PILOT’S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL

Number and Revised DescriptionofRevisions Signature Code Pages and Date a9-47 thru 9-56 9-57 thru 9-62 9-63 thru 9-68 9-69 thru 9-72 9-73 thru 9-74 Rev. 5 (PR0009 14) continued Rev.6 (PR001221) Rev. 7 (PR010129) Rev. 8 (PRO1 1220) Sep. 14,2000 Date vi 2-7 a VI Page: 0-0-(6) Revision: 8, DECEMBER 20, 2001 vi PA-28R-201, ARROW PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Rev. 10 (PR040310) iv vi-a vi-b 2-7 2-8 8-1 8-la 8-lb 8-2 9-i 9-40 9-87 thru 9-90 Added Warning and moved info,topage iv. Moved info,from page iii. Added page and Rev. 9 toL of R. Added page. Revised para.2.23. Revised para.2.23. Moved info,topage 8-lb and revisedpara.8.1. Added page and revisedpara.8.1. Added page and moved info. from pages 8-1 and 8-2. Moved info,to page 8-lb and revisedpara.8.3. Revised T of C. Revised Section 1. Added pages and Supplement 15. Added Rev. 10 to L of R. Revised para.3.5b. Revised para.3.5e. Revised para.4.5a. Revised para.4.5a. Added Rev. II toL of R. Added Rev. 11 toL of R. Revised Figure 7-21. Revised T of C. Added pages and Supplement 16. Jan.5,2004 Date AlbertJ.Mill March 10,2004 Date ISSUED: JULY 12, 1995 REVISED: OCTOBER 7, 2004 REPORT: VB-1612 vi-a Revision FAA Approval Number and Revised Descriptionof Revisions Signature Code Pages and Date Rev. 9 (PRO4O 105) 111 AlbertJ.Mill Rev. 11 (PRO4 1007) vi-a 3-3 3-5 4-4 4-5 vi-a vi-b 7-21 9-i 9-91 thru 9-108 Page: 0-0-(7) Revision: 11, OCTOBER 7, 2004 vi-a PA-28R-201, ARROW PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Descriptionof Revisions Signature Code Pages and Date Rev. 11 9-109 Added pages (PR041007) thru and Supplement 17. continued 9-112 Linda J.Dicken October 7,2004 Rev. 12 vi-b Added Rev. 12 to L of R. (PR050117) 2-7 Revised and reorganized thru para.2.23 Placards. 2-10 9-96 Revised Section3. 9-98 Revised Section3. 9-100 Revised Section3. 9-108 Revised Section7. LindaJ. Dicken Jan. 17,2005 Rev. 13 vi-b Added Rev. 13 toL of R. (PR050523) 9-i Revised T of C. 9-91 Revised Supplement 16. thru 9-118 9-119 Revised page numbers. thru Linda I.Dicken 9-122 May 23, 2005 Rev. 14 vi-b Added Rev. 14 toL of R. (PR050912) 2-5 Revised para.2.15. 9-94 Moved info,from page 9-95. 9-95 Moved info,to page 9-94 and Linda J.Dicken revisedSection2. Sept. 12,2005 Rev. 15 vi-b Added Rev. 15 toL of R. (PRO51 128) 9-96 Revised Section3. 9-99 Revised Section3. 9-101 Revised Section3. 9-103 Revised Section3. Lind’aI.Dicken 9-104 Revised Section3. Nov. 28, 2005 REPORT: VB-1612 ISSUED: JULY 12, 1995 vi-b REVISED: NOVEMBER 28, 2005 Page: 0-0-(8) Revision: 15, NOVEMBER 28, 2005 vi-b PA-28R-201, ARROW PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Descriptionof Revisions Signature Code Pages and Date Rev. 16 vi-c Added page and Rev. 16 to (PR060109) LofR. vi-d Added page. 9-i Revised T of C. 9-91 Revised Supplement 16. thru Linda J.Dicken 9-118 Jan. 9, 2006 Rev. 17 vi-c Added Rev. 17 to L of R. (PR06041 1) 9-111 Revised Section7A. Linda J.Dicken April 11,2006 Rev. 18 vi-c Added Rev. 18 to L of R. (PR060522) 9-i Revised T of C. 9-123 Added pages and thru Supplement 18. Lin1a J.Dicken 9-158 May 22, 2006 Rev. 19 vi-c Added Rev 19 to L of R. (PR090121) 9-u Added Supplements 19 and 20 to T of C. All’ertJ Mill 9-159 Added Supplements 19 and Januy 21, 2009 thru 20. 9-172 Rev. 20 vi-c Added Rev. 20 to L of R. (PR0905 10) 9-92 Revised wording in Para. Section 1 of Supp. 16. 9-124 Revised wording in Para. Albert J Mill Section 1 of Supp. 18. May 10, 2009 Rev. 21 vi-c Added Rev. 21 to L of R. 8-lb Revised wording in (PR090930) 4-20 Revised Para.4.13d General Section. Albert 3 Mill September 30,2009 ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: SEPTEMBER 30, 2009 VC Page: 0-0-(9) Revision: 21, SEPTEMBER 30, 2009 vi-c PA-28R-201, ARROW PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) 4-ui 4-iv 4-7 4-8 4-9 4-10 4-11 4-1 4-13 4-18 4-18a 4-18b 4-20 7-29 7-32 9-u 9-107 9-144 9-173 thru 9-184 Added Rev. 22 toL of R Added Note to Para.2.23 Revised TOC. Relocated text topg. 4-u. Added textfrom pg. 4-i. Revised TOC. Relocated text topg. 4-ui. Added textfrom pg. 4-u. Revised TOC. Relocated textto pg. 4-iv. Added textfrom pg. 4-ui. Revised Para.4.5c.Relocated texttopg. 4-8. Added textfrom pg. 4-7. Relocated texttopg. 4-9. Added textfrom pg. 4-8. Relocated texttopg. 4-10. Added textfrom pg. 4-9. Relocated texttopg. 4-11. Added textfrom pg. 4-10. Relocated textto pg. 4-12. Added textfrom pg. 4-11. Relocated textto pg. 4-13. Added textfrom pg. 4-12. Moved textto pg. 4-18a. Added Page Added Page. Revised Para.4.13d. Revised Para.7.39. Revised Para.7.39. Added Supplement 21 to TofC. Revised Note in Section4. Revised Note in Section4. Added Supplement 21. Vayne E. Gaulzetti May 12,2010 REPORT: VB-1612 ISSUED: JULY 12, 1995 REVISED: MAY 12,2010 Revision FAA Approval Number and Revised Descriptionof Revisions Signature Code Pages and Date Rev. 22 (PR100512) vi-d 2-8 4-i 4-u vi-d Page: 0-0-(10) Revision: 22, MAY 12, 2010 vi-d PA-28R-201, ARROW PILOTS OPERATING HANDBOOK LOG OF REVISIONS (cont) vi-f 9-181 11 vi-e 9-il 9-185 9-186 Updated copyrightdates. Added Page. Added Rev. 23 to L of R. Added Page. Revised Section 4. Updated copyrightdate. Added Rev. 24 to L of R. Revised T of C. Added page. Added Supplement 22. Added page. AIb’rt J.Mill November 1,2010 Wayne E. Gaulzetti October 24, 2011 Revision FAA Approved Number and Revised Descriptionof Revisions Signature Code Pages and Date 11 vi-e Rev. 23 (PR 10 110 1) Rev. 24 (PR1 11024) ISSUED: JULY 12, 1995 fl1 1 REPORT: VB-1612 Page: 0-0-(11) Revision: 24, OCTOBER 24, 2011 vi-e PA-28R-201, ARROW PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approved Number and Revised Descriptionof Revisions Signature Code Pages and Date REPORT: VB-1612 ISSUED: JULY 12, 1995 vi-f REVISED: NOVEMBER 1, 2010 Page: 0-0-(12) Revision: 23, NOVEMBER 1, 2010 vi-f PA-28R-201, ARROW TABLE OF CONTENTS SECTION 1 GENERAL SECTION 2 LIMITATIONS SECTION 3 EMERGENCY PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT AND BALANCE SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AN]) ITS SYSTEMS SECTION 8 AIRPLANE HANDLING, SERVICING AN]) MAINTENANCE SECTION 9 SUPPLEMENTS SECTION 10 OPERATING TIPS 0 ISSUED: JULY 12, 1995 REPORT: VB-1612 Page: 0-0-(13) Issued: JULY 12, 1995 vii PA-28R-201, ARROW 0 THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12,1995 vu’ Page: 0-0-(14) Issued: JULY 12, 1995 viii SECTION 1 PA-28R-201, ARROW GENERAL TABLE OF CONTENTS SECTION 1 GENERAL Paragraph Page No. No. 1.1 Introduction 1-1 1.3 Engines 1-3 1.5 Propellers 1-3 1.7 Fuel 1-4 1,9 Oil 1-4 1.11 Maximum Weights 1-5 1.13 Standard AirplaneWeights 1-5 1.15 BaggageSpace 15 1.17 SpecificLoadings 1-5 1.19 Symbols, Abbreviationsand Terminology 1-6 ISSUED: JULY l2, 1995 REPORT: VB-1612 Page: 1-0-(1) Issued: JULY 12, 1995 1-i SECTION GENERAL PA-28R-201, ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12,1995 1-il Page: 1-0-(2) Issued: JULY 12, 1995 1-ii SECTION 1 PA-28R-201, ARROW GENERAL SECTION I GENERAL 1.1 INTRODUCTION This Pilot’sOperating Handbook is designed for maximum utilization as an operating guide for the pilot.Itincludes the material required to be furnished to the pilotby the Federal Aviation Regulations and additional information provided by the manufacturer and constitutes the FAA Approved Airplane FlightManual. This handbook is not designed as a substitute for adequate and competent flightinstruction,knowledge of currentairworthinessdirectives, applicablefederalairregulationsor advisory circulars.Itis not intended to be a guide for basicflightinstructionor a trainingmanual and should not be used for operationalpurposes unless kept in a currentstatus. Assurance that the airplane is in an airworthy condition is the responsibilityof the owner. The pilot in command is responsible for determining thatthe airplaneissafe for flight.The pilotisalso responsible for remaining within the operating limitationsas outlined by instrument markings, placards,and thishandbook. Although the arrangement