Take Flight G-BSCY PA-28-151 1981 Pilot Operating Handbook Download

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Summary of Contents for G-BSCY PA-28-151 1981

Page 1: ...Pilot s Operating Handbook G BSCY Take A V I A T I O N c o m...

Page 2: ...Pilots Operating Handbook POH is for information and to aid ight planning only It should not replace reference to the original documents due to possible updates since publication These are available...

Page 3: ...ordance with STC SA2969SW The information contained herein supplements or supersedes the information in the form of placards markings and approved4tnanual material For limitations procedures and perfo...

Page 4: ...tic RPM at maximum throttle setting Not over 2450 Not under 2350 Diameter Maximum 74 inches Minimum 72 inches I 3 ENGINE INSTRUMENT TACHOMETER 0 MARKINGS Green Arc 2200 2650 RPM Yellow Arc 2650 2700 R...

Page 5: ...ROV E D AEROPLANE FLIGtT MA NUA L FOR TItE P I P ER MODEL PA 28 151 tO Iff D PREPARED IN ACCORDANCE WITH BRITISH CIVIL AIRWORTHINESS REQUIRENENYS SERIAL NUMBER 28 7415001 TO 28 7615999 BY SheehanBY C...

Page 6: ...stration Marks C3 GY 3 Constructor s Serial Number g 76 506 4 Designed and Constructed by Piper Aircraft Corporation Vero Beach Florida U S A 32960 5 F A A Certificate of Airworthiness for Export Numb...

Page 7: ...Drawing 9 E Determination of Temperature in Relation to i S A 10 F Definitions SECTION II LIMITATIONS A Maximum Weight Limitations 14 B Baggage Loading 14 C Fuel System D Centre of Gravity E Power Pla...

Page 8: ...36 37 L Spins M Open Door 37 SECTION IV NORMAL PROCEDURES A Preflight 39 B Walk around Inspection 39 C Before Starting Engine 42 D Starting Engine When Cold E Starting Engine When Hot 43 F Starting En...

Page 9: ...ERFORMANCE A General 52 B Maximum Take off and LAnding Weight for Altitude and Temperature 58 C Take off Procedures and Speeds 60 D Take off Field Lengths 61 E Net Take off Flight Path 67 F En Route P...

Page 10: ...of Wind Velocities 53 Figure 5 Pitot Head Location 54 Figure 6 Position Error Correction to Obtain E A S MP 55 Figure 7 Position Error Correction to Obtain E A S Knots 56 Figure 8 Maximum Take off an...

Page 11: ...e This revision number supersedes the original issue and all previous revisions and contains the latest approved information pertinent to the airplahe Amendments to supplements published by another og...

Page 12: ...ied Battery Capacity 36 5 4 Deleted Propeller Check 45 Changed Example Climb 70 Q Speed at Light Weight CAJ O 1 A Redrawn 72 a 5 2 L5 10 74 R K Deleted Reference to Aero 7 7 batic Manoeuvres 20 Specif...

Page 13: ...T CORP REPORTVB 575 MODEL PA 28 151 c l DEYELO ENT CETE VE1O BEACH FA PACE 8 C A A AMENDMENT RECORD SHEET REVISION DATE OF REVISED APPROVAL PAGES NO REVISION BY DATE CAA REVISION TITLE AFFECTED AY MO...

Page 14: ...I________ R IER A IR C RAFTI CO0R P REPORT VB 575 EYELOPUEIT CERTER VERO BEACH FLA SECTION I GENERAL continued D General Arrangement Drawing not to scale vp FIGURE 1 5 3 _J P3 9 6 rM GIOVID 0...

Page 15: ...MODEL PA 28 151 PAGE IC0 7 iso 7F 9 I J IL I I n I f 1 1 I I I j T tit 1 1 l i I I II L A I 0j F T 4 i i ih 7i i j _a _ i i i I M ER J TUR 1...

Page 16: ...n the charts is pressure altitude which is the expression of atmospheric pressure in terms of altitude above mean sea level according to the inter relation of these factors in the International Standa...

Page 17: ...RFORMANCE The gross performance modified in the manner prescribed in the relevant requirement to make appropriate allowance for those variations from the Gross Performance which are not dealt with in...

Page 18: ...lity errors 13 T A S The True Air Speed of the aeroplance relative to the undisturbed air which is the E A S corrected for altitude and temperature 14 TAKE OFF SAFETY SPEED The minimum speed at which...

Page 19: ...a zero Id I weight limit B Baggage LoadiI The maximum baggage capacity is 200 pounds For acrohat In operation baggage and aft passengers are not allowed C Fuel System I There are no fuel loading limi...

