Piper Aircraft Corporation PA-28RT-201T TURBO ARROW IV Operating Handbook Download

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Summary of Contents for PA-28RT-201T TURBO ARROW IV

Page 1: ...also responsible for remaining within the operating limitations as outlined by instrument markings placards and this handbook Although the arrangement of this handbook is intended to increase its in f...

Page 2: ...NERAL PIPER AIRCRAFT CORPORATION PA 28RT 201T TURBO ARROW IV I 2 6 m a I Wing Area sq ft 170 0 Min Turning Radius ft from pivot point to wingip 31 0 THREE VIEW Figure l l REPORT VB 940 1 2 ISSUED NOVE...

Page 3: ...30 1978 REVTSED SEPTEMBER 14 1979 I Teledyne Continental TSIO 360 FB 200 Sea Level to 12 000 Ft DensitY Altitude 2575 4t 4 438 3 875 360 7 5 l Six CYlinder Direct Drive HorizontallY Opposed Air Coole...

Page 4: ...acity U S gal total b tJsablc fjucl U S gal total c I ucl Gradc Aviation l Minirnurn Crade 2 Altcrnatc liucls 1 9 OlL a Oil Capacity U S qts b Oil Spccilication c Oil Viscosity RIil 0ll l V8 940 l 4 I...

Page 5: ...ACE a Compartment Volume cu ft b Entry width in c Entry Height in 1 T7 SPECIFIC LOADINGS r 1I MAXIMUM WEIGHTS a Maximum Takeoff Weight lbs b Maximum Landing Weight lbs c Maximum Ramp Weight lbs d Maxi...

Page 6: ...KIAS KCAS Never Exceed Speed VNE Do not exceed this speed in any operation Maximum Structural Cruising Speed VNO Do not exceed this speed except in smooth air and then only with caution Design Maneuve...

Page 7: ...traction Speed Do not exceed this speed when retracting the landing gear Maximum Landing Gear Extended Speed VLE Do not exceed this speed with the landing gear extended 2 5 AIRSPEED INDICATOR MARKINGS...

Page 8: ...grade h Number of Propellers i Propeller Manufacturer CI Propeller Hub and Blade Modbl l Optional Three Blade 2 Standard Two Blade k Propeller Diameter l Optional Three Blade Minimum Maximum 2 Standar...

Page 9: ...d Line Minimum Red Line Maximum d Fuel Pressure Green Arc Normal Operating Range Red Line Maximum e Exhaust Gas Temperature EGT Green Arc Normal Operating Range Red Line Maximum 0 Manifold Pressure Gr...

Page 10: ...ward Limit Inches Aft of Datum Rearward Limit Inches Aft of Datum NOTES Straight line variation between points given The datum used is 78 4 inches ahead of the wing leading edge at the intersection of...

Page 11: ...r this airplane has been determined as 2 5 gallons in each wing tank in critical flight attitudes c Usable Fuel The usable fuel in this airplane has been determined as 36 0 gallons in each wing tank d...

Page 12: ...oise levels of this airplane are or should be acceptable or unacceptable for operation at into or out of any airport The above statement not withstanding the noise level stated above has been verified...

Page 13: ...he pilot the following Takeoff Check List and one of the following Landing Check Lists will be installed TAKEOFF CHECK LIST Fuel on Proper Tank Auxiliary Fuel Pump Off E4gine Gauges Checked Alternate...

Page 14: ...nd Landing Check Lists is mandatory for air conditioned aircraft only On the instrument panel in full view of the pilot MANEUVERING SPEED I24 KIAS AT 2900 LBS SEE A F M or vA t24 AT 2900 LBS SEE P O H...

Page 15: ...L UP RELEASE Near gear selector switch GEAR UP DOWN II I KIAS MAX I33 KIAS MAX ISSUED NOVEMBER 30 197t REVISED AUGUST 15 I9t5 Adjacent to upper door latch ENGAGE LATCH BEFORE FLIGHT In full view of th...

Page 16: ...UANTI I Y INDICATOR READS ZERO CANNOT BE USED SAFELY IN FLIGHl On the instrument panel in full view of the pilot in aircraft with two bladed propeller installations only AVOID CONTINUOUS GROUND OPERAT...

