PIPER AIRCRAFT CORPORATION PA-28RT

PIPER AIRCRAFT CORPORATION
SECTION7
PA-28RT-2OIT,
TURBO ARROW IV DESCRIPTION
/OPERATION
SECTION 7
DESCRIPTION AND OPERATION
OF THf, AIRPLANE AND ITS SYTEMS
7.I THE AIRPLANE
The Turbo Arrow IV is a single engine, retractablelanding gear, all
metal airplane featuring the tail surfacesin a "T" configuration. It has
seatingfor up to four occupants,a 200 pound luggagecompartment,and a
turbocharged200 HP engine.
7.3 AIRFRAME
With the exception of the steel engine mount, the landing gear, miscellaneoussteel parts, the cowling, and the lightweight plastic extremities
{tips of wings, tail fin, rudder and stabilator), the basic airframe is of
aluminum alloy. Aerobatics are prohibited in this airplane since the
structure is not designedfor aerobaticioads.
The fuselageis a semi-monocoquestructure.Thereis a front door on the
right side. A cargo door is installed aft of the rear seat.
The wing is of a conventional design semi-taperedand employs a
laminar flow NACA 652415 airfoil section.The main spar is located at
approximately 4070 of the chord aft of the leading edge. The wings are
attachedto the fuselageby the insertion of the butt ends of the spar into a
spar box carry-through,which is an integral part of the fuselagestructure.
The bolting ofthe spar endsinto the sparbox carry-throughstructure,which
is located under the aft seats,provides in effect a continuous main spar. The
wings are also attached fore and aft of the main spar by an auxiliary front
spar and a rear spar. The rear spar, in addition to taking torque and drag
loads, provides a mount for flaps and ailerons. The four-position wing flaps
are mechanically controlled by a handle located between the front seats.
When fully retracted, the right flap locks into place to provide a step for
cabin entry. Each wing contains one fuel tank.
ISSUED: NOVEMBER 30. 1978
REPORT:VB-940
7-l
SECTION7
PIPER AIRCRAFT CORPORATION
DESCRIPTTON/OPERATION PA-28RT-2OIT,
TURBO ARROW IV
A vertical stabilizer,an all-movablehorizontal stabilator,and a rudder
make up the empennage.The stabilator,which is mounted on top of the fin,
incorporatesan anti-servotab which improves longitudinal stability and
provides longitudinal trim. This tab moves in the same direction as the
stabilator, but with increasedtravel.
7.5 ENGINE AND PROPELLER
The engine is a six cylinder, horizontally opposed, fuel injected,turbocharged engine, rated at 200 horsepower at 2575 RPM and 4l inches MAP
from sealevel to 12,000feet density altitude. It is equippedwith an oil cooler
with a low temperature bypass system and engine mounted oil filter. A
winterization plate is provided to restrict air during winter operation. (See
Winterizationin Handling and ServicingSection.)The turbochargercontrol
system is a fixed, ground adjustable orifice ("fixed wastegate"), and is
adjüsted to provide 4l inches MAP at full throttle at 12,000feet density
altitude. Throttle position controls engine power and no separateturbocharger control system is utilized. An overboost valve prevents manifold
pressurefrom exceeding42 inches Hg. should the throttle inadvertently be
opened too far below 12,000 feet density altitude. Should this occur, the
amber'overboost" warning light in the annunciator panel will illuminate.
The engine induction system is provided with two independent air
sources,an induction air filter box with filter, and interconnectingducting.
The primary air inlet is located above No. I cylinder (right rear) in the engine
rear baffle. Induction air enters at this point and is ducted to the induction
filter box, thru the filter and is further ducted to the turbocharger compressorinlet. The induction air filter box incorporates an alternateair valve.
This valve may be manually operated(opened)with the alternateair control,
allowing air to bypass the filter, supplying heated air directly to the compressor inlet. Should the primary air source become blocked, the alternate
air valve will open automatically due to the sucking action of the turbocharger compressor.The heatedair provided by the alternate air sourcewill
protect against induction system blockage caused by snow or freezing rain,
or by the freezing of moisture accumulated in the induction air filter. The
alternate air is unfiltered and therefore should not be used during ground
operation when dust or other contaminates might enter the system. The
primary (filtered air) induction source should always be used for takeoff.
REPORT:VB-940
7-2
ISSUED:NOVEMBER 30. 1978
SECTION7
PIPER AIRCRAFT CORPORATION
OPERATION
IV
DES
CRIPTION
/
TURBO ARROW
PA-28RT-2OIT.
A RayJay turbocharger on the engineis operatedby the engineexhaust
gases.The exhaust gasesdrive a turbine wheel which is coaxial with a comp..tto. wheel. Induction air entering the compressorwheel,iscompressed
änd delivered to the engineinduction distribution system and henceto each
cylinder. The amount of induction air compressionis a function of engine
power - low power, low compression;high power, higher compression'Any
äxcessiveprössure(and flow) is expelled by the overboost valve discussed
previously.
The fuel injection system incorporates a metering system which
measuresthe rate at which turbocharged air is being used by the engine and
dispensesfuel to the cylinders proportionally. Fuel is suppliedto the injector
pump at a greater rate than the enginerequires.The fuel injection systemis a
"continuous flow" tYPe.
A combination fuel flow indicator and manifold pressure gauge is
installed in the left side of the instrument panel. The fuel flow indicator is
connected to the fuel flow divider and monitors fuel pressure.The instrument converts fuel pressure to an approximate indication of fuel flow in
gallons per hour and percentageof cruise power.
To obtain maximum efficiency and time from the engine, follow the
procedures recommended in the Teledyne continental operator's Manual
provided with the airplane.
The Hartzell constant speed propeller is controlled by a governor
mounted on the left forward side of the crankcase.The governor is controlled by a cable from the power control quadrant. A choice of a two bladed
(standard) propeller or a three bladed (optional) propeller is offered.
ISSUED: NOVEMBER 30. 19?t
REPORT: VB-940
7-3
SECTION7
PIPER AIRCRAFT CORPORATION
DESCRIPTION/OPERATION PA-2tRT.2OIT,TURBO ARROW IV
::t
{
AIRCRAFTEOUIPPED
WITH
BACKUPGEAREXTENDER
CoNTROLQUADRANTAND CONSOLE
Figure7-l
REPORT:YB.9{0
71
ISSUED:NOVEMBER30,l97t
REYISED:AUGUST15,tgtd
PIPER AIRCRAFT CORPORATION
SECTION 7
PA.28RT.2O1T,
TURBO ARROW IV DESCRIPTION/OPERATION
7.7 ENGINE CONTROLS
F-nginecontrols consistof a throttle control. a propellercontrol and a
'fhese
mixture controi lever,
controlsare locatedon the control quadranton
t h e l o w e r c e n t e r o f t h e i n s t r u m e n tp a n e l ( F i g u r e 7 - l ) w h e r e t h e y a r e
a c c e s s i b ltra b o i f r t l r ep i l o t a n d t h e c o p i l o t .T h e c o n t r o l su t i l i z et e f l o n - l i n e d
c o n t r o i c a b l e st c r e c l u c ef r i c t i o n a n d b i n d i n g .
l he throttle levrl ii;usedtciadjustthe manifold pressure.lt incorporates
a gear up *,arning horri srvitchwhich is activatedduring the last portion of
t r a v e l o i t h e t h r o t r l e l e v i i -t o t h e l o w p o w e r p o s i t i o r r I. f t h e l a n d i n gg e a r i s l
n o t i o i k e d d c - r w rt:l.' , eh c r n w i l l s o r , r n d
u n t i l t h e g e a ri s d o w n a r r dl o c k e do r l
u n t i l t h e p o u , e rs e t r i n gi s i n c r e a s e dT. h i s i s a s ä f e t l , f e a t u r et c w a r n o f a n l
i r r a d v e r t e nFl e a ru [ ' l a n d r n p
"i'lrepropeller
control leve; is used to adjust the propellersrreedfiorn
high RPhato iow RPM.
T'he nrixture control lever is used to adiust the air tc fuel ratio. The
enginerssliut down by the placingof the mixture control leverin the full lean
position. In addition, the mixture controi hasa lock to preventactivationof
ttre rnixture control insteaCof the pitch control. For information on the
leaning procedure.seethe Continental Operator's Manual.
The friction adjustmentlever on the right side of the control quadrant
may be adjusted to increaseor decreasethe friction holding the throttle,
propeller. and mixture controls in a selectedposition.
I
The alternateair control is locatedto the right of the control quadrant.
When the alternateair lever is in the up, or closed,position the engineis
operatingon filtered air; when the lever is in the down, or open,positionthe
engine is operating on unfiltered, heatedair (refer to Figure 7-l).