of thishandbook is intended to increaseits in-flightcapabilities, itshould not be used solelyas an occasionaloperating reference.The pilotshould study the entirehandbook to familiarizehimself with the limitations,performance, procedures and operational handling characteristics of the airplanebefore flight. The handbook has been divided into numbered (arabic)sections,each provided with a finger-tiptab dividerfor quick reference.The limitations and emergency procedures have been placed ahead of the normal procedures, performance and other sections to provide easier access to information that may be required in flight.The Emergency Procedures Section has been furnished with a red tab divider to present an instant reference to the section.Provisions for expansion of the handbook have been made by the deliberateomission of certainparagraph numbers, figure numbers, item numbers and pages noted as being intentionallyleftblank. ISSUED: JULY 12,1995 REPORT: VB-1612 1-i Page: 1-1-(0) Issued: JULY 12, 1995 1-1 I GENERAL THREE VIEW Figure 1-1 PA-28R-201, ARROW 170.0 31.0 1.00 Wing Area(sq.ft.) Mi,,.TurningRadius(ft) (frompivotpointtowing tip) REPORT: VB-1612 1-2 ISSUED: JULY 12,1995 Page: 1-2-(0) Issued: JULY 12, 1995 1-2 SECTION 1 PA-28R-201, ARROW GENERAL 1.3 ENGINES (a)Number ofEngines 1 (b) Engine Manufacturer Lycoming (c) Engine Model Number 10-360-C 1C6 (d) Rated Horsepower 200 Ce) Rated Speed (rpm) 2700 (I) Bore(in.) 5.125 (g) Stroke (in.) 4.375 (h) Displacement (Cu.in.) 361 (1) Compression Ratio 8.7:1 (j) Engine Type Four Cylinder,Direct Drive,Horizontally Opposed, Air Cooled and Fuel Injected 1.5 PROPELLERS McCAULEY (a) Number of Propellers 1 (b) PropellerManufacturer McCauley (c) Blade Model 9ODHA- 16 Cd) Number of Blades 2 (e) Hub Model B2D34C213 (f) PropellerDiameter (in.) (1) Maximum 74 (2) Minimum 73 (g) Propeller7’pe ConstantSpeed, HydraulicallyActuated ISSUED: JULY 12, 1995 REPORT: VB.1612 Page: 1-3-(0) Issued: JULY 12, 1995 1-3 SECTION 1 GENERAL PA-28R-201, ARROW 1.5 PROPELLERS (continued) HARTZBLL (a) Number of Propellers (b) PropellerManufacturer (c) Blade Model (d) Number ofBlades (e) Hub Model (f) PropellerDiameter (in.) (1) Ma2dmum (2) Minimum (g) PropellerIype 1.7 FUEL (a) Fuel Capacity(U.S.gal.)(total) (b) Usable Fuel (U.S.gal.)(total) (c) Fuel Grade, Aviation (1) Minimum Octane (a) Oil Capacity(U.S.qts.) (b) Oil Specification I Hartzell F7666A-2R 2 HC-C2YK-1( )F/ 74 72 ConstantSpeed, HydraulicallyActuated 77 72 100/130 Green or 10011-Blue AviationGrade Refer tolatestrevision ofLycoming Service Instruction1070, exceptalcoholisnot approved foruse inthis airplane. M1L-I-27686D isapproved. 8 Refertolatestissue ofLycoming Service Instruction1014 Refer toSection8 paragraph8.19 (2) AlternateFuels 1.9 OIL (c) OilViscosity REPORT: VB-1612 1-4 ISSUED: JULY 12, 1995 Page: 1-4-(0) Issued: JULY 12, 1995 1-4 SECTION 1 PA-28R-201, ARROW GENERAL 1.11 MAXIMUM WEIGHTS (a) Maximum Takeoff Weight (lb.) 2750 (b) Maximum Landing Weight (lb.) 2750 (c) Maximum Weights in Baggage Compartment 200 1.13 STANDARD AIRPLANE WEIGHTS* (a) StandardEmpty Weight (lb.): Weight of a standardairplaneincluding unusablefueL fulloperatingfluidsand fulloil. 1603 (b) Maximum Useful Load (lb.): The differencebetween the Maximum Takeoff Weight and the Standard Empty Weight. 1147 1.15 BAGGAGE SPACE (a) Compartment Volume (cu.ft.) 24 (b) Entry Width (in.) 22 (c) Entry Height (in.) 20 1.17 SPECIFIC LOADINGS (a) Wing Loading (lb.per sq.ft.) 16.18 (b) Power Loading (lb.per hp) 13.75 *These values are approximate and vary from one aircraftto another.Refer to Figure 6-5 for the Standard Empty Weight value and the Useful Load value tobe used forC.G. calculationsfor the aircraft specified. ISSUED: JT.JLY 12,1995 REPORT: VB-1612 Page: 1-5-(0) Issued: JULY 12, 1995 1-5 SECTION 1 GENERAL PA-28R-201, ARROW 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY The following definitions are of symbols, abbreviations and terminology used throughout the handbook and those which may be of added operationalsignificanceto thepilot. (a) GeneralAirspeed Terminology and Symbols CAS Calibrated Airspeed means the indicated speed of an aircraft, correctedfor position and instrument error.Calibrated airspeed is equal to true airspeed in standard atmosphere atsea level. KCAS CalibratedAirspeedexpressedin Knots. GS Ground Speed is the speed of an airplane relativeto theground. lAS Indicated Airspeed is the speed of an aircraft aircraft as shown on the airspeed indicator when corrected for instrument error.lAS values published in thishandbook assume zero instrumenterror. KIAS IndicatedAirspeed expressedin Knots. M Mach Number isthe ratioof true airspeed to thespeed of sound. TAS True Airspeed isthe airspeedof an airplane relative to undisturbed air which is the CAS corrected for altitude,temperature and compressibility. VA Maneuvering Speed isthe maximum speed at which application of full available aerodynamic controlwillnot overstressthe airplane. Maximum Flap Extended Speed is the highest speed permissiblewith wing flaps ina prescribedextendedposition. REPORT: VB-1612 ISSUED: JULY 12, 1995 1.6 Page: 1-6-(0) Issued: JULY 12, 1995 1-6 SECTION 1 PA-28R-201, ARROW GENERAL 1.19 SYMBOLS, ABBREVIATIONS, AND TERM]NOLOGY (continued) VLE Maximum Landing Gear Extended Speed is the maximum speed at which an aircraft can be safely flown with the landing gear extended. VI.o Maximum Landing Gear Operating Speed is the maximum speed at which the landing gearcan be safelyextended or retracted. VwnfMwE Never Exceed Speed or Mach Number isthe speed limitthatmay not be exceeded at any time. VNO Maximum StructuralCruising Speed is the speed thatshould not be exceeded except in smooth airand then only with caution. Vs StallingSpeed or the minimum steady flight speed atwhich theairplaneiscon- troflable. Vso StallingSpeed or the minimum steadyflight speed at which the airplaneiscon- trollable inthelanding configuration. Vx Best Angle-of-Climb Speed is the airspeed which deliversthe greatestgain of altitude in theshortestpossiblehorizontaldistance. Best Rate-of-Climb Speed is the airspeed which deliversthegreatestgain in altitude in theshortestpossibletime. ISSUED: JULY 12,1995 REPORT: VB-1612 Page: 1-7-(0) Issued: JULY 12, 1995 1-7 SECTION 1 GENERAL PA-28R-201, ARROW 1.19 SYMBOLS, ABBREVIATIONS, AND TERMINOLOGY (continued) (b) MeteorologicalTerminology ISA International Standard Atmosphere in which: (1) Theairisadryperfectgas. (2) The temperatureatsea levelis15°Celsius Celsius (59°Fahrenheit). (3) The pressureatsea levelis29.92 inches Hg (1013.2mb). (4) The temperaturegradientfrom sea level to the altitudeatwhich the temperature is -56.5°C (-69.7°F) is 0.00198°C (-0.003564°F)per foot and zero above thataltitude. OAT OutsideAir Temperature isthe freeairstatic temperature,obtained eitherfrom inflight temperature indications or ground meteorological sources, adjusted for instrument instrument errorand compressibility effects Indicated The number actually read from an PressureAltitude altimeterwhen the barometricsubscalehas been setto 29.92 inchesof mercury (1013.2 millibars). PressureAltitude Altitudemeasured from standard sea-level pressure (29.92 in.Hg) by a pressure or barometric altimeter.It is the indicated pressurealtitudecorrectedfor positionand instrument error. In this handbook, altimeter instrument errors are assumed to be zero. StationPressure Actual atmospheric pressure at field elevation. Wmd The wind velocitiesrecorded as variables on the charts of thishandbook are to be understood as the headwind or tailwind components of thereportedwinds. REPORT: VB-1612 ISSUED: JULY 12,1995 1-8 Page: 1-8-(0) Issued: JULY 12, 1995 1-8 SECTION 1 PA.28R-201, ARROW GENERAL 1.19 SYMBOLS, ABBREVIATIONS, AN]) TERMINOLOGY (continued) (c) Power Terminology Takeoff Power Maximum power permissiblefortakeoff. Maximum Con- Maximum power permissiblecontinuously tinuousPower during flight. Maximum Climb Maximum power permissible during Power climb. Maximum Cruise Maximum power permissible during Power