Page 17: ...R 8031031 FUEL l00l130 AVTATTON GRADE MIN USABLE CAPACITY 36 GAL USABLE CAPACITY TO BOTTOM OF FILLER NECK IIT DICATOR 25 GAL Adjacent to fuel tank filler caps Serial numbers 28R 8031031 and up FUEL IO...

Page 18: ...er of the section is devoted to amplified emergency procedures containing additional information to provide the pilot with a more complete understanding of the procedures These procedures are suggeste...

Page 19: ...with backup gcar extendcr locked in OVERRIDE ENGAGED position If suflicient altitude has been gained to attempt a restart Maintain safe airspeed Fuel selcctor switch to tank containing fucl Auxiliary...

Page 20: ...nd position for normal landing approach When ficld can easily bc easily rcached slow to 75 KIAS for shortcst landing GEAR DOWN EMERGENCY LANDING Touchdowns should normally be made at lowest possible a...

Page 21: ...L PRESSURE Land as soon as possible and investigate cause Prepare for power off landing LOSS OF FUEL PRESSURE Auxiliary fuel pump unlatch HI Fuel selector check on full tank ENGINE DRIVEN FUEL PUMP FA...

Page 22: ...auxiliary fuel pump to be activated in the Hl mode while the engine driven fuel pump is operating normally engine roughness and or power loss could occur Should this condition exist pull out the fuel...

Page 23: ...educe to minimum ISSUIiD NOVEMBIIR 30 1978 RIiVISED JUNE 30 l98l 0l ll altclnator output cilllnol bc rcstolctl r ctl ucc clcctrical loads attd lantl irs soon as practical l lte battery is thc only rer...

Page 24: ...remain below 2575 rpm EMERGENCY LANDING GEAR EXTENSION Prior to cmergency extension procedure Master switch check ON Circuit brcakers check Pancl lights OFF in daytime Gear indicator bulbs check If l...

Page 25: ...select gear DOWN SPIN RECOVERY full opposite to direction of rotation full forward while neutralizing ailcrons Throttle idle neutral when rotation stoPs 4s rcquired to smoothlY regain level flight att...

Page 26: ...below 12 500 feet NOTE Time of useful consciousness at 20 000 ft is approximately l0 minutes ln the event an emergency deicent becomes necessary CLO SE the throttie and move the propeller control full...

Page 27: ...g takeoff will depend on the circumstances of the particular situation lf sufficient runway remains to complete a normal landing leave the landing gear down and land straight ahead lf the area ahead i...

Page 28: ...f Landingprocedure refcr to thc emergency check list and Paragraph 3 13 3 II ENGINE POWER LOSS IN FLIGHT Complete engine power loss is usually caused by fuel flow interruption and powcr will bc restor...

Page 29: ...n to restore power are not effective and if time permits check your charts for airports in the immediate vicinity it may be possible to land at one if you have sufficient altitude At besf gliding angl...

Page 30: ...the masteiand ignition switches Flaps may be used as desired Turn the fuel selector valve to OFF and move the mixture to idle cut off The seat belts and shoulder harness if installed should be tighte...

Page 31: ...is not required select master switch OFF If the terrain permits a landing should be made immediately NOTE The possibility of an engine fire in flight rs extremely remote The procedure given is general...

Page 32: ...or engine power up to approximately 75T0 Any combination of RPM and Manifold Pressure defined in the Power Setting Table may be used but leaning may be required for smooth operation at altitudes above...

Page 33: ...dicate a leak in the fuel system or fuel exhaustion DO NOT actuate the auxiliary fuel pump unless vapor suppression is required L O position or the engine driven fuel pump fails Hl position The auxili...

Page 34: ...trical load should be reduced as much as possible Check the alternator circuit breakers for a popped circuit The next step is to attempt to reset the overvoltage relay This is accomplished by moving t...

Page 35: ...BAT switcii OFF and the ammeter should decrease Turn the BAT switch ON and continue to monitor the ammeter If the alternator output does not decrease within 5 minutes turn the BAT switch OFF and land...