ISSUED: NOVEMBER 30, 197t
REVISED: FEBRUARY 6, 1979
REPORT:VB-940
7_5
SECTION 7
PIPER AIRCRAFT CORPORATION
DESCRIPTION/ OPERATION PA.28RT.2OIT.TURBO ARROW IV
lo
Rp[ 25
AIRCRAFTEOUIPPED
WITH
BACKUPGEAREXTENDER
LANDING GEAR SELECTOR
Figure7-3
7.9 LANDING GEAR
TheTurbo Arrow IV isequippedwith a retractabletricyclelandinggear,
pump.
which is hydraulicallyactuatedby an electricallypoweredreversible
The pump is controlledby a selectorswitchon the instrumentpanelto the
left of the control quadrant(Figure7-3).The landinggearis retractedor
extendedin about sevenseconds.
Someaircraft also incorporatea pressuresensingdevicein the system
of gearselectorposition,dependingupon
which lowersthe gearregardless
Gearextensionis designed
airspeedand enginepower(propellerslipstream).
position,
at airspeedsbelow
is
in
the
up
the
selector
if
even
to occur,
approximately 103 KIAS with power off.The extensionspeedswill vary
fr-omapproximately78 KTS to approximately103 KIAS dependingon
powersettingS
and altitude.Thedevicealsopreventsthegearfrom retracting
approximately78 KTS with full power, though the
below
ät airspeeds
with reduced
selectoiswitchmay be in the up position.This speedincreases
REPORT:VF940
1-6
ISSUED:NOVEMBER30,l97t
REVISED:AUGUST15,19t6
SECTION 7
PIPER AIRCRAFT CORPORATION
PA-2tRT-201T,TURBO ARROW IV DESCRIPTION/ OPERATION
power and/or increasedaltitude. Manual overrideof the deviceis provided
by an emergencygear lever located betweenthe front seatsto the left ofthe
flap handle (refer to Figure 7-9). The sensingdeviceoperation is controlled
by differential air pressureacrossa flexible diaphragm which is mechanically
linked to a hydraulic valve and an electricalswitch which actuatesthe pump
motor. A high pressureand static air sourcefor actuating the diaphragm is
provided in a mast mounted on the left side of the fuselageabove the wing.
Any obstruction of the holes in this mast will causethe gear to extend. An
optional heated mast is available to alleviateobstruction in icing conditions.
The optional heated mast is turned on whenever the "PITOT HEAT" is
turned on.
IYARNING
Avoid ejectingobjectsout of the pilot storm
windowwhichcouldpossiblyent€ror obstruct
the holesin the mast.
The emergencygear lever,when placedin the raisedposition,can be
used to overridethe system,and gear positionis then controlledby the
Theemergency
selectorswitchregardless
of airspeed/power
combinations.
gearleveris providedwith a lockingdevicewhichmay be usedto lock the
overrideleverin the up position.The lock is locatedon theleft sidepanelof
the consolebelowthelevelof themanualoverridelever.To lock theoverride
leverin the up position,raisethe overrideleverto the full up positionand
push the pin in. A yellow warning light located below the gearselector
switch(Figure7-3)flashesto warnthepilot that theautomaticgearlowering
systemis disabled.The lock is spring-loadedto the off position to aid
To disengage
the lock raisethe overrideleverand release.
disengagement.
The leverwill returnto its normalpositionand theyellowflashinglight will
extinguish.The levermust also be lockedin the raised(up) positionwhen
gear-upstallsare practiced.
The emergencygear lever,when usedfor emergency
extensionof the
gear,manuallyreleases
hydraulicpressure
to permitthegearto free-fallwith
on the nosegear.The levermustbe heldin thedownward
springassistance
positionfor emergencyextension.
Gear down and locked positionsare indicatedby three greenlights
locatedbelowthe selector,and a red"WarningGearUnsafe'lightislocated
at the top of the panel.An all lightsout conditionindicatesthe gearis up.
The landinggearshouldnot be retractedabovea speedof I I I KIAS and
shouldnot be extendedabovea speedof 133KIAS.
ISSUED: NOVEMBER 30, 197t
REVISED: AUGUST 15, l9t6
REPORT:VB94l)
7-7
PIPER AIRCRAFT CORPORATION
SECTION 7
DESCRIPTION/OPERATION PA.2tRT.2OIT.TURBO ARROW IV
The main landing gear uses6.00 x 6 wheels.The main gear incorporate
brake drums and Cleveland singledisc hydraulic brake assemblies.The nose
wheel carries a 5.00 x 5 four ply tire and the main gear use 6'00 x 6 six ply
tires. All three tires are tube type.
A micro-switchin the throttle quadrant activatesa warning horn and
red "Warning Gear Unsafe" light under the following conditions:
(a) Gear up and power reduced below approximately 14 inches of
manifold pressure.
(b) On aircraft equipped with the backup gear extender, if the system
has extendedthe landing gear and the gearselectoris UP, with the
reducedbelow approximately l4 inches of manifold pressure.
(c) Gear selectorswitch "UP" while on the ground and throttle in
retarded position.
On aircraft which are NOT equippedwith the backup gearextenderan
additional switch is installed which activatesthe warning horn and light
wheneverthe flaps are extendedbeyond the approach position ( l0o) and the
landing gear are not down and locked.
The gear warning horn emits a 90 cycle per minute beepingsound in
contrast to the stall warning horn which emits a continuoussound.
The nose gear is steerablethrough a 30 degree arc each side of center
through the useof the rudder pedals.As the nosewheelretracts,the steering
linkage disengagesto reduce rudder pedal loads in flight. The nosewheel is
equippedwith a hydraulicshimmy dampenerto reducenosewheelshimmy'
Abungee assemblyis also included to reduce ground steeringeffort and to
dampen shocks and bumps during taxiing.
The oleo struts are of the air-oil type, with normal extensionbeing2.75t
.25 inches for the nose gear and 2.5 t .25 inches for the main gear under
normal static load (empty weight of airplane plus full fuel and oil).
The standard brake systemincludestoe brakes on the left and right set of
rudder pedals and a hand brake located below and near the center of the
instrum-entpanel. The toe brakes and the hand brake have individual brake
cylinders, but all cylindersuse a common reservoir.The parking brake is
incorporatedin the lever brake and is operatedby pulling bat on the lever
and depressingthe knob attachedto the top of the handle.To releasethe
parking brake, pull back on the brake lever;then allow the handleto swing
forward.
REPORT: VF940
7-t
ISSUED: NOVEMBER 30' l97t
REVISED: AUGUST 15, l9t6
PIPER AIRCRAFT CORPORATION
SECTION 7
PA.2tRT.2IIIT, TURBO ARROW IV DESCRIPTION/OPERATTON
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LANDING GEAR ELECTRTCAL SCHEMATIC
Figure7-5
ISSUED:NOVEMBER30,l97t
REWSED:AUGUST15,l9t6
REPORT:V&9{0
7-9
SECTION 7
PIPER AIRCRAFT CORPORATION
DESCRIPTION/OPERATION PA.28RT.2OIT,TURBO ARROW IV
PUiIPRISERVOIR
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WITH
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L A N D I N GG E A R HYDRAUI,TCSCHEMATIC
Fisure7-7
Rf,PORT: VB-940
?-10
ISS{JED:NOVEIltBf,R30, 1978
REV{SED:AUGIJST15.1986
PIPER AIRCRAFT CORPORATION
SECTION7
TT]RBOARROW IV DESCRIPTION/OPERATION
PA-2ERT-2O1T.
I
I
J
\
WITH
AIRCRAFTEOUIPPED
EACKUPGEAR EXTENDER
FLIGHT CONTROL CONSOLE
Figure 7-9
7.II FLIGHT CONTROLS
Dual flight controls are provided as standard equipment. A cable
system provides actuation of the control surfaceswhen the flight controls
are moved in their respectivedirections.
The horizontal surface (stabilator) is mounted atop the fin in a "T"
configuration and features a trim tab/servo mounted on the trailing edge.
This tab servesthe dual function ofproviding trim control and pitch control
forces, The trim function is controlled by a trim control wheel located on the
control consolebetweenthe two front seats(Figure 7-9). Rotating the wheel
forward gives nose down trim and rotation aft gives nose up trim.
The rudder is conventional in design and incorporates a rudder trim.
The trim mechanism is a spring-loadedrecenteringdevice. The trim control
is located on the right side of the pedestal below the throttle quadrant.
Turning the trim control clockwise gives nose right trim and
counterclockwise rotation gives nose left trim.
