76400',7r)rO-s4GKlAs
(serial
nos.
7640066,7640072
and
up)
IO-54SKlG5
300
2700
).lz)
4.3',15
541.5
8'7:
I
45'l
HC-C2YK-I
( )|847
s-4
orHC{2YK-r( )
|8475D-4
orHC-C2YK-I
( )F/F847
5D-4
HC{2YK-I( )/847sR4
orHC{2YK-I( )F/F8475R-0
80
84
1824
to16
50
84
t2
100/l
3o
Forward
100
8
16x22
GENERAL SPECMCATIONS
REVISED:FEBRUARY 2, 1916
Aft
100
20
thru7540188only

CHEROKEE
SD(-3OO
.ll
f
ir DIMENSIONS
WingSpan
(ft)
Wing
Area
(sqft)
WingLoading(lbs persqft)
Length(ft)
Height (ft)
PowerLoading(lbs) per hp)
LANDING GEAR
Wheel
Base
(ft)
Wheel
Tread
(ft)
TirePressure
(lbs)
GENERAL SPECIFICATIONS
ISSUED:
JULY l2,t97g
Nose
Main
32.8
17
4.5
19.5
27.7
8.2
I1.3
7.8
10.6
28-30
35-40
1-3

CHEROKEE
SIX.3OO
32'8.t5"
I ,,0.,r'
GENERAL SPECIFICATIONS
ISSUED:
JULY 12.1973
t4

DESCRIPTI(III
AIRPLAIIEAllDSYSTEI'IS
TheAirplane .
Airframe
Engine
andPropeller
InductionSystem .. .;
Landing
Gear
FlightControls
FuelSystem
Electrical
System
Vacuum
System
InstrumentPanel
Pitot-StaticSystem
Heating
and
Ventilating
System
Cabin
Features
Baggage
Area
StallWarning
Finish
Air Conditioning
Piper
External
Power
2-l
2-l
2-l
aa
L-L
2-4
2-6
a1
2-9
2-t3
2-13
2-t5
2-15
2-r5
2-r8
2-t8
2-18
2-r8
2-t9
2-i

CHEROKEE
SIX. 3OO
DESCRIPTION
AIRPLANEAND SYSTEMS
THEAIRPLANE
The PA-32-300
is a six-place
(seventh
seatoptional),
single-engine,low-wing.
all metal
monoplane.Removable
seats
give
the
airplane
a
wide
range
ofcargo
andpassenger
loading
options.
Its
large
capacity,
combined
withan
economical
and
powerful
fuel
injected
300horsepowerengine.
rnakes
thisCherokeea versatile
airplane
for personal or commercial
use.
AIRFRAME
Exceptforthe
tubularsteelengine
mount,steel
landinggear
struts,
other
miscellaneoussteel
parts,
and
the
dent
resistantfiberglassextremities
-cowling
and
tips
ofwings
and
tailsurfaces
-the
basicairframe
isof aluminumalloy.
Thefuselage
is
aconventional
semi-monocoque
structurewitha
cabindoor
onthe
right
front
anda cargoandpassenger dooron theleftrear.
Thewingsareattached
to each
side
of thefuselage
by theinsertion'ofthebutt ends
of the
mainspars
intoa sparboxcarry-throughwhichisanintegral partof the
fuselage
structure.This
provides,
ineffect,
acontinuous main
sparwith splices
ateachside
ofthe
fuselage.
There
arc
also
foreandaft attachmentsat therear
spar
andat an auxiliary
front spar.
. The
wing
airfoil
section
is
alaminarflowtype,
NACA65r4l5 with
a maximum
thickness
at
about
40Vo
aftof theleadingedge.
Theempennageconsists
of the fin,the
stabilator,andthestabilator
trim tab.
ENGINE
AND PROPELLER
The LycominglO-5{0'KlA5 (Serial
nos.7440001 through7640065and 7640067
through
'7ffi71 orlO-540-KlG5
(Serial
nos.
764+Cf,66,7640072and
up)
engineinstalled
inthe
PA-32'300
is
rated
at 300horsepower
at2700
rpm.Thisenginehas
a
compression
ratio
of8.7
to Iand required
100/
130
minimum
octanefuel.
The
engineis
equippedwitha
gearcd
starter,a
60amperealternator,
dualmagnetos,vacuum
pump
drive,
a vane-type
fuelpump,
andfuelinjection.
Theexhaustsystemconsistsofdualexhauststacks
routed
toasingleheavy
gauge
stainless
steel
muffler
onserialnumbers7440001through 7540188.
On
later
modelsindividual
exhaust
pipes
are
routed
in pairs
tothree
heavy
gauge
stainlesssteelmufflers.
Exhaust
gases
are
routedoverboard
at
theundersideof the
engine
cowling.
Themuffler
(ormufflers)
are
surrounded
byashroudwhich
provides
heat
for the cabinandfor windshield
defrosting.
Cowlingon theCherokee
Six isdesigned
to cooltheengine
in all normalflightconditions.
including
protracted
climb,
without
theuseof cowl
flapsor coolingflanges.
AIRPLANE AND SYSTEMS
REVfSED:
FEBRUARY
2. 1976 2-l