Page 36: ...ure is performed for training purposes If the landing gear does not check down and locked reduce the airspeed below 88 KIAS Move the landing gear selector switch to the DOWN position If the gear has f...

Page 37: ...artially open This will usually happen at takeoff or soon afterward A partially open door will not affect normal flight characteristics and a normal landing can be made with the door open If both uppe...

Page 38: ...power with full RICH mixture to a landing at the first available airport If roughness persists prepare for a precautionary landing at pilot s discretion 3 37 EMERGENCY DESCENT A malfunction of the ox...

Page 39: ...liarize themselves with the procedures given in this section in order to become proficient in the normal operations of the airplane The first portion of this section consists of a short form check lis...

Page 40: ...ent atmospheric conditions and piloting technique a Best Rate of Climb Speed gear up flaps up 97 KIAS gear down flaps up 79 KIAS b Best Angle of Climb Speed gcar up flaps up 79 KIAS gear down flaps up...

Page 41: ...PREFLIGHT CHECK COCKPIT Control wheel Parking brake All switches Mixture Master switch Fuel gauges Annunciator panel Master switch Primary flight controls Flaps Trim Pitot and static systems Windows...

Page 42: ...r belt Chock Nose gear strut Nose wheel tire Engine baffle seals oit Dipstick Oil filler cap Fuel strainer LEFT WING Surface condition Fresh air inlet REPORT VB 940 4 4 check on board stow properly se...

Page 43: ...ing Pitot heat All switches Passengers Cabindoor Seat belts and harness BEFORE STARTING ENGINE Avionics switch Parking brake Propeller Fuelselector Alternate air ISSUED NOVEMBER 30 1978 REVISED JULY 1...

Page 44: ...ts check check STARTING ENGINE AIRPLANE EQUIPPED WITH OPTIONAL ENGINE PRIMER SYSTEM Fuel selector Mixture ON Throttle full RICH full FORWARD check full FORWARI oN oFF ON See Figure 4 3 for Priming Tim...

Page 45: ...ngage retard full FORWARD full FORWARD ON HIGH BOOST engage full FORWARD for 3 sec full FORWARD to full AFT leave engaged oN LOW BOOST tap until rhythmic firing release half travel REPORT VB 940 4 7 M...

Page 46: ...ARTING WITH EXTERNAL POWER SOURCE Master switch All electrical equipment Terminals External power plug Proceed with normal start Throttle External power plug Master switch Oil pressure bbo Jil OFF aft...

Page 47: ...tard Manifold pressure line drain BEFORE TAKEOFF Masterswitch Flight instruments Fuel selector Auxiliary fuel pump oN check proper tank Enginc gauges Alternate air Seat backs Mixture Prop Bclts harnes...

Page 48: ...d 97 KIAS SOFT FIELD 64 KIAS depending o 25 second notch n aircraft wcight back prcssure to rotate to climb attitude Aftcr brcaking ground accclerate to 59 to 68 KIAS dcpending on aircraft wcight Gcar...

Page 49: ...e Propeller Gear Flaps Airconditioner Trim to 75 KIAS STOPPING ENGINE Flaps Air conditioner Radios Propeller Throttle Mixture Magnetos Master switch PARKING Parking brake Control wheel Flaps Wheel cho...

Page 50: ...he seat belts securing the control wheel and set the parking brake Insure that all electrical switches and the magneto slvitch are OFF and the mixture is in idle cut off Turn ON the master switch chec...

Page 51: ...x posure under a normal static load Check the tire for cuts wear and proper inflation Make a visual check of the brake block and disc Check that the fresh air inlet is clear o foreign matter NOSE SECT...

Page 52: ...ly attached and in good condition FUSEI AGE Check thc condition and security of the antennas The empennage should be clear of ice frost snow or other extraneous substances and the I resh air inlet at...

Page 53: ...QUIPPED WITH STANDARD ENGINE PRIMER SYSTEM The first step in starting is to move the fue I selector to the ON position Advance the mixture control to full RICH open the throttle half travel and move t...

Page 54: ...nded when ambient temperatures are below 20oF Upon entering the cockpit begin starting procedure by moving the fuel selector to ON Advance the mixture to full RICH and the throttle and prop controls t...