Manually controlled flaps are provided. They are extendedby a control
cable and are spring-loaded to the retracted (up) position. The control is
located between the two front seatson the control console. To extend th€
ISSUED: NOVEMBER 30, 1978
REVISED:AUGUST 15. l9t6
REPORT: VF940
7-ll
PIPER AIRCRAFT CORPORATION
SECTION 7
TURBO ARROW IV
DESCRIPTION/OPERATION PA-28RT-201T,
To
flapspull the handleup to the desiredflap settingof 10,25or 40degrees.
retract,depressthe button on the end of the handleand lowerthe control.
When extendingor retractingflaps,thereis a pitch changein the aircraft. This pitch changecan be correctedeither by stabilator trim or
increasedcontrolwheelforce. Whenthe flapsare in the retractedposition
the right flap, providedwith a over-centerlock mechanism,actsas a step'
NOTE
The right flap will supporta load only in the
fully retracted(up) position.Whenloadingand
makesuretheflapsarein
unloadingpassengers
the retracted(uP) Position.
7.T3 FUEL SYSTEM
The fuel systemwas designedwith simplicityin mind. lt incorporates
two fueltanks,onein eachwing containing38.5U.S'Gallons,givinga total
Eachtankisequipped
; capacityof 77gallons,of which72gallonsareusable.
whenthe
fuelremaining
I with a fillerneckindicatortab to aid in deterrnining
I tanksare not full. Usablecapacityto the bottomof the indicatortab is 25
I gallons.Theminimumfuelgradeis i00or l00LL AviationGrade.Thetanks
areattachedto the leadingedgeof thewingwith screwsandarean integral
The tanksare
part of the wing structure.This allowsremovalfor service.
the
bottomof the
protrudes
below
ventedindividuallyby a venttubewhich
should
bechecked
The
vents
tank.
of
each
corner
inboard
rear
wing at the
periodicallyto ascertainthat the vent is not obstructedand will allow free
passageof air.
Each fuel tank has an individual quick drain locatedat the bottom
a quickdrain,which
inboardrearcorner.Thefuel straineralsoincorporates
is locatedon the left lowerportion of thefirewall.Thequick drain protrudet
thru the cowlingto allow easydrainingof the fuel strainer.To avoid the
accumulationof water and sediment,the fuel tank sumps and strainer
shouldbe draineddaily prior to first flight and after refueling.
CAUTION
When draining fuel, careshould be taken to
ensurethat no fire hazardexistsbeforestarting
the engine.
REPORT:V&94O
7-t2
ISSUED:NOVEMBER30,l97t
REVISED:AUGUST22, l9t0
PIPER AIRCRAFT CORPORATION
SECTION 7
P A - 2 8 R T - 2 O I T ,T U R B O A R R O W I V D E S C R I P T I O N / O P E R A T I O N
-t
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i
Yrfinnm,ni
---i-,
sfl-rcr0R
Yil.Yr
j\
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I
üillfitn GAUGIS
FUEL SYSTEMSCHEMATIC
Figure7-l I
ISSUED: NOVEMBER 30, 1978
REPORT: VB-940
7-13
PIPER AIRCRAFT CORPORATION
SECTION7
, URBO ARROW IV
DESCRIPTION/OPERATION P A - 2 E R T - 2 O I T T
FUEL SELECTOR
Figure 7-13
A fuel tank selector allows the pilot to control the flow of fuel to the
engine,and is locatedon the left sidewall below the instrumentpanel.It has
three positions:OFF, LEFT TANK and RIGHT TANK. The arrow on the
handle of the selectorpointsto the tank which is supplyingfuel to the engine.
The vapor return from the engine is also routed back to the tank selected.
When the selectorvalve is in the OFF position, vapor return is routed back
to the right fuel tank. The valve also incorporates a safety latch which
preventsinadvertentlyselectingthe "OFF" position.
The engine fuel injection system is a "continuous flow" type, which
utilizesa vapor return line leadingback to the fuel tanks.This line providesa
route back to the tanks for vapor laden fuel that has been separatedin the
injector pump swirl chamber.The engine has an engine driven fuel pump
that is a part of the fuel injection system.An auxiliary fuel pump is also
provided. The purpose of the electrically powered auxiliary fuel pump is to
supply fuel to the engine in caseof engine driven fuel pump shaft failure or
malfunction, for ground and inflight engine starting, and for vapor suppression.The auxiliary fuel pump switch is located on the instrument panel
above the engine control quadrant, and is a three position rocker switch;
LO, HI and OFF. The LO auxiliary fuel pressureis selectedby pushingthe
REPORT: VB-940
7-t4
ISSUED:NOVEMBER30. l97E
PIPER AIRCRAFT CORPORATION
SECTION 7
P A . 2 8 R T - 2 O I TT, T I R B O A R R O W I V D E S C R I P T I O N / O P E RA T I O N
1 - h ee n g i n ef u e l i n j e c t i o n s y s t e mi s a " c o n t i n u o u sf l o w " t y p e . w h i c h
u t i l i z e sa v a p o r r e t u r nl i n e l e a d i n gb a c kt o t h ef u e l t a n k s .T h i s l i n ep r o v i d e sa
r o u t e b a c k t o t h e t a n k s f o r v a p o r l a d e nf u e l t h a t h a s b e e ns e p a r a t e d
in the
i n j e c t o rp u m p s w i r l c h a m b e r .T h e e n g i n eh a s a n e n g i n ed r i v e n f u e l p u m p
t h a t i s a p a r t o f t h e f u e l i n j e c t i o ns y s t e m .A n a u x i l i a r y f u e l p u m p i s a l s o
p r o v i d e d .T h e p u r p o s eo f t h e e l e c t r i c a l l yp o w e r e da u x i l i a r yf u e l p u m p i s t o
s u p p l yf u e l t o t h e e n g i n ei n c a s eo f e n g i n ed r i v e nf u e l p u m p s h a f tf a i t u r eo r
m a l f u n c t i o n ,f o r g r o u n d a n d i n f l i g h t e n g i n es t a r t i n g ,a n d f o r v a p o r s u p pression.'l'he
a u x i l i a r yf u e l p u m p s w i t c hi s l o c a t e do n t h e i n s t r u m e n tp a n e l
a b o v e t h e e n g i n ec o n t r o l q u a d r a n t ,a n d i s a t h r e e p o s i t i o nr o c k e r s w i t c h ,
l - O , H I a n d O F F . T h e l - O a u x i l i a r yf u e l p r e s s u r e
isselected
b y p u s h i n gt h e
t o p o f t h e s w i t c h .T h e H l a u x i l i a r yf u e l p r e s s u r ei s s e l e c t e db y ,p u s h i n gr h e
b o t t o m o f t h e s w i t c h ,b u t t h i s c a n b e d o n eo n l y a l t e ru n l a t c h i n gt h ea d j a c e n r
g u a r d .W h e n t h e H I a u x i l i a r vf u e l p u m p i sa c t i v a t e da. n a m b e ri i g h t n e a rt h e
a n n u n c i a t i o np a n e l i s i l l u m i n a t e dT. h i s l i g h t d i m s w h e n e v e rt h e p u m p
p r e s s u r cr e d u c e sa u t o n r a t i c a l l ya n d m a n i f o l d p r e s s u r ei s b e l o w a p p r o x i m a t e l y2 l i n c h e s .
l n c a s co f a l a i l e d e n g i n ed r i v e n f u e l p u m p , t h e a u x i l i a r ye l e c t r i cf u e l
p u m p s h o u l db e s e to n H l . A d e q u a t ep r e s s u r e
a n d l ' u e lf l o w w i l l b e s u p p l i e d
1 w e r .M a n u a l l e a n i n gt o t h e c o r r e c tf u e l f l o w
f o r u p 1 o a p p r o x i m a t e l y7 5 a 7pi o
w i l l b e r e q u i r e da t a l t i t u d e sa b o v e 1 5 , 0 0 0l e e ta n d f o r e n g i n es p ee d sl e s st h a n
2 3 0 0 R P M . A n a b s o l u t ep r e s s u r es w i t c ha u t o m a t i c a l l ys e l e c t sa l o w e r f u e l
p r e s s u r ew h e n t h e t h r o t t l e i s r e d u c c db e l o w) l " H g m a n i f o l dp r e s s u r ea n d
t h e H I a u x i l i a r vf u e l p u m p i s o n .
NOTE
E x c e s s i v ef u e l p r e s s u r ea n d v e r y r i c h f u e l / a i r
m i x t u r e s w i l l o c c u r i f t h e H l p o s i t i o ni s e n e r g i z e d w h e n t h e e n g i n ef u e l i n j e c t i o ns y s t e mi s
f u n c t i o n i n gn o r m a l l y .
L o w a u x i l i a r yf u e l p r e s s u r ei s a v a i l a b l ea n d m a y b e u s e dd u r i n g n o r m a l
e n g i n e o p e r a t i o nb o t h o n t h e g r o u n d a n d i n f l i g h t f o r v a p o r s u p p r e s s l o n
should it be necessaryas evidenced by unstable engine operation or
fluctuating fuel flow indicationsduring idle or at high altitudes.