cruise. (d) Engine Instruments EGT Gauge Exhaust Gas Temperature Gauge (e) AirplanePerformance and FlightPlanningTerminology Climb Gradient The demonstrated ratio of the change in height during a portion of a climb, to the horizontaldistance traversed in the same time interval. Demonstrated The demonstratedcrosswind velocityisthe Crosswind velocityof the crosswind component for Velocity which adequate control of the airplane during takeoff and landing was actually demonstratedduring certification tests. Accelerate-Stop The distancerequired to acceleratean air- Distance plane to a specifiedspeed and, assuming failureof an engine atthe instantthatspeed isattained, tobringthe airplaneto a stop. MBA Minimum en routeIFR altitude. Route Segment A part of a route.Each end of that partis identifiedby: (1) a geographical location; or (2) a point at which a definiteradio fix can be established. ISSUED: JULY 12,1995 REPORT: VB.1612 Page: 1-9-(0) Issued: JULY 12, 1995 1-9 L GENERAL PA-28R-201, ARROW 1.19 SYMBOLS, ABBREVIATIONS, AND TERMINOLOGY (continued) (f) Weight and Balance Terminology Reference Datum An imaginary verticalplane from which all horizontal distances are measured for balance purposes. Station A location along the airplane fuselage usuallygiven in terms of distancefrom the referencedatum. Arm The horizontaldistancefrom the reference datum to the centerof gravity(C.G.) of an item. Moment The product of the weight of an item multiplied multiplied by itsarm. (Moment divided by a constantis used to simplifybalance calculations calculations by reducingthenumber of digits.) Center of Gravity The point at which an airplane would (C.G.) balance ifsuspended. Itsdistancefrom the reference datum is found by dividing the totalmoment by the totalweight of the airplane. C.G. Arm The arm obtained by adding the airplane’s individualmoments and dividingthe sum by thetotalweight. C.G. Limits The extreme center of gravity locations within which the airplanemust be operated ata given weight. Usable Fuel Fuel availableforifightplanning. Unusable Fuel Fuel remaining aftera runout testhas been completed in accordance with governmental governmental regulations. StandardEmpty Weight of a standard airplane including Weight unusable fuel,fulloperatingfluidsand full oil. REPORT: VB-1612 ISSUED: JULY 12, 1995 1-10 Page: 1-10-(0) Issued: JULY 12, 1995 1-10 SECTION 1 PA-28R-201, ARROW GENERAL 1.19 SYMBOLS, ABBREVIATIONS, AND TERMINOLOGY (continued) Basic Empty Standard empty weight plus optional Weight equipment. Payload Weight of occupants,cargo and baggage. Useful Load Difference between takeoff weight, or ramp weight ifapplicable,and basic empty weight. MaximumRamp Maximum weight approved for ground Weight maneuver. (Itincludesweight of start,taxi and run up fuel.) Maximum Maximum weight approved forthe startof Takeoff Weight thetakeoffrun. Maximum Maximum weight approved for the landing Landing Weight touchdown. Maximum Zero Maximum weight exclusiveof usablefuel. Fuel Weight ISSUED: JULY 12,1995 REPORT: VB-1612 Page: 1-11-(0) Issued: JULY 12, 1995 1-11 SECTION 1 GENERAL PA-28R-201, ARROW THIS PAGE INTENTIONALLY LEFT BLANK 0 REPORT: VB-1612 ISSUED: JULY 12,1995 1-12 Page: 1-12-(0) Issued: JULY 12, 1995 1-12 SECTION 2 PA-28R-201, ARROW LIMITATIONS TABLE OF CONTENTS SECTION 2 LiMITATIONS Paragraph Page No. No. 2.1 General 2-1 2.3 Airspeed Limitations 2-1 2.5 Airspeed IndicatorMarkings 2-2 2.7 Power PlantLimitations 2-3 2,9 Power PlantInstrumentMarkings 2-4 2.11 Weight Lmii 2-5 2.13 Center of GravityLum 2-5 2.15 Maneuver Lami 2-5 2.17 FlightLoad Factors 2-6 2.19 I,pes of Operations 2-6 2.21 Fuel Limitations 2-6 2.23 Placards 2-8 ISSUED: JULY 12,1995 REPORT: VB-1612 Page: 2-0-(1) Issued: JULY 12, 1995 2-i SECTION 2 LIMiTATIONS PA-28R-201, ARROW TElLS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12,1995 2-li Page: 2-0-(2) Issued: JULY 12, 1995 2-ii SECTION 2 PA-28R-201, ARROW LIMITATIONS SECTION 2 LIMiTATIONS 2.1 GENERAL This section provides the FAA Approved operating limitations, instrumentmarkings, color coding and basic placardsnecessaryfor the safe operationof the airplaneand itssystems. Limitations associated with those optional systems and equipment which require handbook supplements can be found in Section 9 (Supplements). 2.3 AIRSPEED LIMITATIONS SPEED KIAS KCAS Never Exceed Speed (Van) Do not exceed thisspeed in any operation. 183 186 Maximum StructuralCruisingSpeed (VNO) Do not exceed thisspeed except in smooth airand then only with caution. 146 148 Design Maneuvering Speed (VA) Do not make ftllor abruptcontrolmovements above thisspeed. At27501bs.G.W. 118 120 At18651bs.G.W. 96 96 CAUTION Maneuvering speed decreasesat lighterweight as the effectsof aerodynamic forces become more pronounced. Linear interpolationmay be used for intermediate gross weights. Maneuvering speed should not be exceeded while operatinginrough air. ISSUED: JULY 12, 1995 REPORT: YB-1612 Page: 2-1-(0) Issued: JULY 12, 1995 2-1 SECTION 2 LTh1ITATIONS PA-28R-201, ARROW 2.3 AIRSPEED LIMITATIONS (continued) SPEED KIAS KCAS Maximum FlapsExtended Speed (Vin) Do not exceed thisspeed withthe flaps extended. 103 103 Maximum Landing Gear ExtensionSpeed Do not exceed thisspeed when extending thelandinggear. 129 130 Maximum Landing Gear RetractionSpeed Do not exceed thisspeed when retracting thelandinggear. 107 107 Maximum Landing Gear Extended Speed (VLE) Do notexceed thisspeed with the landinggear extended. 129 130 2.5 AIRSPEED INDICATOR MARKINGS MARKING lAS Red RadialLine (Never Exceed) 183 KTS Yellow Arc (CautionRange Smooth Air Only) 146 KTS to 183 KTS Green Arc (Normal OperatingRange) 60 KTS to146 KTS White Arc (FlapDown) 55 KTS to 103 KTS C) REPORT: VB-1612 ISSUED: JULY 12,1995 2.2 Page: 2-2-(0) Issued: JULY 12, 1995 2-2 SECTION 2 PA-28R-201, ARROW LIMITATIONS 2.7 POWER PLANT LIMITATIONS (a) Number of Engines I (b) Engine Manufacturer Lycoming (c) Engine Model No. IO-360-C1C6 (d) Engine OperatingLimits (1) Maximum Horsepower 200 (2) Maximum RotationSpeed (RPM) 2700 (3) Maximum Oil Temperature 245°F (e) Oil Pressure Minimum (redline) 25 PSI Maximum (redline) 100 PSI (f) Fuel How/Pressure Maximum (redline) 21.4 GPHJ12 PSI (g) Fuel Grade (minimum octane) 100 or IOOLL AviationGrade (h) Number of Propellers I (i) PropellerManufacturer McCauley orHaxtzell (j) PropellerHub and Blade Model (1) McCauley B2D34C213/9ODHA-16 (2) Hartzell HC-C2YK-1( )F/ F7666A-2R (k) PropellerDiameter (1) McCauley Minimum 73 Maximum 74 (2) Hartzell Minimum 72 Maximum 74 (1) Blade Angle Limits (1) McCauley Low PitchStop 12.5+ 0.2° High PitchStop 27.5 + 0.5° (2) Hartzell Low PitchStop 14.0÷ 02° High PitchStop 29.0÷ 2.0° (m) RPM Restriction Avoid continuous (McCauley PropellerOnly) operationbetween 1500 and 1950 rpm below 15 inches manifold pressure. ISSUED: JULY 12,1995 REPORT: VB-1612 Page: 2-3-(0) Issued: JULY 12, 1995 2-3 JI.L1UJN L LIMITATIONS PA-28R-201, ARROW 2.9 POWER PLANT INSTRUMENT MARKINGS (a) Tacbometer Green Arc (Normal OperatingRange) 500 to 2700 RPM Red Line (Maximum Continuous Power) 2700 RPM (b) Oil Temperature Green Arc (Normal OperatingRange 75° to 245°F Red Line (Maximum) 245°F (c) Oil Pressure Green Arc (Normal OperatingRange 60 PSI to90 PSI Yellow Arc (CautionRange) (Idle) 25 PSI to60 PSI Yellow Arc (CautionRange) (Startand Warm-up) 90 PSI to 100 PSI Red Line (Minimum) 25 PSI Red Line (Maximum) 100 PSI (d) Fuel Flow! Pressure Green Arc (Normal OperatingRange 2 GPHJO.05 PSI to 21.4 GPHI12 PSI Red Line (Maximum) 21.4 GPHJ12 PSI fl REPORT: VB-1612 ISSUED: JULY 12,1995 Page: 2-4-(0) Issued: JULY 12, 1995 2-4 SECTION 2 PA-28R-201, ARROW LIMITATIONS 2.11 WEIGHT LIMITS (a) Maximum Weight 2750 LBS. (b) Maximum Baggage 200 LBS. NOTE Refer to Section 5 (Performance) for maximum weight as limitedby performance. 2.13 CENTER OF GRAVITY LIMITS Weight Pounds Forward Limit Inches Aft of Datum Rearward Limit Inches Aft of Datum 2750 88.9 91.5 2375 and 82.0 91.5 Below NOTES Straightlinevariationbetween points given. The datum used is 78.4 inches ahead of the wing leading edge at the intersection of the straightand tapered section. It is the responsibilityof the airplane owner and the pilot to insure that the airplane is properly loaded. See Section 6 (Weight and Balance) for proper loading instructions. 