CHEROKEESIX.3OO
The
constant
speed
propeller
isaHartzell
HC-C2YK-I ( )F/
F8475D-4
with
adiameter
of
80
inches.The
propeller
is
controlled
bya
governor
mounted
at
theleftforward
side
ofthecrankcase
.
Thegovernor isoperatedbya cable
from thepower
control
quadrant.
Thepower
control
quadrant
located
in thelowercenter
of theinstrumentpanel
includes
throttle,
mixture.and
propeller
controls.A friction
lockonthe
right
sideofthe
quadrant
prevents
creeping
of the
controls.
Inaddition.
the
mixturecontrolhas
alock* to prevent
activationofthe
mixturecontrolinsteadof the
pitch
control.
For information ontheleaning procedure,
see
the
Avco-Lycoming
Operator's
Manual.
INDUCTION
SYSTEM
On SerialNumbers
74y',0001
through7540188,
theInduction
Air for theengineenters
an
opening
inthe
nose
cowlbelow
the
propeller
and
is
picked
upbya
large
air
duct.
Theair
is
directed
through
a filterandon to the
servo
regulator.
Shouldthefilter becomeblocked,
aspringJoaded
door
inthe airbox
betweenthe
lilterand
theservo
regulatoropensautomatically.The
door
may
alsobeopened
manuallybya controllocated
ontherightsideof thequadrant.
,,: QnSerialNumbers764000
| andup,
aninductionscoop is
locatedontheleft sideofthe lower
cbwl.An intakeairboxis
attached
tothe inside
ofthecowl
adjacent
tothe
airfilter
box.Thefilter
box is located at the aft endof the induction
scoop.
Access
to thefilter isgained
through
a
detachable
platelocated
on the outside
of the lowercowl. Theintake air box incorporates
a
manuallyoperated
two-way
valve
designed
toallowinduction
aireithertopass through
thefilter
or
to bypass
thefilter andsupply
heatedair directlyto the
engine.
Alternate
airselectioninsures
induction
airflowshouldthe
filterbecome
blocked.
Since
the
air
isheated,thealternateair system
offers
protection
againstinduction
system
blockagecaused
by
snow
or freezing
rain, or by the freezing
of moisture
accumulated
in the induction
air filter.
Alternate
air isunfiltered;therefore,
it should
notbeusedduring
ground
operationwhen
dust
or
othercontaminantsmightenter
the system.
Theprimary(through
thefilter)induction
source
should
always
beusedfor takeoffs.
Onserial
numbers
7640001
andup,the
controlis
operated
by
pressing
theknobto theleftto clear
theretaining gateandthen
movedin the
desired
direction.
TheBendix
RSA-lOEDI type
fuel
injection
systemconsists
ofaservoregulator which
meters
fuelflow in proportion
to airflowto theengine,giving
theproper
fuel-air
mixture
at all engine
speeds,andafuelflowdividerwhich
receives
themeteredfuel
and
accuratelydivides
thefuel
flow
amongtheindividual
cylinderfuelnozzles.
A combinationfuel flowindicatorand
manifold
pressuregauge
isinstalled
in
the
left
sideofthe
instrument
panel.
Thefuelflow indicator
isconnected to the
fuel
flowdividerand
monitors
fuel
pressure.
The
instrument
converts
fuel
pressure
toan
accurate
indication
offuel flowingallonsper
hourandpercentage of cruise power.
fSerial
nos.7540001and
up
AIRPLANE AND SYSTEMS
REYISED:
JULY 17.l97S
2-2