A s p r i n gl o a d e dO F F p r i m e r b u t t o n s w i t c hi s l o c a t e do n t h e i n s t r u m e n t
p a n e l a n d i s u s e dt o s e l e c tH I a u x i l i a r y f u e l p u m p o p e r a t i o nf o r p r i m i n g ,
irrespectiveof other switch positions.The primer button may be usedfor
both hot or cold engine starts.
ISSUED:NOVEMBER30, 1978
REVISEDA
: U G U S T8 . 1 9 8 3
REPORT:VB-940
7-15
PIPER AIRCRAFT CORPORATION
S E C T I O N7
D E S C R I P T I O /NO P E R A T I O N P A - 2 8 R T . 2 O I T ,T T ] R B O A R R O W I V
O n a i r p l a n e se q u i p p e dw i t h a n o p t i o n a le n g i n ep r i m e rs y s t e m( i d e n t i f i e d
b y P l a c a r db e l o w p r i m e r b u t t o n s h o w n i n F i g u r e 7 - 2 l 1 , t h e p r i m e r s w i t c h
l o c a t i o n a n d a c t u a t i o n i s t h e s a m e a s t h e b a s i c a i r p l a n e .H o w e v e r ,t h i s
s y s t e md o e s p r o v i d e a s e p a r a t ep r i m e r s y s t e ma s a n i n t e g r a lp a r t o f t h e
c n g i n ef u e l s y s t e m .A n e l e c t r i c a l l yo p e r a t e dd i v e r t e rv a l v e i s l o c a t e di n t h e
m e t e r e df u e l s u p p l y l i n e b e t w e e nt h e a i r t h r o t t l e v a l v e a n d t h e m a n i f o l d
v a l v e . O t h e r c o m p o n e n t sa r e t w o p r i m e r n o z z l e s ,l o c a t e di n t h e i n t a k e
m a n i l ' o l do n e a c hs i d eo f t h e e n g i n e ,t h e i n t e r c o n n e c t i nfgu e l l i n e s ,a n d f i n e
w i r e s p a r k p l u g s . A c t u a t i o n o f t h e e n g i n e p r i m e r s w i t c h o p e r a t e st h e
n d e n e r g i z . et h
s e d i v e r t e rv a l v e w h i c h
a u x i l i a r y e l e c t r i cf u e l p u m p o n H l a
'fhe
d i v e r t e rv a l v ed o e sn o t s h u t o f f a l l
s u p p l i e sf u e l t o e a c hp r i m e r n o z z l e .
f u e l f l o w t o t h e m a n i f o l d v a l v e . t h e r e f o r es o m e q u a n t i t y o f f u e l i s a l s o
s u p p l i e dt o e a c hc y l i n d e rn o z z l ed u r i n g p r i m i n g .O p e r a t i o no f t h e a u x i l i a r v
fuel pump on Hl and LO is unchanged.
7.I5 ELECTRICAL SYSTEM
A l l s w i t c h e sa r e g r o u p e di n a s w i t c hp a n e la b o v et h e p o w e r q u a d r a n t .
O n t h e l o w e r r i g h t s i d e o f t h e i n s t r u m e n tp a n e l i s t h e c i r c u i tb r e a k e rp a n e l ,
w i t h e a c h b r e a k e rc l e a r l ym a r k e d t o s h o w w h a t c i r c u i t i t p r o t e c t s .A l s o ,
s nd
c i r c u i t p r o v i s i o n sa r e m a d et o h a n d l et h e a d d i t i o n o f c o m m u n i c a t i o n a
n a v i g aito n a l e q u i p m e n t .
S t a n d a r de l e c t r i c aal c c e s s o r i ei sn c l u d ea l t e r n a t o r ,s t a r t e r ,e l e c t r i cf u e l
p u m p , s t a l l w a r n i n g i n d i c a t o r .a m m e t e r ,a n d a n n u n c i a t o rp a n e l .
T h e a n n u n c i a t o rp a n e li n c l u d e sa l t e r n a t o ra n d l o w o i l p r e s s u r ien d i c a t o r
r a n e la l s o
l i g h t s .W h e n t h e o p t i o n a lg y r o s y s t e mi s i n s t a l l e dt.h e a n n u n c i a t o p
i n c l u d e sa l o w v a c u u m i n d i c a t o r l i g h t . T h e a n n u n c i a t o rp a n e l l i g h t s a r c
p r o v i d e do n l y a s a w a r n i n gt o t h e p i l o t t h a t a s y s t e mm a y n o t b e o p e r a t i n g
p r o p e r l y ,a n d t h a t h e s h o u l dc h e c ka n d m o n i t o r t h ea p p l i c a b l es y s t e mg a u g e
t o d e t e r m i n ew h e n o r i f a n y n e c e s s a ray c t i o n i s r e q u i r e d .
O p t i o n a le l e c t r i c aal c c e s s o r i ei ns c l u d e sn a v i g a t i o ng, r o u n dr e c o g n i t i o n ,
a n t i - c o l l i s i o nl.a n d i n g ,i n s t r u m e n ta n d c a b i n d o m e l i g h t s .N a v i g a t i o na n d
r a d i o l i g h t sa r e c o n t r o l l e db y a r h e o s t a st w i t c ho n t h e l e f t s i d eo f t h e s w i t c h
p a n e l .T h e i n s t r u m e n tp a n e ll i g h t sa r e c o n t r o l l e db y a r h e o s t ast w i t c ho n t h e
r i g h t s i d eo f t h e p a n c l .
REPORT:V8-940
7-16
ISStlf,D: NOVEMBER 30. 1978
REVISED: JULY 16.l9E4
S E C T I O N7
P I I ' F , RA I R ( ] R A F TC ] O R P O R A T I O N
ATION
P A - 2 8 R T ' - 2 0 1t {TJ,R B OÄ R R O W I V D [SCRI P]'ION/ OPE,R
. r o v i d c si t r s t r u t t t c n t
ilanc[p
A n o p t i o n a l i g h t ,m o u n t c di n t h c -ol vl rccr l r c a p
l i g h t i s c o n t r o l l c dh y a r h c o s t a t
a n d c o c k p i t l i g h t i n gf . o rn i g h t f l y i n g .
t thc light. A rnap light window in the lcns is
s w i t c h l o c a t c da c l . j a c c nt o
a c t u i r t c db y a n a c l . i a c c nstw i l c h .
A n o p t i o n a lw i n gt i p l r c c o g r r i t i o lni g h t s y s t e mc o n s i s t os f 2 I i g h t s( o n ci n
c n t : hw i n g t i p ) a n d i s o p e r a t c db y a s p l i t l a n d i n gl i g h t / r e c o g n i t i olni g h t
i ' o c k c rt y p c s w i t c l rr r . r o r r n t co<nl t l t c s w i t c hp a n c l .
II/ARNING
Wlrcn optional p:rncl lights arc irrstallcd,
r h eo s t a ts r v i t c hn r r r sbt c o i f t o o b t a i ng c a rl i g h t s
f u l l i n t e n s i t yd u r i u g d a y t i m c f l y i n g . W h e n
a i r c r a f ' ti s < l p e r a t c da t n i g h t z r n dp a n e l l i g h t
r h e o s t a ts w i t c h i s t u r n e d o n , g e a r l i g h t s a n d
o v c r b o o s l l i g h t w i l l a u t o n l a t i c a l l<yl i l r r .
C'AL]7-ION
I ) o n o t u s c c i g a r l i g h t e r r c c c p t a c l eass p ( ) \ . \ / c r
s o u r c c sf o r a n l , d e v i c c so t h c r t h a n t l r c c i g a r
. rtvotlrcr
l i g h t c r ss u p p l i c dr v i t ht l r ca i r p l a n e A
r l c v i c ep l u g g c r li n t o t h c s cr c c ep t a c l c sr r t a yb c
d a ntageil.
I S S t I I i I ) : A t l ( ; t J S ' l '8 . 1 9 8 3
RIiVISl,ll):SIiP'iliMßltR 30, 1985
RIrl'OR'l': Vß-940
7 -l6a
PIPER AIRCRAFT CORPORATION
S E C T I O N7
P A - 2 8 R T . 2 O I TT, U R B O A R R O W I V D E S C R I P T I O N / O P E R A T I O N
.. i
AI'ERNATOR
srJrcH
.<j
r+=,_.+_t1
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FEcUL^ron
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ai
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-
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iI
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L ' 0H r E F
ALTERNATORAND STARTERSCHEMATIC
Figure7-15
I S S U E D :N O V E M B E R3 0 , 1 9 7 8
REVISEDF
: E B R U A R Y9 . l 9 8 l
REPORT:V8-940
7_17
SECTION7
PIPER AIRCRAFT CORPORATION
DESCRIPTION/OpERATION pA-28RT-201T,
TURBO ARROW IV
CIRCUIT BREAKER PANEL
Figure7-17
The anti-collisionand landing lights are controlled by rocker switches
on the switch panel.