Page 55: ...longer than normal elapsed time may be required before an oil pressure indication is observed 4 17 STARTING ENGINE WHEN FLOODED If an engine is flooded move the mixture control to idle cut off and ad...

Page 56: ...iary fuel pump should be ON in the HIGH position Engage the starter rotate magneto switch clockwise and advance the mixture control to full RICH simultaneously Begin moving the throttle control back a...

Page 57: ...started reduce power to the lowest possible RPM to reduce sparking and disconnect the jumper cable from the aircraft Turn the master switch ON and check the alternator ammeter for an indication of out...

Page 58: ...xi areas are clear Release the parking brake Power should be applied slowly to start the taxi roll Taxi a few feet forward and apply the brakes to determine their effectiveness Taxi with the propeller...

Page 59: ...eoff t obtain maximum rpm push the pedestal mounted control fully forward on the instrument panel Do not allow a drop of more than 200 RPM to 300 RPM during thiis check In cold weather the propeller c...

Page 60: ...the OVERRIDE ENGAGED position can be selected and locked before takeoff and the gear will then retract as soon as the gear selector switch is placed in the UP position Care should always be taken not...

Page 61: ...controls including fuel selector flaps trim etc while maintaining adequate restraint for the occupant If the inertia reel type shoulder harness is installed a pull test of its locking restraint featu...

Page 62: ...ntrol wheel to rotate to climb attitude The procedure used for a short field takeoff with an obstacle clearance or a soft field takeoff differs slightly from the normal technique The flaps should be l...

Page 63: ...l should remain at full rich during the climb Cylinder head temperatures should be monitored during climb and should be kept below 460o at all times During climbs under hot weather conditions it may b...

Page 64: ...ng is p i a prace the alternate ir control in the oN position During flight keep account of time and fuel used in connection with p iii gn i i il how the fuel flow and fuel q antitv gauging systems ar...

Page 65: ...acceleration if it shourd be necessary to open the throttre again The amount of flap used during randings and the speed of the aircraft at contact with the runway shourd bevaried ccording t the tanoin...

Page 66: ...ecured behind the rear seats The aileron and stabilator controls should be secured by looping the safety belt through the control wheel and pulling it snug The flaps are locked when in the UP position...

Page 67: ...ped with an airspeed power sensing system backup gear extender which extends the landing gear under low airspeed power conditionsr even though the pilot may not have selected gear down This system wil...

Page 68: ...craft is operated at night and panel lights dimmer switch is turned on gear lights and overboost light will automatically dim On aircraft equipped with the backup gear extender the yellow Auto Ext OFF...

Page 69: ...WEIGHT AND BALANCE It is the responsibility of the owner and pilot to determine that the airplane remains within the allowable weight vs center of gravity envelope while in flight For weight and bala...

Page 70: ...d for the various parameters of weight altitude temperature etc The performance charts are unfactoied and do not make any allowance for varying degrees of pilot proficiency or mechanical deterioration...

Page 71: ...outlines a detailed flight plan using the performance charts in this section Each chart includes its own example to show how it is used WARNING Performance information derived by extrapo lation beyond...

Page 72: ...ight and Balance Loading Form Figure 6 ll and the C G Range and Weight graph Figure 6 15 to deter mine the total weight o the airplane and the center of gravity position After proper utilization of th...

Page 73: ...same manner using tlie existing conditions at the destination airport and when established the landing weight The conditions and calculations for the example flight are listed below The takeoff and la...

Page 74: ...b segment of the flight plan corrected for lield pressure altitude and temperature The lollowing values were determined from the above instruc tions in the flight planning example l Cruise Pressure Al...

Page 75: ...e Refer to the Pow gr Setting Table Figure 5 19 when selecting the cruise power setting The established pressure altitude and temperature values and the selected cruise power should now be utilized to...

Page 76: ...to hours before adding them to the cruise time fhe following flight time is required for the flight planning example l Total Flight Time cX3 plus d l plus e 6 l0 hrs plus I I hrs plus 4 78 hrs 6 min...