CHEROKEE
SIX.3OO
ThrottleQuadrant
and
Console
AIRPLANE AND SYSTEMS
REVISED:
ruLY 17,1975
oN sER.NOS.
7640m1
AND UP,
THE CONTROL
KNOB
MUSTBE
PRESSED
TO THE LEFT TO
CLEAR THE RETAINING
GATE
PRIOR TO SELECTING THE
DESIRED
POSITION.
:-_------:::::\
fir--Em

CHEROKEESIX.3OO
LANDING GEAR
All three
landing
gear
use
Cleveland
6.00x 6wheels. Themain
gear
havebrakedrums
and
Cleveland
doubledischydrualic
brakeassemblies.
Thenose
wheel
carries
a6.00
x 6fouror six
ply tireandthemain gear
use
6.00
x 6six
ply tires.All threetiresaretube
type.
Thenosegear
is steerableusinga combinationof full rudder pedal
traveland
brakes.
The
nose
gear
canbe tumed 24oeach
sideof center. A spring device
is incorporatedin therudder
pedal
torquetube
assemblyto aid
inrudder centeringandto provide
rudder
trim.Thenose
gear
alsoincludesa
shimmy
dampener.
Theoleostruts,are of the air-oiltype.The
normalextensions,
arc,3-l
l4 inches.for the
nose
gear
and4l 12inches
for themain
gear
under
normal
static
load
(empg weight
of airplane
plus
full fueland
oil).
Thebrakesareoperatedby toepedals
attachedto theleftrudder
pedals
or byahandlever
and mastercylinder locatedbelow and behindthe left center of the instrumentsub-panel.
Optional
toe brakes
areavailable for the right rudder
pedals.
Hydraulic
cylindenarelocated
above
each
pedal
andadjacentto the handlever.
The brake
fluid reservoiris on the top left
front of the fue wall. The parkingbrakeis incorporatedin the lever
brakeandis engagedby
p'uling
backon thelever
and
depressing
theknobattached
to thetopof the handle.
Torelease
theparking
brake,
pull back
on thebrake
leverto disengagethecatch;
then
allow
the
handle
to
sri'ing
forward.
NRPI.ANE AND SYSTEMS
REVISED:NOVEMBER
6, 197424

;/
\\-i-\
CHEROKEE
SIX-3OO
MainWheel
Assemblv
AIRPLAI{E AND SYSTEMS
ISSUED:
JULY 12,1973

CHEROKEE
SIx.3OO
Console
FUGHT CONTROLS
Dualcontrols,with a cablesystem
between
the controls
and
the surfaces, are
installed
as
standard
equipment.
The horizontaltail isof theall-movable slabtype (stabilator).
Thestabilator
provides
extra
stabilityand
controllability
with less
size,
drag,andweight
than
conventionaltailsurfaces.
An anti-servotab which alsoacts
asalongitudinaltrim tab, is locatedon the horizontal
tail.Thistailisactuatedbyacontrol
mounted
onthecontroltunnel
between
the
front seats.
Theailerons are
provided
with adifferentialactionwhich tendsto eliminate
adverse
yawin
turningmaneuverand
to reduce
theamountof coordinationrequired
innormalfurns.
Theflapsaremanually
operated,
balanced
for light operatingforces,
andspring-loaded
to
retum to theup position.A past-center
lock incorporatedin the actuating
linkage
holdstheflap
whenit isin theup positionsothat it maybeusedasastepon theright side.Since
theflapwill
not supporta steploadexcept
in the full up position,
it should
becompletelyretracted
when
theairplaneis on the ground.
Theflaps
have
three
extended
positions,
10,25,and
40degrees.
AIRPI.AI{E AI{D SYSTEMS
ISSUED:
JULY 12.1973
24