WARNING
S t r o b e l i g h t s s h o u l d n o t b e o p e r a t i n gw h e n
flying through overcast and clouds since reflectedlight can producespacialdisorientation.
Do not operatestrobelights in closeproximitv
to ground, such as during takeoff and landing.
NOTE
O n a i r p l a n e sw i t h i n t e r l o c k e dB A T a n d A L T
switches,the ALT switch is mechanicallyinterlocked with the BAT switch.When ALT switch
is turned ON, the BAT switch will also be
turned ON. On airplaneswith separateBAT
and ALT switch operations,the switchesmay
be positioned independentlyas desired.
REPORT: VB-940
7-18
ISSUED: NOVEMBER 30, l97B
REVISED: JUNE 30, l98l
PIPER AIRCRAFT CORPORATION
SECTION 7
P A . 2 8 R T - 2 O I TT, T ] R B O A R R O W I V D E S C R I P T I O N/ O P E R A T I O N
T h e p r i m a r y e l e c t r i c a lp o w e r s o u r c ei s a l 4 - v o l t , 6 5 - a m p a l t e r n a t o r ,
w h i c h i s p r o t e c t e db y a v o l t a g er e g u l a t o ra n d a n o v e r v o l t a g er e l a y . T h e
a l t e r n a t o rp r o v i d e sf u l l e l e c t r i c a pl o w e r o u t p u t e v e na t l o w e n g i n eR P M .
T h i s p r o v i d e s i m p r o v e d r a d i o a n d e l e c t r i c a le q u i p m e n to p e r a t i o n a n d
i n c r e a s eb
s a t t e r yl i f e b y r e d u c i n gb a t t e r yl o a d .
S e c o n d a r yp o w e r i s p r o v i d e d b y a I 2 - v o l t , 2 5 - a m p e r eh o u r b a t r e r y .
T h e a m m e t e r a s i n s t a l l e dd o e s n o t s h o w b a t t e r y d i s c h a r g er; a t h e r i t
s h o w st h e e l e c t r i c allo a d p l a c e do n t h e s y s t e m W
. i t h a l l t h e e l e c t r i c ael q u i p m e n t o f f , a n d t h e m a s t e rs w i t c ho n , t h e a m m e t e rw i l l i n d i c a t et h e c h a r g i n g
r a t e o f t h e b a t t e r y .A s e a c he l e c t r i c aul n i t i s s w i t c h e do n , t h e a m m et e r w i l l
i n d i c a t et h e t o t a l a m p e r ed r a w o f a l l t h e u n i t s i n c l u d i n gt h e b a t t e r y .F o r
e x a m p l e t, h e a v e r a g ec o n t i n u o u sl o a df o r n i g h tI ' l y i n gw i t h r a d i o so n i s a b o u t
3 0 a m p e r e sT. h e 3 0 a m p e r ev a l u ep l u s2 a m p e r e sf o r c h a r g i n gt h e b a t t e r yw i l l
t h e ns h o r , o
. rn t h e a m m e t e r ,i n d i c a t i n gt h e a l t e r n a t o ri s f u n c t i o n i n gp r o p e r l l ' .
S o l e n o i d s "p r o v i d e d i n t h e b a t t e r y a n d s t a r t e r c i r c u i t s ,a r e u s e d t o
c o n t r o l h i g h c u r r e n t d r a i n f u n c t i o n sr e m o t e l yf r o m t h e c a b i n .
7.I7 VACUUM SYSTIM
-l'he
v a c u u m s y s t e mi s d e s i g n e dt o o p e r a t et h e a i r d r i v e n g y r o i n s t r u m e n t s .T h i s i n c l u d e st h e d i r e c t i o n a la n d a t t i t u d eg y r o sw h e n i n s t a l l e dT. h e
s y s t e mc o n s i s t so f a n e n g i n ev a c u u mp u m p , a v a c u u mr e g u l a t o r a
, filterand
t h e n e c e s s a rpy l u m b i n g .
T h e v a c u u m p u m p i s a d r y t y p e p u m p w h i c h e l i m i n a t e st h e n e e df o r a n
a i r / o i l s e p a r a t o ra n d i t s p l u m b i n g . A s h e a rd r i v e p r o t e c t st h e e n g i n ef r o m
d a m a g e .I f t h e d r i v e s h e a r st h e g y r o s w i l l b e c o m ei n o p e r a t i v e .
The vacuum gauge,mounted on the right instrumentpanelto the right
of the radios, (refer to Figure 7-21) provides valuable information to the
pilot about the operation of the vacuum system.A decreasein pressurein a
systemthat has remainedconstantover an extendedperiod, may indicatea
dirty filter, dirty screens,possiblya stickingvacuum regulatoror leak in system (a low vacuum indicator light is provided in the annunciator panel).
Zero pressurewould indicate a shearedpump drive, defectivepump, possibly a defectivegaugeor collapsedline. In the event of any gaugevariation
from the norm, the pilot should havea mechaniccheckthe systemto prevent
possibledamageto the systemcomponentsor eventualfailure of the system.
ISSUED:NOVEMBIR 30. 1978
REPORT:VB-940
7_t9
S E C T I O N7
PIPER AIRCRAFT CORPORATION
DESCRIPTION
/OPERATION P A - 2 8 R T . 2 O I T .T T ] R B O A R R O W I V
A v a c u u mr e g u l a t o ri s p r o v i d e di n t h e s y s t e mt o p r o t e c tt h e g y r o s .T h e
v a l v ei s s e ts o t h e n o r m a lv a c u u mr e a d s4 . 8t o 5 . I i n c h e so f m e r c u r v a
, settins
w h i c h p r o v i d e ss u f f i c i e n tv a c u u m r o o p e r a t ea l l t h e g y r o s a t i h . i r r u r . ä
R P M . H i g h e rs e t t i n g sw i l l d a m a g et h eg y r o sa n d w i t h a l o w s e t t i n gt h e g y r o s
w i l l b e u n r e l i a b l e .T h e r e g u l a t o ri s l o c a t e db e h i n d t h e i n s t r u m e n tn a n e l .
7.I9 PITOT-STATIC SYSTEM
T h e s y s t e ms u p p l i e sb o t h p i t o t a n d s t a t i cp r e s s u r e
f o r t h e a i r s p e e di n d i c a t o r , a l t i m e t e ra n d v e r t i c a ls p e e di n d i c a t o r( w h e n i n s t a l l e d ) .
Pitot and static pressureis picked up by the pitot headon the bottom of
the left wing. An optional heatedpitot head,which alleviaresproblemswith
icing or heavy rain, is available.The switch for pitot heat is iocatedon the
switch panel. Push-button type pitot and static drains are located on the
lower left sidewall of the cockpit.
An alternate static source is available as optional equipment. The
control valve is locatedbelow the left sideof the instrunrentpanel.when the
valve is set in the alternateposition, the altimeter,vertical speedindicator
and airspeedindicator will be using cabin air for static pressure.The storm
window and cabin vents must be closedand the cabin heaterand defroster
must be on during alternatestatic sourceoperation.The altimeter error is
lessthan 50 feet unlessotherwiseplacarded.
To prevent bugs and water from enteringthe pitot pressureholeswhen
the airplane is parked, a cover should be placed over the pitot head. A
partially or completelyblocked pitot head will give erratic or zero readings
on the instruments.
NOTE
During preflight, check to make sure the pitot
cover is removed.
REPORT:VB-940
7-20
ISSUED:NOVEMBER30, 1978
P I I ) E R A I R C R A I . " I 'C ( ) R P ( ) I IA I ' I 0 N
P A - 2 8 R T - 2 0 1 11' ,' t J R I l ( )A R R O W l V
sllc'iloN 7
I)IjS(]RII'1'ION /()I'I]RATION
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= 9 ? F e "/ ", /
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Itl,.l'0R'l': Vß-9,t0
7 -21
PIPER AIRCRAFT CORPORATION
SECTION7
DESCRIPTION/OPERATION PA.2tRT.2OIT.TURBO ARROW IV
'l'
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INSTRUMENT PANEL
Figure7-21
REPORT: VB-940
7-22
ISSUED:NOVEMBER 30, 1978
REVISED: AUGUST 15, l9E6
PIPER AIRCRAFT CORPORATION
SECTION7
TURBO ARR.OWIV DESCRIPTION/OPERATION
PA-28RT-2OIT.