2.15 MANEUVER LIMITS No acrobaticmaneuvers includingspins. Approved maneuvers which do not exceed 60° of bank and 30° of pitch: Steep Turns Lazy Eights Chandelles ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: SEPTEMBER 12,2005 2-5 Page: 2-5-(0) Revision: 14, SEPTEMBER 12, 2005 2-5 • LIMITATIONS PA-28R-201, ARROW 2.17 FLIGHT LOAD FACTORS (a) PositiveLoad Factor(Maximum) 3.8 0 (b) Negative Load Factor (Maximum) No invertedmaneuve approve 2.19 TYPES OF OPERATIONS The airplaneis approved for the following operationswhen equipped in accordance with FAR 91 or FAR 135. (a) Day VER. (b) Night V.F.R. (c) Day I.RR. (d) Night I.ER. (e) Non Icing 2.21 FUEL LIMITATIONS (a) TotalCapacity 77 U.S. GAL. (b) Unusable Fuel 5 U.S. GAL. The unusable fuelforthisairplanehas been determined as 2.5 gallonsin each wing tank in critical flightattitndes. (c) Usable Fuel 72 U.S. GAL. The usable fuelin thisairplanehas been determined as 36.0 gallonsin each wing tank. (d) Fuel remaining when the quantityindicators indicators read zero cannot be used safely in flight. (n REPORT: VB-1612 ISSUED: JULY 12,1995 2-6 Page: 2-6-(0) Issued: JULY 12, 1995 2-6 PA-28R-201, ARROW SECTION 2 LIMITATIONS 2.23 PLACARDS In fullview of the pilot: On the instrumentpanel in fullview of the pilot(notrequired ifAvidyne Entegra isinstalled): NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED Above fuelquantitygauges (notrequiredifAvidyne Entegra isinstalled): FUEL REMAINING WHEN THE QUANTITY INDICATORS READ ZERO CANNOT BE USED SAFELY IN FLIGHT. On the instrumentpanel in fullview of the pilot(not requiredifAvidyne Entegra isinstalled): WARNING TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY TO GROUND OR DURING FLIGHT THROUGH CLOUD, FOG OR HAZE. On the instrumentpanel in fullview of the pilot: GEAR DOWN GEAR UP EXTENDED 129 KIAS (MAX.) 107 KIAS (MAX.) 129 KIAS (MAX.) ISSUED: JULY 12, 1995 REVISED: JANUARY 17, 2005 REPORT: VB-1612 2-7 4- LIMITATIONS THISAIRCRAFTAPPROVED FOR NIGHT I.F.R., HON-ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR St OR FAR 135. NO ACROBATIC MANEUVERS, INCLUDINGSPINS,APPROVED. THISAIRCRAFT MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE 11TH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. FUEL REMAINING WHEN THE QUANTITY INDICATORSREAD ZERO CANNOT BE USED SAFELY IN FLIGHT. INFORMATION —4 OIL COOLER WINTER IZATTON PLATE TO BE REMOVED WHEN AMBIENT TEMPERATUREEXCEEDS 50’F. VIARNING TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY IHYV OR DURING 0000 CLOUD. FOR OR HAZE. Page: 2-7-(0) Revision: 12, JANUARY 17, 2005 2-7 SECTION 2 LIMITATIONS PA-28R-201, ARROW 2.23 PLACARDS (continued) (SerialNumbers 2844001 through 2844021 only) In fullview of the pilot, the followingTakeoff and Landing Checklistswillbe installed: TAKEOFF CHECKLIST Fuel on Proper Tank Fasten Belts/Harness ElectricFuel Pump On Flaps Set Engine Gauges Checked Trim Tab Set AlternateAir Closed Controls Free Seat Backs Erect Doors Latched Mixture Set Air Conditioner Off Propeller Set LANDING CHECKLIST Fuel on Proper Tank Propeller Set Seat Backs Erect Gear Down Fasten Belts/Harness Flaps Set (White Arc) ElectricFuel Pump On Air Conditioner Off Mixture Rich The Air Conditioner Off item in the above Takeoff and Landing Checklistsismandatory forairconditionedaircraftonly. On the instrumentpanel in fullview of the pilot(not requiredifAvidyne Entegra isinstalled): MANEUVERING SPEED 118 KIAS AT 2750 LBS. (SEE P.O.H.) On the instrument panel in fullview of the pilot(notrequiredifAvidyne Entegra isinstalled): DEMONSTRATED CROSSWIND COMPONENT 17 KTS On the instrumentpanel in fullview of the pilot(only requiredifAvidyne Entegra isinstalled): VA- 118 KIAS AT 2750#(SEE POH) DEMO. X-WIND 17 KTS. NOTE Demonstrated crosswind valuesareNOT limitations. REPORT: VB-1612 ISSUED: JULY 12, 1995 2-8 REVISED: MAY 12, 2010 Page: 2-8-(0) Revision: 22, MAY 12, 2010 2-8 SECTION 2 PA-28R-201, ARROW LIMITATIONS 2.23 PLACARDS (continued) On the instrumentpanel in fullview of thepilotinaircraft with McCauley propellerinstallations only: AVOID CONTINUOUS OPERATIONS BETWEEN 1500 AND 1950 RPM BELOW 15” MANIFOLD PRESSURE. In fullview of pilot: CAUTION COMPASS CAL. MAY BE IN ERROR WiTH ELECT. EQUIPMENT OTHER THAN AVIONICS ON In fullview of the pilot,in the area of the airconditionercontrols,when theairconditionerisinstalled: WARNING AIRCONDITIONER MUST BE OFF TO INSURE NORMAL TAKEOFF CLIMB PERFORMANCE. In fullview of thepilotand passengers(serial numbers 2844012 and up): NO SMOKING Near emergency gear lever: EMERGENCY DOWN Near gear selectorswitch: GEAR UP 107 KIAS MAX. DOWN 129 KIAS MAX. ISSUED: JULY 12,1995 REPORT: VB-1612 REVISED: JANUARY 17,2005 2-9 Page: 2-9-(0) Revision: 12, JANUARY 17, 2005 2-9 SECTION 2 LIMITATIONS PA-28R-201, ARROW 2.23 PLACARDS (continued) On theaftbaggage closeout: MAXIMUM BAGGAGE 200 LBS. NO HEAVY OBJECTS ON HAT SHELF. Adjacent toupper door latch: ENGAGE LATCH BEFORE FLIGHT On insideof baggage compartment door: BAGGAGE MAX. 200 LBS. SEE WEIGHT AND BALANCE DATA FOR BAGGAGE LOADINGS BETWEEN 150 LBS. AND 200 LBS. Adjacent tofueltank filler caps: AVGAS ONLY GRADE GRADE IOOLL 100 0 REPORT: VB-1612 ISSUED: JULY 12,1995 2-10 REVISED: JANUARY 17,2005 Page: 2-10-(0) Revision: 12, JANUARY 17, 2005 2-10 / /?J?-f (HB-2008-135R1) ,;74:;t.1 (tef.. ATTN: Solomon Hecht,AerospaceEngineer,BostonACO, 12 New EnglandExecutivePark, Burlington, MA 01803;telephone:(781)238-7159;fax:(781)238-7170.Beforeusingany approved AMOC on any airplane to which theAMOC applies, notifyyour appropriate principal inspector(P1) intheFAA FlightStandardsDistrict Office(FSDO), or lackinga PT,your localFSDO. AdditionalInformation (g)For theservicealertreferencedinthisAD, contactAvidyne Corporation, 55 Old Bedford Road, Lincoln,MA 01773;telephone:(781)402-7400;fax:(781)402-7599. Appendix to AD 2008-06-28Ri LimitationsRegarding Avidyne Primary FlightDisplays (PFDs) Beforeconductingflightoperations, pilotsmust reviewand be familiar withtheCrosscheck Monitor sectionof theAvidyne PrimaryFlightDisplayPilot’s Guide and alllimitations containedin theairplaneflight manual,pilot’s operatinghandbook,or aircraft operatinghandbook. As a normalpractice, allpilotsshouldbe vigilant inconductingproperpreflight and in-flight checksof instrumentaccuracy,including: • Preflight checkof theaccuracyof boththeprimaryand backupaltimeter againstknown airfield elevationand againsteach other. • Verification ofairspeedindications consistent withprevailing conditions atstartup, duringtaxi, and priortotakeoff. • “Airspeedalive”checkand reasonableindications duringtakeoffroll. • Maintenanceof currentaltimetersetting inbothprimaryand backupaltimeters. • Cross-checkofprimaryand backup altimeters ateach changeof altimeter settingand priorto enteringinstrumentmeteorological conditions (IMC). • Cross-checkofprimaryand backup altimeters and validation againstotheravailabledata,suchas glideslopeintercept altitude, priortoconductingany instrumentapproach. • Periodiccross-checks of primaryand backup airspeedindicators, preferably incombinationwith altimeter cross-checks. For flight operations underinstrumentflight rules(IFR)or inconditions inwhich visual referenceto thehorizoncannotbe reliably maintained(thatisIMC, nightoperations, flight operationsoverwater,inhaze or smoke) and thepilothas reasonstosuspectthatany source(PFD or back-upinstruments) of attitude, airspeed, oraltitude isnotfunctioning properly, flightunderIFR or intheseconditionsmust notbe initiated (when conditionisdeterminedon theground)and further flightunderllR or intheseconditionsisprohibited untilequipmentisservicedand functioning properly. Operationof aircraft notequippedwithoperatingbackup (orstandby)attitude, altimeter, and airspeedindicators thatarelocatedwhere theyarereadilyvisibletothepilotisprohibited. Pilotsmust frequently scanand