Page 20: ...I It pnilp when switching tanks D Centre of Gravity I The aircraft loading is to be listri tl ed so Ilioo uit centre of gravity ties between the lh lts of 83 0 i aft of the datum at 1950 pounds 87 0...

Page 21: ...1 Ji lJ I 1 1 j 9 ir 1111 I I I I aiy4 g mit I III52 III j1i dY g I9 Lb 16 s LJ 6 i e tI i j i Lt z o iu 5 1 1 55 KI 1950 Lbs 885 Kgs I 1 J 2 86 5 Inches 1 I l T1 T I 2 sted on Vage 22 I i I I I iii i...

Page 22: ...r drain valve not being closed properly after use on Piper PA 28 series aircraft APPLICABILITY Applicable to Piper PA 28 series aircraft fitted with a Curtis fuel strainer drain valve including thode...

Page 23: ...s Static RPM at maximum permissible throttle setting Not over 2375 RPM Not under 2275 RPM No additional tolerance permitted McCauley IC160EGM7653 Diameter 76 Inches Maximum 74 5 Inches Minimum Pitch 5...

Page 24: ...I should be obtained or ex ceeded within 30 seconds when starting the engine Normal Operating Range 60 PSI to 90 PSI Green Arc Caution Range 25 PSI to 60 PSI Yellow Arc Minimum 25 PSI Red Line Maximum...

Page 25: ...not be flown at a speed greater than VNO The aeroplane shall only be flown at speeds between the normal operating limit speed and the tever exceed speed at the discretion of the pilot having due regar...

Page 26: ...STED ON PAGE 22 Is 127 MPH I A S 111 Knots for steep turns Lazy Eights and Chandelles 7 AIRSPEED INDICATOR COLOR MARKINGS Green Arc Normal Operating Range 65 MPH to 140 MPH E A S Yellow Arc Caution Ra...

Page 27: ...8 50 Wings Flaps Extended Range White Arc 119 103 115 100 S N 28 7615001 and up 51 44 58 50 5 Normal operating Range Green Arc 145 126 140 122 58 50 65 56 6 Caution Range Smooth Air Only 185 160 176 1...

Page 28: ...ions 4 FLIGHT AT HIGH ALTITUDE When flying above 10 000 feet it is the pilot s responsibility to consider the phy sical limitations of the pilot and passengers oxygen equipment required and compliance...

Page 29: ...51 structure has been designed to withstand a positive manoeuvring load factor of 4 4 g flaps up 2 0 g with the flaps fully deflected 400 and a negative manoeuvring load factor of 1 76 g flaps up with...

Page 30: ...OkING Smoking is prohibited while the aeroplane is on the grbund and during tnke off nnd landing 11 CLIMATIC CONDITIONS The operating suitability of the aeropl ne has been established for temperatures...

Page 31: ...weight and I S A conditions 15 ADDITIONAL PLACARDS The following placards and markings ore required to be displayed in the aeroplane a Adjacent to upper door latch Engage Latch Before Flight b On the...

Page 32: ...capacity 24 Cal Usable Capacity to bottom of filler neck indicator 17 Gal f On the instrument panel when the oil cooler winterization kit is installed Oil Cooler Winterization Plate to be removed when...

Page 33: ...LOPUE T EAIR VEO DEACH FLA MODEL PA 28 151 APAOU 27 SECTION II LIMITATIONS continued 17 ENGINE STARTER Limit engine starting to 30 second periods 18 STALL WARNING SYSTEM The stall warning system is i...

Page 34: ...common sense Pilots should familiarize themselves with the procedures given in this section and be prepared to take appropriate action should an emergency arise B ENGINE FIRE DURING START Engine fires...

Page 35: ...circumstances Normally flaps should be fully extended for touchdown 3 If you have gained sufficient altitude to attempt a restart proceed as follows a Maintain safe airspeed b Fuel Selector switch to...

Page 36: ...ed as follows I Fuel Selector switch to another tank containing fuel 2 Ele ctric Fuel Pump on 3 Mixture rich 4 Carburetor Heat on 5 Engine Gauges check for an indication of the cause of power loss 6 P...

Page 37: ...ions will be normal C 12 If engine failure was caused by fuel exhaustion power will not be regained after tanks are switched until empty fuel lines are filled which may require up to ten seconds 13 If...

Page 38: ...our pattern using flaps slipping or a combination of these e Touchdowns should normally be made at the lowest possible airspeed with full flaps 5 When committed to a landing a Ignition off b Master Sw...