7.2I INSTRUMENT PANEL
The instrument panel is designed to accommodate the customary
advancedflight instrumentsand the normally required power plant instruments.The artificial horizon and directionalgyro are vacuum operatedand
are located in the center of the left hand instrument panel. The vacuum
gaugeis located on the right hand instrumentpanel.The turn indicator,on
the left side, is electricallyoperated.
T h e r a d i o sa r e l o c a t e di n t h e c e n t e rs e c t i o no f t h e p a n e i ,a n d t h e c i r c u i t
breakersare in the lower right corner of the panel.An optional radio master
switch is located near the top of the instrument panel betweenthe radio
stacks.It controls the power to all radios through the aircraft masterswitch.
An emergencybus switch is also provided to provide auxiliary power to the
avionicsbus in eventof a radio masterswitchcircuit failure. The emergency
bus switch is located behind the lower right shin guard left of the circuit
b r e a k e rp a n e l .
A n a n n u n c i a t o rp a n e li s m o u n t e di n t h e u p p e ri n s t r u m e n p
t a n e lt o w a r n
t h e p i l o t o f a p o s s i b l em a l f u n c t i o n i n t h e a l t e r n a t o r ,o i l p r e s s u r e a, n d
vacuum systems.The overboost light is located beside the annuncrator
panel.
A ground clearanceenergy saver systemis availableto provide direct
p o w e r t o C o m m # 1 w i t h o u t t u r n i n g o n t h e m a s t e rs w i t c h .A n i n t e r n a l l yl i t
p u s h b u t t o ns w i t c h ,l o c a t e do n t h e i n s t r u m e n tp a n e l ,p r o v i d e sa n n u n c i a t i o n
for engagementof the system.When the button is engageddirect aircraft
b a t t e r y p o w e r i s a p p l i e dt o C o m m # l a u d i o a m p l i f i e r( s p e a k e ra) n d r a d i o
accessories.The switch must be turned OFF or depletion of the batterv
could result.
The manifold pressureline has a drain valve locatedbehind and below
the manifold pressuregauge. This allows any moisture which may have
collectedfrom condensationto be pulled into the engine.This is accomplished by depressingthe valve for 5 secondswhile operatingthe engineat
1 0 0 0R P M .
NOTE
Do not depressthe valve when manifold pressure exceeds25 inches He.
ISSUED: NOVEMBER 30, l97t
REVISED: JULY 15, 1982
REPORT: VB-940
7-23
S E C T I O N7
PIPERAIRCRAFT CORPORATION
DESCRIPTION
/ OPERATION PA-28RT-2OIT.
TT]RBOARROW IV
-::::-='
1Ll
-t-2
{rutP
CABIN DOOR LATCH
Figure7-23
7.23 CABIN FEATURES
A l l s e a t b a c k s h a v e t h r e e p o s i t i o n :n o r m a l , i n t e r m e d i a t ea n d r e c l i n e .
T h e a d j u s t m e n lte v e ri s l o c a t e da t t h e b a s eo f t h e s e a tb a c k o n t h e o u t b o a r d
side of the seat. The front seatsadjust fore and aft for easeof entry and
o c c u p a n tc o m f o r t . A n a r m r e s ti s l o c a t e do n t h e s i d r :p a n e l sa d j a c e n t o t h e
f r o n t s e a t .T h e r e a rs e a t sa r ee a s i l yr e m o v e dt o p r o v i d er o o m f o r b u l k y i t e m s .
R e a r s e a ti n s t a l l a t i o n si n c o r p o r a t el e g r e t a i n e r sw i t l i l a t c h i n gm e c h a n r s m s
w h i c h m u s t b e r e l e a s e db e f o r et h e r e a r s e a t sc a n b e r e m o v e d .R e l e a s i n g
the
r e t a i n e r si s a c c o m p l i s h e db y d e p r e s s i n g
t h e p l u n g e rL r e h i n de a c h r e a r l e g .
sre available.
Optional headresta
s i t h i n e r t i a r e e l sa r e p r o v i d e df o r e a c hf r o n t s e a t
S h o u l d e rh a r n e s s ew
o c c u p a n t .O n a i r c r a f t s e r i a ln u m b e r s2 8 R - 7 9 31 0 0I t h r o u g h 2 8 R - 8 4 31 0 3 2 ,
s h o u l d e rh a r n e s s ew
s i t h i n e r t i a r e e l sw e r ep r o v i d e da s o p t i o n a le q u i p m e n t
f o r t h e o c c u p a n t so f t h e r e a r s e a t sO
. n a i r c r a f ts e r i a ln u m b e r s2 8 R - 8 5 3l 0 0 l
a n d u p . s h o u l d e r h a r n e s s e sw i t h i n e r t i a r e e l sa r e p r o v i d e d a s s t a n d a r d
e q u i p m e n tf o r t h e o c c u p a n t so f t h e r e a r s e a t s .A c h e c k o f t h e i n e r t i a r e e l
m e c h a n i s mc a n b e m a d e b y p u l l i n g s h a r p l y o n t h e s t r a p a n d c h e c k i n g
t h a t t h e r e e l w i l l l o c k i n p l a c e u n d e r s u d d e ns t r e s s T
. his locking feature
REPORT:VB-940
7-24
ISSUED:NOVEMBER30, 1978
R E V I S E D J: U L Y 1 6 .1 9 8 4
S E C T I O N7
PIPER AIRCRAFT CORPORATION
P A - 2 8 R T . 2 O I TT, U R B O A R R O W I V D E S C R I P T I O /NO P E R A T I O N
p r e v e n t st h e s t r a p f r o m e x t e n d i n ga n d h o l d st h e o c c u p a n ti n p l a c e .U n d e r
. n earlier
n o r m a l m o v e m e n t ,t h e s t r a p w i l l e x t e n da n d r e t r a c ta s r e q u i r e d O
a i r c r a f t p r o v i d e d w i t h a s i n g l es t r a p a d j u s t a b l es h o u l d e rh a r n e s sl o c a t e d
a b o v et h e s i d ew i n d o w f o r e a c hf r o n t s e a t ,t h e s h o u l d e rs t r a pi s r o u t e do v e r
t h e s h o u l d e ra d j a c e n tt o t h e w i n d o w a n d a t t a c h e dt o t h e l a p b e l t i n t h e
g e n e r aal r e ao f t h e o c c u p a n t ' sh i p . A d j u s t t h i s f i x e d s t r a ps o t h a t a l l c o n t r o l s
a r e a c c e s s i b l ew h i l e m a i n t a i n i n g a d e q u a t er e s t r a i n t f o r t h e o c c u p a n t .
S h o u l d e rh a r n e s s essh o u l d b e r o u t i n e l yw o r n d u r i n g t a k e o f f .l a n d i n g ,a n d
w h e n e v e ra n i n f l i g h t e m e r g e n c )s' i t u a t i o no c c u r s .
A d d i t i o n a l f e a t u r e si n c l u d e p i l o t s t o r m w i n d o w , t w o s u n v i s o r s ,a s h
t r a y s f o r e a c ho c c u p a n t .m a p p o c k e t sl o c a t e do n t h e s i d ep a n e l sb e l o wt h e
i n s t r u m e n tp a n e l ,m i s c e l l a n e o upso c k e t so n t h e r e a ro f t h e f r o n t s e a tb a c k s ,
a r m r e s t sf o r t h e f r o n t o c c u p a n t sc, a b i n o r b a g g a g ed o o r l o c k sa n d i g n i t i o n
lock.
. o c l o s et h ec a b i nd o o r . h o l d t h e d o o r
T h e c a b i nd o o r i s d o u b l el a t c h e d T
c l o s e dw i t h t h e a r m s e tw h i l e r n o v i n gt h e s i d ed o o r l a t c ht o t h e " L A T C H E D "
p o s i t i o n .T h e n e n g a g et h e t o p l a t c h . B o t h l a t c h e sm u s l b e s e c u r e db e f o r e
flight.
7.25 BAGGAGf, AREA
A l a r g eb a g g a g ea r e a ,l o c a t e db e h i n dt h e r e a r s e a t s i,s a c c e s s i b leei t h e r
d o o r o n t h e r i g h t s i d eo f
f r o m t h e c a b i n o r t h r o u g h a l a r g eo u t s i d eb a g g a g e
t h e a i r c r a f t . M a x i m u m c a p a c i t yi s 2 0 0 l b s . T i e - d o w ns t r a p sa r e p r o v i d e d
a n d s h o u l d b e u s e da t a l l t i m e s .
NOl'E
I t i s t h e p i l o t ' s r e s p o n s i b i l i t yt o b e s u r ew h e n
the baggageis loadedthat the aircraftC.G. falls
w i t h i n t h e a l l o w a b l eC . G . R a n g e .( S e eW e i g h t
a n d B a l a n c eS e c t i o n . )
ISSUED:NOVEMBER30, 1978
REVISED:JULY 16.1984
REPORT:VB-940
7-25
SECTION7
PIPER AIRCRAFT CORPORATION
DESCRIPTION/OPERATION PA-2ERT-2OIT.