cross-checkflight instrumentstomake suretheinformation depictedon thePFD correlates and agreeswiththeinformationdepictedon thebackup instruments. IssuedinKansasCity,Missouri,on April4,2008. David R. Showers, ActingManager,SmallAirplaneDirectorate, Aircraft Certification Service. [FR Doc. E8-7802 Filed4-11-08;8:45am] Page: 2-11-(1) Issued: APRIL 4, 2008 HB-2008-135R1 SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page No. No. 3.1 General 3-1 3.3 Airspeeds For Safe Operation 3-2 3.5 Emergency Procedures Checklist 3-3 3.5a Engine FireDuring Start(3.9) 3-3 3.5b Engine Power Loss During Takeoff (3.11) 3-3 3.5c Engine Power Loss In Flight(3.13) 3-3 3.Sd Power Off Landing (3.15) 3-4 Gear Down Emergency Landing (3.15a) 3-4 Gear Up Emergency Landing (3.15b) 3-5 3.5e FireIn Flight(3.17) 3-5 3.5f Loss Of OilPressure(3.19) 3-6 3.5g Loss Of Fuel FlowlPressure(3.21) 3-6 3.5h High OilTemperature (3.23) 3-6 3.5i Electrical Failure(3.25) 3-6 3.5j Electrical Overload (3.27) 3-6 3.5k PropellerOverspeed (3,29) 3-7 3.5m Emergency Landing Gear Extension (3.31) 3-8 3.5n Spin Recovery (3.33) 3-9 3.5o Open Door (3.35) 3.5p Engine Roughness (3.37) 3-9 ISSUED: JULY 12, 1995 REPORT: VB-1612 2: Page: 3-0-(1) Issued: JULY 12, 1995 3-i SECTION 3 EMERGENCY PROCEDURES PA-28R-201, ARROW TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES (cont) Paragraph Page No No. 3.7 Amplified Emergency Procedures(General) 3-11 3.9 Engine FireDuring Start(3.5a) 3-11 3.11 Engine Power Loss During Takeoff(3.5b) 3-11 3.13 Engine Power Loss In Flight(3.5c) 3-12 3.15 PowerOffLanding(3.5d) 3-13 3.lSa Gear Down Emergency Landing (3.5d) 3-14 3.lSb Gear Up Emergency Landing (3.5d) 3-14 3.17 FirelnFlight(3.Se) 3-15 3.19 Loss of Oil Pressure(3.50 3-15 3.21 Loss ofFuel FIow!Pressure(3.5g) 3-16 3.23 High Oil Temperature (3.5h) 3-16 3.25 Electrical Failure(3.5i) 3q16 3.27 Electrical Overload (3.5j) 3-17 3.29 PropullerOverspeed (3.5k) 3-18 3.31 Emergency Lauding Gear Extension(3.5m) 3-18 3.33 Spin Recovery(3.5n) 3-19 3.35 Open Door (3.So) ‘3-19 3.37 Engine Roughness (3.5p) 3-19 REPORT: VB-1612 ISSUED: JULY 12,1995 3-il Page: 3-0-(2) Issued: JULY 12, 1995 3-ii SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES 3.1 GENERAL This section provides the recommended procedures for coping with vanous emergency or criticalsituations.All of the emergency procedures requiredby the FAA as well as those necessaryfor operationof the airplane, as determined by the operating and design features of the airplane,are presented. Emergency procedures associatedwith optionalsystems and equipment which require handbook supplements are presented in Section 9, Supplements. This sectionis divided into two basic parts.The firstpart containsthe emergency procedures checklists.These checklistssupply an immediate actionsequence to be followed during criticalsituationswith little emphasis on the operationof systems. The numbers located in parenthesesaftereach checklist heading indicate where the corresponding paragraph in the amplifiedprocedures can be found. The second part of the section provides amplified emergency procedures corresponding to the emergency procedures checklistitems. These amplified emergency procedures contain additionalinformation to provide thepilotwith a more complete descriptionof the procedures so they may be more easilyunderstood. The numbers located in parentheses after each paragraph heading indicatesthe corresponding checklistparagraph. Pilotsmust familiarizethemselves with the procedures given in this section and must be prepared to take the appropriate action should an emergency situationarise.The procedures are offered as a course of action forcoping with the particularsituationor condition described.They are not a substitutefor sound judgment and common sense. Most basic emergency procedures are a normal part of pilottraining. The information presented in this section is not intended to replace this training.This information is intended to provide a source of referencefor the procedures which are applicableto thisairplane.The pilotshould review standardemergency proceduresperiodicallytoremain proficientinthem. ISSUED: JULY 12, 1995 REPORT: YB-1612 1.1 Page: 3-1-(0) Issued: JULY 12, 1995 3-1 SECTION 3 EMERGENCY PROCEDURES PA-28R.201, ARROW 3.3 AIRSPEEDS FOR SAFE OPERATION 3.3a STALL SPEEDS 2750 lbs(Gear Up, 0 Flap) 60 KIAS 2750 lbs(Gear Down, 40 Flap) 55 KIAS 3.3b MANEUVERING SPEEDS 27501bs 118 KIAS 1865 lbs 96KIAS 3.3c NEVER EXCEED SPEED Never Exceed Speed 183 KIAS 3.3c1POWER OFF GLIDE SPEED 2750 lbs(Gear Up, 0 Flap) 79 KIAS /Th REPORT: VB-1612 ISSUED: JULY 12,1995 3-2 Page: 3-2-(0) Issued: JULY 12, 1995 3-2 SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES 3.5 EMERGENCY PROCEDURES CHECKLIST 3.5a ENGINE FIRE DURING START (3.9) Starter CRANK ENGINE Mixture IDLE CUT-OFF Throttle OPEN ElectricFuel Pump OFF Fuel Selector OFF Abandon iffirecontinues. 3.5b ENGINE POWER LOSS DURING TAKEOFF (3.11) If sufficient runway remains for a normal landing,leavegear down and land straightahead. Ifareaahead isrough or ifitisnecessaryto clearobstructions: Gear SelectorSwitch UP Ifsufficient altitudehas been gained toattempta restart: Maintain safeairspeed. Fuel Selector SWITCH totank containingfuel ElectricFuel Pump CHECK ON Mixture CHECK RICH AlternateAir OPEN Ifpower isnotregained,proceed with power offlanding(3.5d). 3.5c ENGINE POWER LOSS IN FLIGHT (3.13) Ifat low altitude: Airspeed MAINTAIN 79 KIAS minimum Prepareforpower offlanding(3.5d). Ifaltitudepermits: Fuel Selector SWITCH totank containingfuel ISSUED: JULY 12,1995 REPORP. VB-1612 REVISED: MARCH 10,2004 3-3 Page: 3-3-(0) Revision: 10, MARCH 10, 2004 3-3 SECTION 3 EMERGENCY PROCEDURES PA-28R-201, ARROW 3.5c ENGINE POWER LOSS IN FLIGHT (3.13)(continued) Electricfuelpump ON Mixture RICH AlternateAir OPEN Engine Gauges CHECK forindication of cause of power loss Ifno fuelflow/pressureisindicated,check tank selectorpositiontobe sureitison a tankcontainingfuel. When power isrestored: AlternateAir CLOSE ElectricFuel Pump OFF Ifpower isnot restored,prepareforpower offlanding. Trim for79 KIAS. 3.5d POWER OFF LANDING (3.15) Trim for79 KIAS. Locate suitablefield. Establishspiralpattern. 1000 ft.above field at downwind position for normal landing approach. When fieldcan be easilyreached,slow to72 KIAS forshortestlanding. Gear Down Emergency Landing (3.15a) Touchdowns should normally be made atthe lowestpossibleairspeed with fullflaps. When committed tolanding: Landing Gear Selector DOWN Flaps AS DESIRED Throttle CLOSE Mixture IDLE CUT-OFF Ignition OFF BATI’ MASTR Switch OFF ALTR Switch OFF Fuel Selector OFF SeatBeltsand Harness TIGHT NOTE Ifbatterymaster switch isOFF, the landinggear cannot be retracted. REPORT: VB-1612 ISSUED: JULY 12, 1995 3.4 Page: 3-4-(0) Issued: JULY 12, 1995 3-4 SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES 3.5d POWER OFF LANDING (3.15)(continued) Gear Up Emergency Landing (3.15b) In theeventa gear up landingisrequired,proceed as follows: Flaps AS DESIRED Throttle CLOSE Mixture IDLE CUT-OFF Ignition OFF BATT MASTR Switch OFF ALTR Switch OFF Fuel Selector OFF SeatBeltand Harness TIGHT Contactsurfaceatminimum possibleairspeed. 3.5e FIRE IN FLIGHT (3.17) Source of Fire CHECK ElectricalFire (Smoke in Cabin): BATT MASTR Switch OFF ALTR Switch OFF Vents OPEN Cabin Heat OFF Land as soon aspossible. Engine Fire: Fuel Selector OFF Throttle CLOSED Mixture IDLE CUT-OFF ElectricFuel Pump CHECK OFF Heater and Defroster OFF Proceed with power offlandingprocedure (3.5d). NOTE The possibilityof an engine firein flightis extremely remote. The procedure given is general and pilot judgement should be the determining factor for action in such an emergency. ISSUED: JULY 12,1995 REPORT: VB-1612 REVISED: MARCH 10,2004 3-5 Page: 3-5-(0) Revision: 10, MARCH 10, 2004 3-5 SECTION 3 EMERGENCY PROCEDURES PA-28R-201, ARROW 3.5f LOSS OF OIL PRESSURE (3.19) Land as soon as possibleand investigate cause. Prepareforpower offlanding. 