Page 77: ...TEM CALIBRATION GROSS WEIGHT 29OO LBS 165 KIAS 160 KCAS l9 lrl 6 F H JI eav 8 r j tzt a oo E E i 2 PA 28RT 2O17 F a FU Et It U U ta IE g FI D lr l J 1 F ll 7 H z o a Itl I z trt IE F F L o t 6 2o 0 18...

Page 78: ...O1T TURBO ARROW IV o UJ UI o o J J F o lt f o tr lrt IL o IJJ J F F o N I F t N I o o o o 6 o t o o N o o u u E u o v 2 E o u J 9 z ooooo o oF oo o svtx o33ds llvls POWER OFF STALL SPEED VS ANGLE OF B...

Page 79: ...I l E o N I o o o N o o o N o t att o z o o I E L o tr 3 I u r E F tr ul o u J F E a ut e o t o o o N o rt ffi I ffi ittH lli flt l fll fit I ffi t L6 8ee 2e ct o 600 JOO o o F 66 atd 9 o 6 F ob oo oo...

Page 80: ...G o N I o t o 2 l o I F o ul 3 o I ul G F G ltr o B l F E lr l o o F 5 o REPORT VB 940 5 14 1 I L I t fl il lil I I L H ooo ooo of o NNN o o o o o J i ffi I 11 fi 1 ul o ut J ul G l v G 6 ul E o L Ou...

Page 81: ...o N o O FLAP TAKEOFF PERFORMANCE Figure 5 9 REPORT VB 940 5 15 ffi il ffi 1il11 ffi 1T fi JJ lr 1 lr lr ffi I ffi I l ffi ffi ffi 1l ffl ffi T l b 4 ffi I 111 ul o ul J ut G uJ I tr o ul E o lr Hi oz...

Page 82: ...F E o sO o oz FY I oO z o o o NCI z f o oe O ol E I I w 83 Or u urS oC at Fac ut oo UJ F o tt o I c o o N o REPORT VB 940 5 16 OO FLAP TAKEOFF GROUND ROLL Figure 5 l I I ffi 1ill lt1 HJ lur ll lsll td...

Page 83: ...elo J o 8 o u F G l F o t I F E o I I o o I I t F E u l c U J F tr ul e o F o o t o N o o o o it GEAR UP CLIMB PERFORMANCE Figure 5 13 REPORT VB 940 5 17 zo o E q x 22 odil ga B oE 2 e H ft st o F O E...

Page 84: ...o I u l E F G uJ G E ut F E a uJ o D F 3 o l F N I F t I o o o 6 o o u o E ido EO i6 eb JNE Ek s do 9 o E E o U o o r o N o o o o N o t o GEAR DOWN CLIMB PERFORMANCE Figure 5 15 REPORT VB 940 5 r8 IS...

Page 85: ...F F o N I F E o N I o o REPORT VB 940 5 19 o o o JJ 6 o o co o E oErr s p q g E t i ir N9 f rE 3 ii oAE E E iXEo Eo 3r 9b E a E E iEr g oo 9 9 oQ F 8339 E E goouorFo FUEL TIME AND DISTANCE TO CLIMB Fi...

Page 86: ...tandard 55gi power 9 2 CpH 659i Power l0 tJ GPH J59i Power 12 0 CiPH NOTE Fuel flsw ill vary with altitudc therefore cruise fuel control must be accomplished by adjusting EGT peak EGT for best cconomy...

Page 87: ...o z Y I o u l lr l o o G tu l tr F o I ul G F tr llJ o E l F E a uJ _o o F f o o MAXIMUM SPEED PERFORMANCE Figure 5 21 ISSUED NOVEMBER 30 1978 REVISED JULY 16 1984 REPORT VB 940 5 23 o n oC oL fr t 9...

Page 88: ...E n Fz rn 7 qv O O J r OUTSIDE AIR TEMPERATURE _ C 4 i g HIGH SPEED ECONOMY 65 LONG FANGE 55 SPEED P tJ 1 650 F uP 2900 Cruise pressure altitude 85OO ft Cruise outside air remp r lO C Power 75o o True...

Page 89: ...O6 o u tE qO z 08 tu E o z l J I J o tr 2 U 9 2 tr o o o o o o o o 6 o o o I 6 9o I I o o I t oE NJ F c u o E ouJ F a u oO 6 F f o o o t Ux x l6Dh otsoo c o 2 t o cc ul N F FI o 9 UJE 3t ui l 4L nou...