TURBO ARROW IV
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HEATING, VENTILATING AND DEFROSTINGSYSTEM
Figure7-25
REPORT:VB-940
7-26
ISSUED:NOVEMBER30, l97E
REVISED:SEPTEMBER14.1979
PIPERAIRCRAFT CORPORATION
SECTION7
TURBO ARROW IV DESCRIPTION
PA-28RT-2OIT,
/OPERATION
7.27 HEATING, VENTILATING AND DEFROSTING SYSTEM
The heating system is designedto provide maximum comfort for the
occupantsduring winter and cool weatherflights.The systemincludesa heat
shroud, heat ducts, defroster outlets,heat and defrostercontrols.
CAUTION
When cabin heat is operated,heatduct surface
becomeshot. This could resultin burns if arms
or legs are placedtoo closeto heatduct outlets
or surface.
An opening in the front of the lower cowl admits ram air to the heater
shroud and then the air is ductedto the heatershut-offson the right and left
sideof the fire wall. When the shut-off s areopenedthe heatedair then enters
the heat ducts located along each side of the centerconsole.Outlets in the
heat duct are located at eachseat location. Airflow to the rear seatscan be
regulatedby controls in the heat ducts locatedbetweenthe front seats.The
temperatureof the cabin is regulatedby the heatercontrol located on the
right side of the instrument panel.
Defrosting is accomplishedby heat outletslocatedon the right and left
side of the cowl cover. Heated air is ducted directly to defrostershut-off
valvesat the fire wall, then to the defrosteroutlets.The airflow is regulated
by a defrostercontrol located below the heat control.
To aid air distribution, the cabin air is exhaustedoverboardby an outlet
located on the bottom of the fuselage.Cabin exhaust outlets are located
below and outboard ofthe rear seats.The abovefeaturesare removedwhen
a i r c o n d i t i o n i n gi s i n s t a l l e d .
An optional overheadventilating systemwith outlets over each seatis
also available.An additional option to aid in fresh air circulationon models
without air conditioning is a cabin air blower to force air through the overhead vent system.This blower is operatedby a fan switch with three posit i o n s- " O F F , " " L O W , " a n d " H I G H . " T h e s w i t c hi s l o c a t e do n t h e r i g h t s i d e
of the instrument panel with the heater and defrostercontrols.
ISSUED:NOVEMBER30, l97t
REVISED: SEPTEMBER14. 1979
REPORT:VB-940
7-27
SECTION 7
PIPER AIRCRAFT CORPORATION
D E S C R I P T I O N/ O P E R A T I O N P A - 2 8 R T - 2 O I TT, T ] R B O A R R O W I \ I
7.29STALL WARNING
A n a p p r o a c h i n gs t a l l i s i n d i c a t e db y a s t a l l w a r n i n g h o r n w h i c h i s
a c t i v a t e db e t u , e e nf i v e a n d t e n k n o t s a b o v e s t a l l s p e e d . M i l d a i r f r a m e
b u f f e t i n ga n d g e n t l ep i t c h i n g m a y a l s o p r e c c d et h c s t a l l . S t a l l s p e e d sa r e
s h o w no n g r a p h si n t h e P e r f o r m a n cSee c t i o nT. h e s t a l l w a r n i n h
g o r nc m i t sa
c o n t i n u o us o u n d T
. h e l a n d i n gg e a rw a r n i n gh o r ni sd i f { ' e r e ni nt t h a t i t e m i t s
a 9 0 c y c l ep e r m i n u t eb e e p i n gs o u n d T
. h es t a l l w a r n i n h
g o r n i sa c t i v a t e b
dy a
l i f t d e t e c t o ri n s t a l l e do n t h e l e a d i n ge d g eo f t h c l e f t u ' i n g .D u r i n g p r e f l i g h t .
t h e s t a l l w a r n i n gs y s t e ms h o u l d b e c h e c k e db y t u r n i n gt h e m a s t e rs w i t c h
" O N . " l i f t i n gt h e d e t e c t o ar n d c h e c k i n gt o d e t e r m i n e
i f t h e h o r ni s a c t u a t e d .
7.3I FINISH
A l l e x t e r i o rs u r f a c e sa r e p r i m e d w i t h e t c h i n gp r i m e r a n d f i n i s h c dw i t h
a c r l ' l i c l a c q u e r .A n o p t i o n a l p o l y u r e t h a n ef i n i s h i s a v a i l a b l e .
7.33 AIR CONDITIONING*
T h c a i r c o n d i t i o n i n gs y s t e mi s a r e c i r c u l a t i nagi r s y s t e m . ' f h cm a j o r
c o m p o n c n t si n c l u d ea n e v a p o r a t o r ,a c o n d e n s e ra, c o m p r e s s o ra, b l o w e r .
s w i t c h e sa n d t e m p e r a t u r ec o n t r o l s .
-I-he
e v a p o r a t o ri s l o c a t e db e h i n dt h e r e a r b a g g a g ec o m p a r t m e n t T
. 'his
c o o l st h e a i r u s e df o r t h e a i r c o n d i t i o n i n gs y ' s t e m .
l . h e c o n d c n s eirs m o u n t c do n a r e t r a c t a b l es c r ; o pl o c a t e do n t h e b o t t o n t
o f t h e f u s e l a g ca n d t o t h e r e a r o f t h e b a g g a g ec o m p a r t m e n a
t r e a .T h e s c o o p
e x t e n d sw h en t h c a i r c o n d i t i o n e ri s O N a n d r e t r a c t st o a f l u s hp o s i t i o nw h e n
t h e s y s t e mi s O F F .
T h e c o m p r e s s oirs m o u n t e do n t h e r e a r l e f t s i d eo f t h e e n g i n e l. t h a sa n
e l e c t r i cc l u t c hw h i c h a u t o m a t i c a l l ye n g a g e os r d i s e n g a g et sh e c o m p r e s s otro
t h e b e l t d r i v e s y s t e mo f t h e c o m p r e s s o r .
* O p t i o n a le q u i p m e n l
REPORT: V8-940
7-28
I S S t i E D :N O V E M B U R3 0 . 1 9 7 8
R E \ / I S E D J: I I L Y 1 6 .1 9 8 4
PIPER AIRCRAFT CORPORATION
SECTION 7
P A - 2 8 R T - 2 O I T ,T U R B O A R R O W I V DESCRIPTION/OPERATION
A i r f r o m t h e b a g g a g ea r e a i s d r a w n t h r o u g h t h e e v a p o r a t o rb y t h e
b l o w e r a n d d i s t r i b u t e dt h r o u g h a n o v e r h e a dd u c t t o i n d i v i d u a l o u t l e t s
l o c a t e da d j a c e n t o e a c h o c c u p a n t .
T h e s w i t c h e sa n d t e m p e r a t u r ec o n t r o la r el o c a t e do n t h e l o w e rr i g h t s i d e
o f t h e i n s t r u m e n tp a n e li n t h e c l i m a t ec o n t r o lc e n t e rp a n e l .T h e t e m p e r a t u r e
c o n t r o l r e g u l a t e st h e t e m p e r a t u r eo f t h e c a b i n .T u r n i n g t h e c o n t r o l c l o c k w i s e i n c r e a s e cs o o l i n g ;c o u n t e r c l o c k w i sdee c r e a s ecso o l i n g .
T h e f a n s p e e ds w i t c h a n d t h e a i r c o n d i t i o n i n gO N - O F F s w i t c h a r e
i n b o a r do f t h e t e m p e r a t u r ec o n t r o l .T h e f a n c a n b e o p e r a t e di n d e p e n d e n t l y
o f t h e a i r c o n d i t i o n i n g ;h o w e v e r ,t h e f a n m u s t b e o n f o r a i r c o n d i t i o n e r
o p e r a t i o n .T u r n i n g e i t h e r s l v i t c ho f f w i l l d i s e n g a g teh e c o m p r e s s o cr l u t c h
a n d r e t r a c tt h e c o n d e n s edr o o r . C o o l i n ga i r s h o u l db ef e l t w i t h i n o n em i n u t e
a f t e r t h e a i r c o n d i t i o n e ri s t u r n e d o n .
NOTE
I f t h e s y s t e mi s n o t o p e r a t i n gi n 5 m i n u t e s t, u r n
t h e s y s t e r nO F F u n t i l t h e f a u l t i s c o r r e c t e d .