Page 39: ...a Mixture Control idle cut off b Fuel Selector off c Electric Fuel Pump check off d Master Switch off e Magneto Switch off f Throttle closed g Dive to blow out fire if altitude permits h Proceed with...

Page 40: ...as A dead stick landing can be accomplished Don t change power settings unnecessarily as this may hasten com plete power loss 3 Depending on the circumstances it may be advisable to make an off airpor...

Page 41: ...the nearest airport and let a mechanic investigate the problem Watch the oil pressure gauge for an accompanying loss of pressure J ALTERNATOR FAILURE i Loss of alternator output is detected through a...

Page 42: ...accumulate restoration of full power may not be possible There fore prompt action is required 2 Carburetor heat on See Item K 4 Rill willdecrease slightly and roughness will increase Wait for a decrea...

Page 43: ...worse than no heat at all since it may partially melt ice which will re freeze in the intake system When using carbure tor heat therefore always use full heat and when ice is removed return the contr...

Page 44: ...ION Ill EMERGENCY PROCEDURES continued 1 Slow aircraft to 100 MPH IAS 2 cabin Vents Close 3 Stor Window Open 4 If upper latch is open Latch 5 If olower latch is open a Open top latch b Push door open...

Page 45: ...ction i In Cabin a Avionics turn off to save power and wear on the units b Master Switch turn on c Fuel quantity ensure adequate for flight plus reserve d Master Switch turn off to save battery e Igni...

Page 46: ...k hinges b Right main gear no leaks tires inflated and not excessively worn approximately 4 5 inches piston exposed under static load Check brake blocks and discs for wear and damage c Right wing tip...

Page 47: ...for leaks approximately 3 25 inches piston exposed under static load tire inflated and not excessively worn Tow bar removed and stowed properly m Air Inlets check for foreign matter bottom of cowl an...

Page 48: ...nas secure and undamaged w Baggage Compartment Door close and secure after baggage is properly stored and secured x Navigation and Landing Lights check after master switch and light switches have been...

Page 49: ...switch clockwise and pressing in 6 Throttle control desired setting when the engine fires 7 If engine does not fire within 5 to 10 seconds a Starter disengage b Priming Pump prime with one to three s...

Page 50: ...ure Control advance b Throttle Control retard to desired setting C General Infoi mation for Starting Engine 1 When engine is firing evenly advance throttle to 800 RPM 2 If oil pressure is not indicate...

Page 51: ...lled should be off during taxiing and the electric fuel pump should be off in order to check the operation of the engine driven fuel pump I Before Take off I Warm up engine between 800 RPM and 1200 RP...

Page 52: ...os check right and left Maximum drop 175 RPM Maximum differential drop 50 RPM 5 Carburetor Heat on A drop in RPM indicates proper operation Turn carburetor heat off 6 Throttle Control retard 800 RPM t...

Page 53: ...is manual The performance shown on charts will be reduced by soft wet or grassy surface Avoid fast turns onto the runway followed by immediate thke off especially with a low fuel supply As power is ap...

Page 54: ...a safe altitude has been attained M Normal Climb The climb performance presented on page 72 is based on a climbing speed of 74 Knots IAS 86 MPH IAS at a gross weight of 2325 pounds The electric fuel p...

Page 55: ...proach and Landing Prior to entering the traffic pattern the following landing checklist should be observed 1 Seat Backs erect 2 Seat Belts and Shoulder Harness fastened 3 Fuel Selector on proper tank...

Page 56: ...aeroplane loading It is generally good practice to contact the ground at minimum possible safe speed consistent with existing conditions Normally the best technique for short and slow landings is to u...

Page 57: ...weight P Post Landing After leaving the runway I Electric Fuel Pump off Q Engine Shut Down 1 Radio and Electrical Equipment off 2 Throttle Control closed 3 Mixture Control idle cut off 4 Magneto Switc...

Page 58: ...used in addition to any other correction which may be applicable as indicated by the text It is not permissible to extrapolate the scheduled data beyond the limits of the existing charts Page 59 Maxi...

Page 59: ...uired or enter the chart at a weight 200 lbs heavier than the actual weight Page 72 En Route Performance Ceiling and Gross Rate of Climb Fig 12 To obtain the gross rate of climb enter fig 12 with the...

Page 60: ...110 knots 127 MPH 3 The performance presented in ehis section is based upon the aeroplane using the engine and propellers listed in the Limitations Section of this manual 4 The performance may not be...

Page 61: ...V PERFORMANCE Continued Conversion of Wind VelocitieA Flgurc4 50 c 0 ORTED WIND 200 SV J I D KNIOTS 40 r 4c 20 o0 00 0 1 QD 10 I0 II00 30 i 40 50 Example Reported wind j s 30 Kiots ond 150 relot Ivc...