Page 90: ...o o o N E J o u o 1l o J ul f I u l J o ul o j gt AI F o f at o I tl u o z tr f o z il ffi ffi li q F U tr D o r I uJ z E 3 o z u t 6 o q o rt F F o N I l E ct N I o T n r ri o c o o c o D c U Qc 3q F...

Page 91: ...Cruisc pressure lhituda 85oo ft Cruisa OAT 1O C Destrnrtion presluro lltituda 2mo ft D63rinrtion OAT 3O C Fusl to d6scand 2 minug O 5 1 5 gal Timo to d scrnd 8 5 minus 2 6 5 min Distsnco ro drs6nd 19...

Page 92: ...d u l tfl llll g Z o io 11 rr Tfr E c 5 vE E Z9 o9Etl i 3 Ii E E aE q o EEE oGoo 5 pp eoo o a E o x U fil I I I o o REPORT VB 940 5 29 o o o N UJ o z F I o d uJ tr u o J o F F F E I o o e o o o o n o...

Page 93: ...ii50 e E 696 t q q L L E 2 J35 o le HH f FO P Ei lF o J F sq rc E a o H 55 H n uEE 5 9 6 o FEA ul o t 8r8888 oEl oOl LANDING DISTANCE OVER 50 FT Figure 5 35 u F o oz zv tt f d3 o o ut o s3 FR I F oI...

Page 94: ...CE Figure 5 37 I o I o d o dr F F o N I F E I o o d o o o o o c s h EE 3 gE E9r3 6q 4q e ocrc 3i _5 ts t N l o o 6 6 o B c 9 6 c o E 6 x UJ REPORT VB 940 5 31 I I ffi fll t II 11 il l ll I l 1 lt L il...

Page 95: ...ance it will have center of gravity is a determining factor in flight characteristics If the C G is too far forward in any airplane it may be difficult to rotate for takeoff or landing If the C G is t...

Page 96: ...Note that the useful load includes usable fuel baggage cargo and passen gers Following this is the method for computing takeoff weight and C G 6 3 AIRPLANE WEIGHING PROCEDURE At the time of licensing...

Page 97: ...tion and all control surfaces in the neutral position Tow bar should be in the proper location and all entrance and baggage doors closed 6 Weigh the airplane inside a closed building to prevent errors...

Page 98: ...Basic Empty Weight Center of Gravity l The following geometry applies to the PA 28RT 2017 airplane when it is level Refer to Leveling paragraph 6 3 b C G Arm Level Points Fuselage Left Side N R Wing L...

Page 99: ...ese figures apply only to the specific airplane serial number and registration number shown The basic empty weight of the airplane as licensed at the factory has been entered in the Weight and Balance...

Page 100: ...Empty Weight 167221 Pilot and Front Passenger 2731A Passengers Rear Seats 40t54 Fuel 72 Callons Maximum 29640 Baggage 200 Lbs Maximum 3427 Ranrp We ight 2912 Lbs Maximum 2671t ill c The c e nrer of gr...

Page 101: ...ine asic Empty Weight G is noted on the Weight and Balance Ou f tr Figure e t li ttre a irplane has been altered refer to the Weight and Balance R cord for this information Basic Empty Weight Pilot an...

Page 102: ...T 2OIT TURBO ARROW IV SECTION 6 WEIGHT AND BALANCE at o z 3 o I I J UI o 9 4S 400 350 300 250 200 150 100 50 o 5 10 15 20 25 MOMENT IOOO POUNDS NCHES LOADING GRAPH Figure 6 13 35 40 45 50 REPORT vB 94...

Page 103: ...GROSS WT I 85 86 87 88 89 90 91 92 93 C G LOCATION INCHES AFT DATUM WEIGHT VS C G ENVELOPE 85 RIil OR I Vll 940 6 12 I o E C G RANGE AND WI IGHT Figure 6 l 5 87 2800 2700 2500 2200 100 2000 1800 _160...