T h e f a n s r v i t c ha l l o w s o p e r a t i o n o f t h e f a n w i t h t h e a i r c o n d i t i o n e r
t u r n e d O F F t o a i d i n c a b i n a i r c i r c u l a t i o n ." L O W " o r " H I G H " c a n b e
s e l e c t e dt o d i r e c t a f - l o wo f a i r t h r o u g h t h e a i r c o n d i t i o n e ro u t l e t si n t h e
o v e r h e a dd u c t . T h e s e o u t l e t sc a n b e a d j u s t e do r t u r n e d o f l i n d i v i d u a l l y ' .
T h e c o n d e n s edr o o r l i g h t i s l o c a t e dt o t h e r i g h t o f t h e e n g i n ei n s t r u m e n t
c l u s t e ri n f r o n t o f t h e p i l o t . T h e d o o r l i g h t i l l u m i n a t e sw h e nt h e d o o r i s o p e n
and is ofl when the door is closed.
A c i r c u i t b r e a k e ro n t h e c i r c u i t b r e a k e rD a n e lD r o t e c t st h e a i r c o n d i tioning electricalsystem.
Whenever38 inches Hg or more manifold pressureis used a manifold
p r e s s u r es w i t c h d i s e n g a g e st h e c o m p r e s s o ra n d r e t r a c t st h e s c o o p . T h i s
a l l o w sm a x i m u m p o w e r a n d m a x i m u m r a t e o f c l i m b . T h e f a n c o n t i n u e st o
o p e r a t ea n d t h e a i r w i l l r e m a i nc o o l f o r a b o u t o n em i n u t e .W h e nt h e t h r o t t l e
is retardedso that lessthen 38 inchesHg manifold pressureis used,the clutch
w i l l e n g a g et,h e s c o o pw i l l e x t e n d ,a n d t h e s y s t e mw i l l a g a i ns u p p l l ' c o o l d
, ry
alr.
ISSUED:NOVEMBER30, 1978
REVISED:JULY 15. 1982
REPORT: VB-940
7-29
SECTION7
PIPER AIRCRAFT CORPORATION
DESCRIPTION/OPER
ATION P A - 2 8 R T - 2 O I T ,T U R B O A R R O W I V
7.35 PIPER EXTERNAL POWER*
A n o p t i o n a ls t a r t i n gi n s t a l l a t i o nk n o w n a s p i p e r E x t e r n a lp o w e r( p E p )
is accessible
through a receptaclelocatedon the right side of the fuselageafi
o f t h e w i n g . A n e x t e r n a l b a t t e r y c a n b e c o n n e c t e dt o t h e s o c k e t ,t h u s
a l l o w i n gt h e o p e r a t o rt o c r a n k t h e e n g i n ew i t h o u t h a v i n gt o g a i n a c c e s st o
the airplane'sbattery.
7.37 EMERGENCY LOCATOR TRANSMITTER*
The EmergencyLocator Transmitter (ELT) meetsthe requirementsof
FAR 91.52.It operateson self-containedbatteriesand is locatedin the ali
fuselagesection. It is accessiblethrough a rectangularcover on the right
hand side. A number 2 Phillips screwdriveris requiied to removethe cover.
. A battery replacementdate is marked on the transmitter.To comply
with FAA regulations,the battery must be replacedon or beforethis dite.
The battery must also be replaced if the transmitter has been used in an
emergencysituation or if the accumulatedtest time exceedsone hour, or if
the unit has beeninadvertentlyactivatedfor an undeterminedtime period.
NOTE
If for any reason a test transmission is
necessary,the test transmission should be
conductedonly in the first five minutesof any
h o u r a n d l i m i t e d t o t h r e ea u d i o s w e e p sl .f t e s t s
must be madeat any other time, the testsshould
b e c o o r d i n a t e dw i t h t h e n e a r e s tF A A t o w e r o r
flight servicestation.
NARCO ELT IOOPERATION
on the ELT unit itselfis a threeposition switchplacarded*oN," *oFFa n d " A R M . " T h e A R M p o s i t i o ns e t st h e E L T s o t h a t i t w i i l t r a n s m i ta f t e r
impact and will continue to transmit until its battery is drained.The ARM
position is selectedwhen the ELT is installedin the airplaneand it should
remain in that position.
*Optionalequipment
REPORT:VB-940
7-30
ISSUED:NOVEMBER30, lgTE
REVISEDA
: P R I L 1 3 .1 9 7 9
PIPER AIRCRAFT CORPORATION
SECTION7
P A - 2 8 R T . 2 O I T ,T U R B O A R R O W I V DESCRIPTION/OPERATION
To usethe ELT as a portableunit in an emergency,removethe cover and
unlatch the unit from its mounting base.The antennacableis disconnected
by a left quarter-turn of the knurled nut and a pull. A sharp tug on the two
small wires will break them loose. Deploy the self-containedantenna by
p u l l i n gt h e p l a s t i ct a b m a r k e d" P U L L F U L L Y T O E X T E N D A N T E N N A . "
M o v e t h e s w i t c h t o O N t o a c t i v a t et h e t r a n s m i t t e r .
In the event the transmitter is activated by an impact, it can only be
t u r n e do f f b y m o v i n gt h e s w i t c ho n t h e E L T u n i t t o O F F . N o r m a l o p e r a t i o n
can then be restoredby pressingthe small clear plasticresetbutton located
o n t h e t o p o f t h e f r o n t f a c eo f t h e E L T a n d t h e nm o v i n gt h e s w i t c ht o A R M .
A pilot's remote switch locatedon the left sidepanelis providedto allow
the transmitter to be turned on from inside the cabin. The pilot's remote
s w i t c h i s p l a c a r d e d" O N " a n d " A R M E D . " T h e s w i t c h i s n o r m a l l y i n t h e
A R M E D p o s i t i o n .M o v i n g t h e s w i t c ht o O N w i l l a c t i v a t et h e t r a n s m i t t e r .
M o v i n g t h e s w i t c hb a c kt o t h e A R M E D p o s i t i o nw i l l t u r n o f f t h et r a n s m i t r e r
only if the impact switch has not been activated.
The ELT should be checkedto make certainthe unit has not beenactiv a t e d d u r i n g t h e g r o u n d c h e c k . C h e c k b y s e l e c t i n g1 2 1 . 5 0M H z o n a n
operating receiver.lf there is an osciilatingchirping sound, the ELT may
have been activated and should be turned off immediately.This requires
removal of the accesscover and moving the switch to OFF, then pressthe
resetbutton and return the switch to ARM. Recheckwith the receiverro
ascertainthe transmitter is silent.
CCC CIR I I-2 OPERATION
On the unit itself is a three position selectorswitch placarded,.OFF,"
" A R M " a n d " O N . " T h e A R M p o s i t i o ni s p r o v i d e dt o s e tt h e u n i t t o t h e a u t o matic position so that it will transmit only after impact and will continue to
transmit until the battery is drained to depletion or until the switch is
m a n u a l l ym o v e d t o t h e O F F p o s i t i o n .T h e A R M p o s i t i o ni s s e l e c t e dw h e n
the transmitteris installedat the factory and the switchshould remain in that
position wheneverthe unit is installedin the airplane.The ON position is
provided so the unit can be usedas a portable transmitteror in theeventthe
automatic feature was not triggeredby impact or to periodically test the
function of the transmitter.
Selectthe OFF position when changingthe battery,when rearmingthe
unit if it has beenactivatedfor any reason,or to discontinuetransmission.
ISSUED:NOVEMBER30, 197E
REVISED:APRIL 13.1979
REPORT:VB-940
7_31
StrCTION7
PIPER AIRCRAFT CORPORATION
DESCRIPTION/OPERATIONPA-28RT_201T,
TURBO ARROW rV
NOTE
If the switch has beenplacedin the ON position
for any reason, the OFF position has to be
selected before selecting ARM. If ARM is
selecteddirectly from the ON position,the unit
will continue to transmit in the ARM position.
A pilot's remote switch, located on the left side paner,is provided to
allow the transmitter to be controlled from inside the cabin. The pilot's
remote switch is placarded "ON," *AUTO/ARM" and ..OFF/RESET.The switch is normally left in the AUTo/ARM position.To turn the transmitter off, move the switch momentarilyto the oFFi RESET position. The
aircraft masterswitch must be oN to turn the transmitteroFF. ro acruare
the transmitterfor testsor other reasons,move the switchupward to the oN
position and leave it in that position as long as transmissionis desired.
The unit is equippedwith a portable antennato allow the locator to be
removed from the aircraft in case of an emergencyand used as a portable
signal transmitter.
The locator should be checkedduring the ground checkto make certain
the unit hasnot beenaccidentallyactivated.check by tuning a radio receiver
to 121.50MHz. If there is an oscillatingsound, the locatoi may have been
activatedand should be rurned off immediately.Resetto the AIiM position
and check again to insure against outside interference.
REPORT:VB-940
7-32
ISSUED: APRIL 13.1979