Page 62: ...head is parallel to the centerline of the aeroplane d A static vent is located in the bottom of the pitot head 7 The position error corrections to be applied to the I A S to obtain E A S are shown in...

Page 63: ...ECTION V PERFORMANCE continued 7 Position Error Correction to obtain E A S a Figure 6 200 1401 K 1r L IfII II L J Jr r l j 1 1 8 P 4 10 ttj i 180 LI I I L I lr rt 1 I I l 411 I II I L fp Al 7 410 4 I...

Page 64: ...EITET NERI BEACH L SECTION V PERFORMANCE continued 7 Position Error Correction to obtain E A S a Figure 7 18 1 V IS 604 K T i 4 160 16 2 It II I v4 I 1202 1 0I Y i II P4100 r Fb i w II i1i i 80 I 60 T...

Page 65: ...rward C G and gross weight are given in the following tables Angle of Bank 00 200 400 I A S E A S I A S E A S I A S E A S MPH Kts MPH Kts MPH Kts MPH Kts MPH Kts MPH Kts Flaps Up 58 50 65 56 60 52 67...

Page 66: ...the arrowed dashed line shows that for an aerodrome altitude of 3800 ft and an air temperature of 25 0 C ISA 180 C 770 F the maximum permissible take off and landing weight is 2220 Lbs 1007 Kgs NOTE T...

Page 67: ...28 151 r I I i I i t T T I i I Jt i T I AXI OFF ING ii j II F TU A D 14 A U IHA till 11 L SP1 LI I Ib b ILIl 1 2o l b i g M I LtiI I I i IT I 1r t i i i i Vl T t I t ii I II 1 i i i 1 2 i I _ _J_ i t...

Page 68: ...flaps up ahd the engine at full throttle accelerate the aeroplane to the take off safety speed of 64 Knots I A S 74 MPH I A S and initiate the lift off This speed applies to all weights and altitudes...

Page 69: ...the take off safety speed of 74 MP I A S 64 Knots 77 mPH E A S 67 Knots This take off safety speed is for all weights and altitudes and lift off should be initiated at this speed Runway Dry Tarmac Run...

Page 70: ...SECTION V PERFORMANCE continued 2 For operation from short dry grass the distances given for a dry tarmac runway should be increased by 6 5 3 The wind correction grids are factored so that 50 of head...

Page 71: ...PA 2 IG F UIE 9 TAE OFF RUN 1U Q II fED l AG 63 TI l s I I I4 l N t i 44 I L I Or n l JNoC LIMN R v 2j 4 It t I I 4 3 t i ai DL t i o t Re 15 10 71 RFI I t I vi II v4 r i r H I I hlH Jt I I t i Rev 2...

Page 72: ...64 Knots 77 MPH E A S 67 KnotS and rotate his take off safety speed is for all weights and altitudes Dry Tarmuac RunWay p jnway ILLUSTRATED EXAMPLE The example given by the arrowed dashed title hows t...

Page 73: ...N V PERFORMANCE continued 2 The wind correction grids are factored so that 507 of headwinds and 1507 of tailwinds are obtained Reported winds may therefore be used directly in the grids 3 For operatio...

Page 74: ...__0 _ 7 I r _ I I LOG I 5 k KC 4 AIaoE DW U 110 I I t _700 600 OFF R j A l wL D k D zirz zr _ tc L _ 160 Z ZL i _ _ i I __ _ __ 7 7 ___ ___ ___ _ ___ 140 _ _ _ _ T AL 7 t k L __ n a c __ __ _Dim L f...

Page 75: ...A S 64 Knots 71 MPH E A S 67 Knots This speed is valid for all weights and altitudes ILLUSTRATED EXAMPLE The example given by the arrowed dashed lines shows that with an air temperature of 240 C I S A...

Page 76: ...ance reduced by a margin of 2 0 gradient 2 The wind correction grids are factored so that 50 of headwinds and 150 of tailwinds are obtained Reported winds may therefore be used directly in the grids A...

Page 77: ...r F GpRij 1 N T TA 9 I FL G TI 17 a hig1 CT R11 1 E I I 7 4 I T I d fJ _ Ar f 1 1 I 12 I II ijj4 5 i i I H J ill I U A _ j L t 2l TI I I 1 I I I I 0 I i...