Page 104: ...n on the seats cr in the baggage compartments Brief instructions are given on the plotter itself To use it first plot a point on the grid to locate the basic weight and c G location This can be put on...

Page 105: ...fe envelope a Place a dot on the plotter grid at I600 pounds and 88 00 inches to represent the basic airplane See illustration b Slide the slotted plastic into position so that the dot is under the sl...

Page 106: ...BAGGAGE l I EAR TS FRONT 2900 tBs MAX GROSS WT 89 90 91 92 93 2900 WEIGHT vs C G ENVETOPE a7 270I TAKEOFF WEIGHT AND C G 600 2500 85 2200 21 00 lo tD o o to J 2000 o 2 r c o 7 IL l raoo ll _17OO E o S...

Page 107: ...t side A cargo door is installed aft of the rear seat The wing is of a conventional design semi tapered and employs a laminar flow NACA 652415 airfoil section The main spar is located at approximately...

Page 108: ...ld the throttle inadvertently be opened too far below 12 0 feet density altitude Should this occur the amber overboost warning light in the annunciator panel will illuminate The engine induction syste...

Page 109: ...rs proportionally Fuel is supplied to the injector pump at a greater rate than th engine requires The fuel injection system is a continuous flow type A combination fuel flow indicator and manifold pre...

Page 110: ...RCRAFT CORPORATION DESCRIPTTON OPERATTON pA 2tRT 201T TURBO ARROW tV ar CoNTROL QUADRANT AND CONSOLE Figure 7 l AIRCRAFT EOUIPPED WTH BACKUP GEAR EXTENDER ISSUED NOVEMBER 3ll l97t REVISED AUGUST 15 l9...

Page 111: ...dvertent gear up landing The propeller control lever is used to adjust the propeller speed frorn high RPM to low RPM The mixture control lever is used to adjust the air to fuel ratio The engine is shu...

Page 112: ...is retracted orl extended in about seven seconds I some aircraft also incorporate a pressure sensinS device in the system lwfricn f owers the gear regardiess of ge r selector position depending upon I...

Page 113: ...a locking device which may be used to lock the verride levei in the up position Th lock is located on the left side panel of the console below the ievel of the manual override lever To lock the overr...

Page 114: ...rn emits a 90 cycle per minute beeping sound in contrast t o the stall warning horn which emits a continuous sound The nose gear is steerable through a 30 degree arc each side of center through the u...

Page 115: ...wtTcH OEAR WARNING LANDING GEAR ELECTRICAL SCHEMATIC Figure 7 5 AUTOTATIC GEAi OOWN ACTUATOR L ___ t PFE swtrcB O UP GYCLE TENMINAL 6EAR ACIUATOR toTE t sw toTfs r GEAR SHOTX rfl OOWi LmXEO rcSrtroN s...

Page 116: ...lBtt 6tai 00wll tlmottcl tml tltl orrn vrtvr lil0lE l ltll Gtm cYUilDln REPORT VB 940 7 1 l mn m clilt0m I tnon Pnlssunt it0 0ll fustlASt slDt otlPlrr6n lrllTE l rur0tul Gnn 00f 11 ltss nt sH il8 Cfil...

Page 117: ...ction is controlled by a trim control wheel located on the control console between the two front seats Figure 7 9 Rotating the wheel forward gives nose down trim and rotation aft gives nose up trim Th...

Page 118: ...e t inaicator tab to ai in determining fuel re maining when the I ili bie apa ity to the bolior f tn indicatoi tab is 25 I I gui r rrr minimum fuet gr ae ii 100 or l00LL Aviation Grade The tanks are a...

Page 119: ...t x u Yltlt Infis ulfl NUM M T nmcilnEx 8ttilct tffi mmr Mr rutP szu 0nilt ft nF mtssunr il0 lltD btxlr fl ot tEltn v Pon nrrunt um UT c tc Yil Yt YMn nflunll sH tcmn vil YE RA SIUCI0R mU sttrfl0n Yil...

Page 120: ...dvertently selecting the OFF position The engine fuel injection system is a continuous flow type which utilizes a vapor return line leading back to the fuel tanks This line provides a route back io th...