CHEROKEE
SIX
. 3OO
FUEL SYSTEM
The standard fuel capacity
of theCherokee
Sixis 84gallons,
allof whichisusableexcept
for approximatelyonepint in eachof thefour tanks.
Thetwomaininboard
tanks,
which
hold
25 gallons
each,ate attached to the wing structure
with screwsand nut plates
andcanbe
removedeasilyfor service
or inspection.The tip tanksareconstructed
of resin-impregnated
fiberglass,
andeach
one
holds
l7 gallons.
Whenusingless
than
the
standard
84
gallon
capacity
ofthetanks,fuel should
be
distributed
equally
between
each
side.The
tiptanks
shouldalways
befilledfirst,
and
fuel
from
themain
tanks
shouldbe
used
first.
All weight
in excess of 3ll2 pounds
must
be
in fuel weight
only.
Thefuelselectorcontrol
is
locatedbelow
the
center
of theinstrument
panel
onthesloping
face
of the controltunnel.It has
fivepositions,
one
position
correspondingto each of thefour
tanks
plus
anOFFposition.
To avoidthe accumulation
of water
and
sediment,
thefuelsystemshould bedrained
daily
prior to first flight and after refueling.Eachtank is equipped
with anindividualquick drain
located
at thelowerinboardrear
comer
of thetank. The
fuelstrainerand
asystem
quick
drain
valve
arelocatedin the fuselageat thelowest
p<irint
of thefuelsystem. It isimportant
thatthe
fuelsystembe
drained
in thefollowing
manner:
l. Draineach
tank throughits individual
quick drainlocated
at thelowerinboard rear
corner
of the tank,making
sure
thatenoughfuelhas
flowedto ensure
theremorral of
allwater
and
sediment.
2. Placea containerbeneaththe fuel sump
drainoutletlocatedunderthefuselage.
A
special
containerisfumishedfor thisoperation.
3. Drainthefuel strainerby pressing downon the lever
locatedontherightside
o,fthe
cabinon the forward
edge
of thewingspar
housing.
Movethe selector
throughthe
following
sequence:
OFF position, left tip, left main,
right main, and
righttip while
draining the strainer.
Make surethat enoughfuel hasflowed to drain the fuel line
betweeneachtankoutlet andthefuel strainer,
aswell
as
thestrainer itself.
Withfull
fuel tanks,
it will takeapproximately
II seconds
to drainall the fuelin one
of the
fuellinesfrom the tip tankto the strainer,
andapproximately6 secondsto drain
all
of the fuel from the line from eithermain tank to the fuel strainer. When
thetanks
are
less
thanfull, it will takeafew seconds longer.
4. Examine
the contentsof thecontainer
placed
under
thefuelsumpdrainoutlet.
When
the fuel flow is free of water and sediment,closethe drain and disposeof the
contentsof thebottle.
CAUTION
Whendrainingfuel, care
should
be takento ensure that no fre
hazard
exists
beforestarting
the
engine.
After usingthe undeneat quick drain, checkfrom the outsideto makesurethat it has
closed
completely
and
isnot leaking.
AIRPLANE A}.IDSYSTEMS
REVISED:
DECEMBER
15.l9?t L7

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FLOW
DISTRIBUTION
FUEL
NOZZLES
FUELINJECTOR
THROTTLE
LEFTTIP TANK LEFTMAINTANK
VENT
FUEL y'
PRESSURE
FUEL
SELECTOR
T
RIGHT
MAINTANK RIGHTTIP TANK
GAUGE FUEL
FUEL
SYSTEM
DRAIN
LEVER
SELECTOR
CONTROL
/ FUEL
TANK
TSELECTOR
VALVE
FUEL
QUANTITY
GAUGES

CHEROKEE
SIX
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FuelDrain Lever
Fuel
quantitygauges
foreach
of
the
four
tanks
are
located
in
theengine
l3uge
clusteron
the
left
side
oftheinstrument
panel.
Afuel
pressure
indictorisalso
incorporated
intheengine
gauge
cluster.
An electric
fuelpumpisprovided for use in case
of failure
of theengine
driven
pump.
The
electric
pump
operates
fromasingleswitch
and
independent
circuit
protector.
Itshouldbe
ONfor
all takeoffs
andlandings.
ELECTRICALSYSTEM
Thel4-voltelectricalsystem
includes
a l2-voltbrtteryfor starting
andto backupalternator
output.Electrical
power
issupplied
bya60
ampere
rlternaior.
Thebattery,
a
master
switch
relay,a
voltage
regulator
andan overvoltage
relayarelocated
beneath
thefloor of the
forward
baggage
compartnient,
and
access
isobtainedby removing
thefloor.
Electricelswitches
arelocated
ona panel
to the
pilot's
leftand
allcircuitbreakersare
onthe
lower
rightinstrument
panel
behind
adecorative
door.
Twothumb-wheel
rheostatswitches
tothe
leftof thecircuitbreakers
controlthenavigation
lights
andthe
intensity
of theinstrument
panel
lights.
AIRPLANE AND SYSTEMS
REVISED:
JUNE20,1974
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