3.5g LOSS OF FUEL FLOW/PRESSURE (3.21) ElectricFuel Pump ON Fuel Selector CHECK on tank containingfuel 3.5h HIGH OIL TEMPERATURE (3.23) Land atnearestairportand investigate theproblem. Prepareforpower offlanding. 3.51 ELECTRICAL FAILURE (3.25) ALT annunciatorlightilluminated: Ammeter CHECK toVERIFY mop, alt. Ifammeter shows zero: ALTR Switch OFF Reduce electrical loadsto minimum: ALTNTR. FIELD CircuitBreaker CHECK and RESET as required ALTR Switch ON Ifpower not restored: ALTR Switch OFF If alternatoroutput cannot be restored,reduce electricalloads and land as soon as practical.The batteryisthe only remaining source of electrical power. 3.5j ELECTRICAL OVERLOAD (Alternatorover 20 amps above known electrical load) (3.27) BATT MASTR Switch OFF REPORT: VB-1612 ISSUED: JULY 12,1995 3-6 Page: 3-6-(0) Issued: JULY 12, 1995 3-6 SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES 3.Sj ELECTRICAL OVERLOAD (Alternator over 20 amps above knoi electricalload) (3.27)(Continued) Ifammeter reading does NOT decrease: LTh Switch Land as soon as possible.Use Emergency Landing Gear Extension (3.5m) to lower landinggear. Ifammeter reading DOES decrease: BAIT MASTR Switch ON Ammeter MONITOR Ifammeter reading does NOT begin to decrease within fiveminutes: BATI’ MASTR Switch OFF Land as soon as possible. CAUTION If the batteryis depleted,the landing gear must be lowered using the emergency extension procedure. The gear position lights will be inoperative. NOTE Due to increased system voltage and radio frequency noise,operation with ALTR switch ON and BATT switch OFF should be made only when required by an electricalsystem failure. Ifammeter reading DOES begin to decrease withinfiveminutes: Proceed with flight. Ammeter MONITOR 3.5k PROPELLER OVERSPEED (3.29) Throttie RETARD Oil Pressure CHECK ISSUED: JULY 12,1995 REPORT: VB4612 Page: 3-7-(0) Issued: JULY 12, 1995 3-7 SECTION 3 EMERGENCY PROCEDURES PA-28R-201, ARROW 3.5k PROPELLER OVERSPEED (continued) PropellerControl FULL DECREASE rpm, thensetifany controlavailable. Airspeed REDUCE Throttle AS REQUIRED to remain below 2700 rpm 3.Sm EMERGENCY LANDING GEAR EXTENSION (3.31) NOTE Refer to paragraph 4.39 for differenceswhen emergency gear extensionisbeing performed for trainingpurposes. Priortoemergency extensionprocedure: BATI MASTR Switch CHECK ON ALTR Switch CHECK ON CircuitBreakers NAV LIGHT Switch OFF (indaytime) Gear IndicatorBulbs CHECK Iflandinggeardoes not check down and locked: REDUCE BELOW 87 KIAS Landing Gear SelectorSwitch GEAR DOWN POSiTION If gear has stillfailedto lock down, move and hold the emergency leverdown totheEmergency Down position. Ifgear has stillfailedto lock down, yaw the airplaneabruptlyfrom sideto sidewiththerudder. Ifthe nose gear willnot lock down using the above procedure,slow theaircrafttothe lowestsafespeed attainableusingthe lowestpower settingrequiredforsafeoperationand accomplish thefollowing: Landing Gear SelectorSwitch GEAR DOWN POSITION Iflandinggeardoes not check down, recyclegearthroughup position and then selectgearDOWN. REPORT: VB-1612 JSSUED JULY 12,1995 3-8 Page: 3-8-(0) Issued: JULY 12, 1995 3-8 SECTION 3 PA-28R-2o1, ARROW EMERGENCY PROCEDURES 3.5n SPIN RECOVERY (3.33) Rudder FULL OPPOSITE to DIRECTION ofROTATION ControlWheel FULL FORWARD WHILE NEUTRALIZING AILERONS Throttle Rudder NEUTRAL (when rotationstops) ControlWheel AS REQUIRED to SMOOTHJX REGAiN LEVEL FLIGHT ATrITUD 3.So OPEN DOOR (3.35) Ifboth upper and sidelatchesare open, the door willtrailslightlyopen and airspeedswillbe reduced slightly. To closethedoor inflight: Slow airplaneto87 KIAS. Cabin Vents CLOSE Storm Window OPEN Ifupper latchisopen LATCH Ifsidelatchisopen PULL on ARMREST while moving Latch Handle to LATCH position If both latches are open LATCH SIDE LATCH thenTOP LATCH 3.Sp ENGINE ROUGHNESS (3.37) Mixture ADJUST formaximum smoothness AlternateAir OPEN ElectricFuel Pump ON Fuel Selector SWITCH TANKS Engine Gauges CHECK Magneto Switch .L then R then BOTh If operation is satisfactory on either magneto, proceed on that magneto at reduced power, with fullRICH mixture,to a landing atthe firstavailableairport. Ifroughness persists, preparefora precautionarylanding. ISSUED: JULY 12,1995 REPORT: VB-1612 2-a Page: 3-9-(0) Issued: JULY 12, 1995 3-9 SECTION 3 EMERGENCY PROCEDURES PA-28R-201, ARROW I THIS PAGE INTENTIONALLY LEFT BLANK C REPORT: VB-1612 ISSUED: JULY 12,1995 3-10 Page: 3-10-(0) Issued: JULY 12, 1995 3-10 SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES 3.7 AMPLIFIED EMERGENCY PROCEDURES (GENERAL) The following paragraphs are presented to supply additional information for the purpose of providing the pilotwith a more complete understanding of the recommended course of actionand probable cause of an emergency situation. 3.9 ENGINE FIRE DURING START (3.5a) Engine firesduring startare usuallythe resultof overpriming.The first attemptto extinguishthe fireisto tryto startthe engine and draw the excess fuelback intothe inductionsystem. If a fireis present before the engine has started,move the mixture control to idle cut-off,open the throttleand crank the engine. This isan attempttodraw thefireback intotheengine. Iftheengine has started,continueoperatingto tryto pullthe fireintothe engine. In eitherof theabove cases,iffirecontinuesformore than a few seconds, the fireshouldbe extinguishedby thebestavailableexternalmeans. The fuelselectorvalves should be OFF and the mixture atidlecut-offif an externalfireextinguishingmethod isto be used. 3.11 ENGINE POWER LOSS DURING TAKEOFF (3.5b) The proper actionto be taken iflossof power occurs during takeoffwill depend on thecircumstancesof theparticularsituation. If sufficientrunway remains to complete a normal landing, leave the landinggeardown and land straightahead. Ifthearea ahead isrough, or ifitisnecessaryto clearobstructions, move thegear selectorswitchto theUP position. Ifsufficientaltitudehas been gained to attempt a restart, maintain a safe airspeed and switch the fuel selectorto a tank containing fuel.Place the electricfuelpump to ON. Check thatthe mixture is RICH. The alternateair shouldbe open. ISSUED: JULY 12,1995 REPORT: VB-1612 3-Il Page: 3-11-(0) Issued: JULY 12, 1995 3-11 SECTION 3 EMERGENCY PROCEDURES PA-28R-201, ARROW 3.li ENGINE POWER LOSS DURING TAKEOff (35b) (continued) If engine failurewas caused by fuel exhaustion power will not be regainedafterswitchingfueltanks untilthe empty fuellinesare filled. This may requireup toten seconds. Ifpower isnot regained,proceed with the Power Off Landing procedure (referto theemergency checklistand paragraph 3.15). 3.13 ENGINE POWER LOSS IN FLIGHT (3.Sc) Complete engine power lossis usuallycaused by fuelflow intemiption and power willbe restoredshortlyafterfuel flow isrestored.Ifpower loss occurs at a low altitude, the firststepisto prepare foran emergency landing (referto paragraph 3.15). An airspeed of at least79 KIAS should be maintained. Ifaltitudepermits,switch.the fuelselectorto another tank containing fuel and turn the electricfuel pump to ON. Move the mixture control to RICH and the alternateair to OPEN. Check the engine gauges for an indication of the cause of the power loss. If no fuel flow/pressure is indicated check the tank selector position to be sure it is on a tank containingfuel. When power isrestoredmove the alternateairto the CLOSED position and turnOFF theelectricfuelpump. Ifthe preceding stepsdo not restorepower, prcpare for an emergency landing. Iftime permits, turn the ignitionswitch to L, then to R, then back to BOTH. Move the throttleand mixture controlleversto differentsettings. This may restorepower iftheproblem istoo richor too lean a mixture or if thereisa partialfuelsystem restriction, Try the otherfueltank.Water in the fuelcould takesome time tobe used up, and allowing the engineto windmill may restore power. If power loss is due to water, fuel flow/pressure indicationswillbe normal. REPORT: VB-1612 ISSUED: JULY 12,1995 3.12 Page: 3-12-(0) Issued: JULY 12, 1995 3-12 SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES 3.13 ENGINE POWER LOSSIN FlIGHT (3.Sc)(continued) If engine failurewas caused by fuel exhaustion