Page 121: ...ated This light dims whenever the pump pressnre reduces automatically and manifold pressure is below approxi mately 2l inches In case of a l iled engine driv n fuel pump the auxiliary electric fuel pu...

Page 122: ...ECTRICAL SYSTEM All switches are grouped in a switch panel above the power quadrant on the lower right side of the instrument panel is the circuit breaker panel with each breaker clearly marked to sho...

Page 123: ...a split landing light recognition light roc kcr typc switclr rnountcd on Ihe switclr pancl WARNING When optional pirnel liglrts are installcd rheostat switch must bc off to obtain gear lights full int...

Page 124: ...itAT0n r I I I I I I Frll F cAPACttOh 1E5t s N5 PiE55 5EilS Y l a lcc I AIP T iERNAL POgER iECEPTACLE I I solEtoto _______J CAAIN LICHI tEc tANlcAl tNlEit x o oME 3TA RTER ct0ai LtofltEi h AlT ntATOS...

Page 125: ...flected light can produce spacial disorientation Do not operate strobe lights in close proximity to ground such as during takeoffand landing NOTE On airplanes with interlocked BAT and ALT switches th...

Page 126: ...circuits are used to control high current drain functions remotely from the cabin 7 I7 VACUUM SYSTtrM The vacuum system is designed to operate the air driven gyro instru ments This includes the direct...

Page 127: ...le The switch for pitot heat is located on 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 op...

Page 128: ...A I ION PA 28RT 2OI I TI JRBO ARROW IV SEC I ION 7 DI SCR IPTION OP ER ATION 3 o E FU o 06 3 EFeF n aIE aZEWn sdfs i EEP3T8 6 X L 6ici i r i PITOT STAI IC SYS TBM I igurc 7 l9 R IiI Oll I V8 940 7 21...

Page 129: ...gsgllgE aEE r gEl s B i rtss idEssi 39 II ol r i r 6 ilEggEi iills p p aasSisB g E g Ef r EI sF EqgI FgH Eg F gEE rElE g E FgF iqtduto FddSi Sgj INSTRUMENT PANEL Figure 7 21 ISSUED NOVEMBER 30 1978 R...

Page 130: ...is located behind the lower right shin guard left of the circuit breaker panel An annunciator panel is mounted in the upper instrument panel to warn the pilot of a possible malfunction in the alterna...

Page 131: ...st be released before the rear seats can be removed Releasing the retainers is accomplished by depressing the plunger behind each rear leg Optional headrests are available Shoulder harnesses with iner...

Page 132: ...two sun visors ash trays for each occupant map pockets located on the side panels below the instrument panel miscellaneous pockets on the rear of the front seat backs armrests for the front occupants...

Page 133: ...3o a P6 F a l I x U c u 4r E a 6 rotr UGq E U rFI r l __ _J t tt I I 3o Edt6 2 a Y J F 9 6E EE g B EEs E s 5F 5 i F g s gg g e PEEF tsp FxsgFecHE333HE33EH i qt d ct F qt ot i Fi st ci F qt v I _ HEAT...

Page 134: ...front seats The temperature of the cabin is regulated by the heater control located on the right side of the instrument panel Defrosting is accomplished by heat outlets located on the right and left s...

Page 135: ...ed 7 31 FINISH All exterior surfaces are primed with etching primer and finished with acrylic lacquer An optional polyurethane finish is available 7 33 AIR CONDITIONING The air conditioning system is...

Page 136: ...em is not operating in 5 minutes turn the system OFF until the fault is corrected The fan switch allows operation of the fan with the air conditioner turned OFF to aid in cabin air circulation LOW or...

Page 137: ...ly with FAA regulations the battery must be replaced on or before this date The battery must also be replaced if the transmitter has been used in an emergency situation or if the accumulated test time...

Page 138: ...r The ELT should be checked to make certain the unit hal not been acti vated during the ground check Check by selecting l r 5 0 MHz on an operating receiver If there is an oscillating chirping sound t...

Page 139: ...entarily to the OFF RESET position The aircraft master switch must be ON to turn the transmitter OFF To actuate the transmitter for tests or other reasons move the switch upward to the ON position and...

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Piper Aircraft Corporation PA-28RT-201T TURBO ARROW IV, Operating Handbook

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