Page 78: ...II IJATIJh itip lOA I l I 4IVI IT Il II N GlH iI VOTlil POhi i I1I 3 9 3 ll l 1 1 1 16iii4 I A IIIMI _________________ J___42__t till IS W i i U u i llE I fifA I i I ANUA MhL liVlr AltI hlS I 1B VA ri...

Page 79: ...7 Q L Ait oji bikllil 9 0 LII IIAI iu t Il A OB T i 1 l l A i I ilOiD J 11 i i A1iI1i AlI ADI TO I I IIAU I WIGH1lT IIl i I r ll i 01 l FiI VAII AIIji AtJl liiBl osA lIj 1 6 b I IFPIyJ I 1 i CAIIil I...

Page 80: ...SOCIATED CONDITIONS Engine Full Throttle Wing Flaps Retracted Airspeed I A S E A S 2325 Lbs 86 MPH 75 Kts 87 MPH 76 Kts V 1400 Lbs 86 MPH 75 Kts 87 MPH 76 KtE Straight line variation between the point...

Page 81: ...itude which may be assumed when establishing compliance with the operating regulations per taining to en route flight It does not prohibit flying at a higher altitude although at vome altitudes the op...

Page 82: ...PAGE 72 F1 I 4T T L ILI tI I i i I H1 IIII l I I I II I 1 I w J i i T H t hjIi1 lii i II I 7 L L l i Iv 25 E 74 125 T 74...

Page 83: ...PAGE 72 1 T I T T h T T T Tr IF hI TT Fil rI I NP lI Pii 6 C F NRtJT it Ndt LI 1 i i4 2LTi i 14i I IT a I hii 1 1 p 4 1 2 0 I60 00 121011I I II I It J I I PI 800 1 25 3 74 0 GO M 8 R mi 11I 1 25 3 7...

Page 84: ...ANCE continued G Landing Procedures and Speeds 1 LANDING TECHNIQUE For the approach and landing refer to pages 49 50 and 51 2 MAXIMUM CROSSWIND COMPONENT The maximum crosswind component in which the a...

Page 85: ...E A S 65 Knots The flaps are retracted after touchdown and maximum wheel braking is applied Runway Dry Tarmac Runway See Note 2 ILLUSTRATED EXAMPLE The example given by the arrowed 4ashed line shows...

Page 86: ...1ANCE continued 2 For operations from dry grass runways with freshly cut grass and firm subsoil the distances for a dry tarmac runway should be in creased by 8 3 The wind grids are factored so that 50...

Page 87: ...PAGE 76 T A tt EisH Q R ED i I I I Fjliijjj 3d 4 L L L Ij hill 47_ kK 1 LLIT4 1 y T j I IIII I Il i ii it r LI k r l III 1 I lIJ I I KH H 4 I Lll L I if il I I II K I I l I IIt o 14...

Page 88: ...ht of 2325 pounds and a no wind condition ASSOQCIATED CONDITIONS Engine Power 6ff propeller windmilling Wing Flaps Retracted Airspeed 83 MPH I A S 72 Knots 85 MPH E A S 74 Knots The example given by t...

Page 89: ...MODEL PA 23 151 PAGE 78 r j 1 I l F A I 1 I4 il SiiI Y i Ii I II I I III I I Lij 1 I I i I i I I I IH I I J tj7 I I I I 4t7 j214 0 O 24 28 Zl Iji GE KILNETRjIP1...

Page 90: ...corded ot the Record of Supplements sheet C A bupplement is identified by a number which is assigned to each complete supplement and recorded at the beginning of the individual presentation and on the...

Page 91: ...retary of the Civil Aviation Authority and embodied in this manual DATE OF DATE OF AUTHORIZED SUPPLEMENT NAME OF SUPPLEMENT APPROVAL EMBODIMENT SIGNATURE OF NUMBER CONSTRUCTOR TITLE Day Mo Yr Da Mo Yr...

Page 92: ...trim operation e If trim system fails preflight disengage electric pitch trim by pushing the pitch trim switch on the instrument panel to the OFF position If the electric pitch trim does not disengag...

Page 93: ...IC PITCH TRIM INSTALLATION SECTION VI SUPPLEMENTS continued 3 In the cruise configuration malfunction results in 100 pitch change and 200 feet altitude variation 4 In the approach configuration a malf...

Page 94: ...rol III is 640 feet B Procedures i Normal Operation Refer to the current Auto Control 111 Owner s Handbook C Emergency Operation i In case of malfunction turn OFF autopilot 2 In emergency autopilot ma...

Page 95: ...Operation Refer to current Autoflite II Owner s Handbook C Emergency Operation I In case of malfunction press disconnect switch located on the pilot s control wheel 2 Move the switch located on the c...

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