power will not be restoredafterswitching fueltanks untilthe empty fuellinesare filled.This may requireup to tenseconds. Ifpower isnot regained,proceed with the Power Off Landing procedure (referto emergency checklistand paragraph 3.15).Trim for79 KIAS. 3.15 POWER OYF LANDING (3.5d) Iflossof power occurs ataltitude, trim the aircraftforbestglidingangle (79 KIAS, airconditioneroff)and look for a suitablefield,TImeasures taken to restorepower are not effective, and iftime permits,check your chartsfor airportsin the immediate vicinity;itmay be possible to land at one ifyou have sufficientaltitude.At best glidingangle,with the engine windrailling, and the propeller control in fullDECREASE rpm, the aircraftwill travel approximately 1.6 miles for each thousand feetof altitude. Ifpossible,notif’ the FAA by radio of your difficultyand intentions.If another pilot or passenger isaboard,lethim help. When you have locateda suitablefield,establisha spiralpatternaround thisfield.Try to be at 1000 feetabove the fieldat the downwind position,to make a normal landing approach.When the fieldcan easilybe reached,slow to 72 KIAS with flapsdown for the shortestlanding.Excess altitudemay be lostby widening your pattern,using flapsor slipping,or a combination of these. Whether to attempt a landing with gear up or down depends on many factors.Ifthe fieldchosen isobviously smooth and firm,and long enough to bring the plane to a stop,the gear should be down. If there are stumps or rocks or other largeobstaclesin the field,the gear in the down positionwill betterprotectthe occupants of the aircraft. If,however, the fieldissuspected to be excessively soft or short,.or when landing in water of any depth, a wheels-up landingwillnormally be saferand do lessdamage totheairplane. Touchdown shouldnormally be made atthelowest possibleairspeed. ISSUED: JULY 12,1995 REPORT: VB-1612 3.13 Page: 3-13-(0) Issued: JULY 12, 1995 3-13 SICELON 3 EMERGENCY PROCEDURES PA-28R-201, ARROW 3.15 POWER OFF LANDING (3Sd) (continued) 3.lSa Gear Down Emergency Landing (3.Sd) When committed to a gear down emergency landing,selectlandinggear DOWN. Flaps may be used as desired.Close the throttle controland move the mixture controlto idlecut-off.Shut OFF the ignition,batterymaster (BATe MASTR), and alternator(ALTR) switches.Turn thefuelselectorvalveto OFE The seatbeltsand shoulder harnessshould he tightened.Touchdown should normally be made atthelowestpossibleairspeed. NOTE If the batterymaster switch is OFF, the landing gearcannot be retracted. 3.lSb Gear Up Emergency Landing (3.Sd) When committed to a gear up landing, CLOSE the throttle, move the mixture to idle cut-off,and shut OFF the ignitionsbatterymaster (BATT MASTR), and alternator(ALTR) switches.Turn OFF the.fuelselectorvalve. Seat belts and shoulder harness should be tightened.Touchdown should normally be made atthelowestpossibleairspeedwith fullflaps. 0 REPORT: VB-1612 ISSUED: JULY 12,1995 3-14 Page: 3-14-(0) Issued: JULY 12, 1995 3-14 SECTION 3 PA-28R.201, ARROW EMERGENCY PROCEDURES 3.17 FERE IN FIJGRT (3.5e) The presence of fireisnoted through smoke, smell and heat in the cabin. It is essentialthat the source of the firebe promptly identifiedthrough instrument readings1characterof the smoke, or other indicationssince the actiontobe takendifferssomewhat ineach case. Check forthesourceof the firefirst. If smoke in the cabin indicatesan electrical fire,turn the batterymaster (BATe MASTR) and alternator(ALTR) switches OFF. The cabin vents should be opened and the cabin heat turned OFF. A landing should be made as soon aspossible. Ifan engine fireispresent,switch the fuelselectorto OFF and closethe throttle. The mixture should be at idlecut-off.Turn the electricfuelpump OFF. In all cases, the heater and defroster should be OFF. If radio communication is not required selectthe batterymaster (BATT MASTR) and alternator(ALTR) switches OFF. If the terrainpermits, a landing should be made immediately. NOTh The possibilityof an engine firein flightis extremelyremote. The procedure given is general and pilot judgment should be the determining factor for action in such an emergency. 3.19 LOSS OF OIL PRESSURE (3.Sf) Loss of oilpressuremay be eitherpartialor complete. A partiallossof oilpressure usually indicatesa malfunction in the oilpressure regulating system, and a landing should be made as soon as possibleto investigatethe cause and preventengine damage. A complete loss of oilpressureindicationmay signifyoilexhaustionor may be the resultof a faultygauge. In eithercase,proceed toward the nearest airport,and be prepared for a forced landing.Ifthe problem is not a pressure gauge malfunction, the engine may stop suddenly. Maintain altitudeuntil such time as a dead sticklanding can be acccnnplished.Don’t change power settingsunnecessarily, as thismay hastencomplete power loss. ISSUED: JULY 12, 1995 REPORT: VB-1612 3-15 Page: 3-15-(0) Issued: JULY 12, 1995 3-15 SECTION 3 EMERGENCY PROCEDURES PA-28R.201, ARROW 3.19 LOSS OF OIL PRESSURE (3.Sf)(continued) Depending on the circumstances, itmay be advisable to make an off airportlanding while power isstillavailable,particularly ifother indications of actualoilpressureloss,such as sudden increasesin temperatures,or oil smoke, areapparent,and an airportisnot close. Ifengine stoppageoccurs,proceed with Power Off Landing. 3.21 LOSS OF FUEL FLOW/PRESSURE (3.Sg) The most probable cause of loss of fuel flow/pressure is eitherfuel depletionin the fueltank selected,or failureof the engine driven fuelpump. If loss,of fuelflow/pressureoccurs,check thatthe fuelselectoris on a tank containingfueland turnON the electricfuelpump. Ifthe problem isnot an empty tank,land as soon as practicaland have the engine drivenfuelpump and fuelsystem checked. 3.23 HIGH OIL TEMPERATURE. (3.5h) An abnormally high oiltemperature indicationmay be caused by a low oillevel,an obstructionin the oilcooler,damaged or improper baffleseals,a defectivegauge, or othercauses.Land as soon as practicalat an appropriate airportand have thecause investigated. A steady,rapid risein oiltemperature is a sign of trouble.Land at the nearest airportand leta mechanic investigatethe problem. Watch the oil pressuregauge foran accompanying lossof pressure. 3.25 ELECTRICAL FAILURE (3.51) Loss of alternatoroutput is detected through zero reading on the ammeter. Before executing the following procedure,ensure thatthe reading iszero,and not merely low,by actuatingan electrically powered device,such as the landinglight.Ifno increasein the ammeter readingisnoted, alternator failurecan be assumed. The electrical load should be reduced as much as possible.Check for an open alternatorfieldcircuitbreaker. Next, attempt toresetthe overvoltagerelayby moving the ALTR switch to OFF for one second and then to ON. If the trouble was caused by a momentary overvoltagecondition(16.5 voltsand up) thisprocedure should returnthe ammeter to a normal reading. REPORT: VB-1612 ISSUED: JULY 12, 1995 3-16 Page: 3-16-(0) Issued: JULY 12, 1995 3-16 SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES 3.25 ELECTRICAL FAILURE (3.51)(continued) If the ammeter continues.to.indicate ZERO output,or if the alternator will not remain reset, turn off the ALTR switch, maintain minimum electricalload and land as soon as practical.All electricalload is being suppliedby the battery. 3.27 ELECTRICAL OVERLOAD (Alternatorover 20 amps above known electricalload)(3.5j) An abnormally high alternatoroutput may be caused by a low battery, batteryfault,or otherabnormal electrical load. Should an abnormally high alternatoroutput be observed, turn the BATT MASTR (batterymaster) switch OFF. If the ammeter reading does NOT decrease,turn the ALTR (alternator) switch OFF and land as soon as possible.The landing gear must be lowered using the Emergency Landing Gear Extension procedure (3.33). If,afterturning the BAT1’ MASTR switch OFF, the ammeter reading DOES decrease, turn the BATT MASTR switch ON, and continue to monitor the ammeter. If the ammeter reading does not begin to decrease within five minutes, turn the BATE MASTR switch OFF and land as soon aspossible. CAUTION Ifthe batteryisdepleted,the landing gear must be lowered using the emergency extension procedure. The gear position lights will be inoperative. NOTE Due to increased system voltage and radio frequency noise, operation with ALTR switch ON and BAY MASTR switch OFF should be made only when required by an electrical system failure. If the ammeter reading DOES begin to decrease within five minutes afterthe BATT MASTR switch is turned ON, proceed with flightwhile continuingto monitor ammeter. ISSUED: JULY 12,1995 REPORT: VB-1612 1.1’? Page: 3-17-(0) Issued: JULY 12, 1995 3-17 SECTION 3 EMERGENCY PROCEDURES PA.28R-201, ARROW 3.29 PROPELLER OVERSPEED (3.5k) Propelleroverspeed iscaused by a malfunctionin thepropellergovernor or low oilpressurewhich allowsthepropellerbladestorotatetofulllow pitch. Ifpropelleroverspeed should occur,retardthe throttle and check the oil pressure.The propellercontrolshould be moved to fullDECREASE rpm and then setifany controlis available.Airspeed should he reduced and throttle used tomaintain2700 rpm. 3.31 EMERGENCY LANDING GEAR EXTENSION (3.Sm) NOTE Refer to paragraph 4.39 for differenceswhen emergency gearextensionisbeing performed for trainingpurposes. Priortoinitiating theemergency extensionprocedure,check toensure that. the batterymaster (BATe MASTR) and alternator(ALTR) switchesare ON, and thatthe circuitbreakershave not opened. If itis in daytime, the NAV LIGHT switch should be turnedOFF Check the lanchnggear indicatorsfor faultybulbs. If the landinggear does not check down and locked,reduce the airspeed below 87 KIAS. Move thelandinggear selectorswitchto theDOWN position. Ifthegear has still failedto lockdown, move and hold theemergency gear leverdown totheEMERGENCY DOWN position. Ifthe gear has stillfailedto lock down, yaw the airplaneabruptlyfrom sidetosidewith theruddet Ifthe nose gear willnot lock down using the above procedure,slow the airplaneto the lowest safe speed attainableusing the lçwest power setting requiredfor safeoperation.Move the landinggear selectorswitch to the gear DOWN position.If thelanding gear does not check down, recycle the gear throughtheUP positionand thenselecttheDOWN position. REPORT: VB-1612 ISSUED: JULY 12,1995 3-18 Page: 3-18-(0) Issued: JULY 12, 1995 3-18 SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDU1ES 3.33 SPIN RECOVERY (3.5n) Intentionalspinsare prohibitedin thisairplane.If a spin isinadvertently entered,immediately apply fullrudder oppositeto the directionof rotation. Move the controlwheel fullforward while neutralizingthe ailerons.Move the throttleto IDLE. When the rotationstops,neutralizethe rudder and ease back on the control wheel as required to smoothly regain a level flight attitude. 3.35 OPEN DOOR (3.So) The cabin door isdouble latched,so the chances of itsspringingopen in flightat both the top and bottom are remote. However, should the upper latchbe overlooked or the side latchnot fullyengaged, the door may spring partiallyopen. This will usually happen at takeoff or soon afterward.A partiallyopen door willnot affectnormal flightcharacteristics, and a normal landingcan be made with the door open. Ifboth upper and side latchesare open, the door willtrailslightlyopen, and airspeedwillbe reduced slightly. To closethe door in ffight,slow the airplaneto 87 KIAS, close the cabin vents and open the storm window. Ifthe top latchisopen, latchit.Ifthe side latch is open, pull on the armrest while moving the latch handle to the latchedposition.If both latchesare open, close the side latchfirst,and then the top latch. 3.37 ENGINE ROUGHNESS (3.5p) Engine roughness may be caused by dirt in the injector nozzles, inductionsystem icing,or ignitionproblems. Firstadjust the mixture for maximum smoothness. The engine willrun rough ifthe mixture istoo richor too lean. Move the alternateairto OPEN and then turnON the electricfuelpump Switch the fuelselectorto anothertank to see iffuelcontamination isthe problem. Check the engine gauges for abnormal readings.If any gauge readings areabnormal proceed accordingly. ISSUED: JULY 12,1995 REPORT: VB-1612 Page: 3-19-(0) Issued: JULY 12, 1995 3-19 SECTION 3 EMERGENCY PROCEDURES PA-28R-201, ARROW 3.37 ENGINE ROUGHNESS (3.5p)(Continued The magneto switch should then be moved L, then R, then back to BOTH. If operation is satisfactoryon either magneto, proceed on that magneto at reduced power with fullRICH mixture to a landing at the first availableairport. If roughness persists,prepare for a precautionary landing at pilot’s discretion. Fm 3 0 REPORT: VB-1612 ISSUED: JULY 12,1995 Page: 3-20-(0) Issued: JULY 12, 1995 3-20 SECTION 9 PA-28R-201, ARROW SUPPLEMENTS TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph Page No. No. 4.1 General 4-1 4.3 Airspeeds forSafe Operations 4-2 4.5 Normal Procedures Checklist 4-3 4.5a PreflightChecklist(4.9) 4-3 4.5b Before StartingEngine Checklist(4.11) 4-6 4.5c Engine StartChecklist(4.13) 4-7 ENGINE START GENERAL 4-7 NORMAL START COLD ENGINE (4.13a) 4-7 NORMAL START HOT ENGINE (4.13b) 4-8 ENGINE START WHEN FLOODED (4.13c) 4-8 ENGINE START WITH EXTERNAL POWER SOURCE (4.13d) 4-8 4.5d Warm-Up Checklist(4.15) 4-9 4.5e Taxiing Checklist(4.17) 4-9 4.5f Ground Check Checklist(4.19) 4-9 4.5g Before Takeoff Checklist(4.21) 4-10 4.5h Takeoff Checklist(4.23) 4-11 NORMAL TECHNIQUE (4.23b) 4-11 ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12,2010 4-i Page: 4-0-(1) Revision: 22, MAY 12, 2010 4-i SECTION 9 PA-28R-201, ARROW SUPPLEMENTS TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES (cont) Paragraph Page No. No. 4 5h Takeoff Checklist(4 23) (continued SHORT FIELD, OBSTACLE CLEARANCE TECHNIQUE (4.23b) 4-11 SOFT FIELD TECHNIQUE (4.23b) 4-11 4.5i Climb Checklist(4.25) 4-12 4.5j Cruise Checklist(4.27) 4-12 4.5k Aproach And Landing Checklist(4.29) 4-12 4.5m Stopping Engine Checklist(4.31) 4-13 4.5n Mooring Checklist(4.33) 4-13 4.7 AMPLIFIED PROCEDURES 4-15 4.9 PREFLIGHT CHECK (4.5a) 4-15 4.9a Cockpit (4.5a) 4-15 4.9b Right Wing (4.5a) 4-15 4.9c Nose Section(4.5a) 4-16 4.9d Left Wing (4.5a) 4-17 4.9e Fuselage (4.5a) 4-17 4.10 ENGINE START GENERAL (4.5c) 4-18 4.11 BEFORE STARTING ENGINE (4.5b) 4-18a 4.13 ENGINE START (4.5c) 4-18a ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12, 2010 4-il Page: 4-0-(2) Revision: 22, MAY 12, 2010 4-ii SECTION 9 PA-28R-201, ARROW SUPPLEMENTS TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES (cont) Paragraph Page No. No. 4.13a Normal Start Cold Engine (4.5c) 4-18a 4.13b Normal Start Hot Engine (4.5c) 4-19 4.13c Engine StartWhen Flooded (4.5c) 4-19 4.13d Engine StartWith ExternalPower Source (4.5c) 4-19 4.15 WARM-UP (4.5d) 4-20 4.17 TAXIING (4.5e) 4-20 4.19 GROUND CHECK (4.5f) 4-21 4.21 BEFORE TAKEOFF (4.5g) 4-22 4.23 TAKEOFF (4.5h) 4-22 4.23a Normal Technique (4.5h) 4-22 4.23b Short Field,ObstacleClearance And Soft FieldTechniques (4.5h) 4-22 4.25 CLIMB (4.5i) 4-23 4.27 CRUISE(4.5j) 4-23 4.29 APPROACH AND LANDING (4.5k) 4-25 4.31 STOPPING ENGINE (4.Sm) 4-25 4.33 MOORING (4.5n) 4-26 4.37 STALLS 4-26 4.37 TURBULENT AIR OPERATION 4-27 ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12,2010 4-ill Page: 4-0-(3) Revision: 22, MAY 12, 2010 4-iii SECTION 9 PA-28R-201, ARROW SUPPLEMENTS TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES (cont) Paragraph Page No No. 4.39 LANDING GEAR 4-27 4.41 WEIGHT AND BALANCE 4-28 4.43 NOISE LEVEL 4-28 U ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12,2010 4-iv Page: 4-0-(4) Revision: 22, MAY 12, 2010 4-iv SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES 4.1 GENERAL This sectionprovides the normal operating procedures for the PA-28R- 201, Arrow airplane.All of the normal operatingprocedures requiredby the FAA, as well as those procedures which have been determined as necessary for the operation of the airplane, as determined by the operating and designed featuresof the airplane,arepresented. Normal operating procedures associated with optional systems and equipment which requirehandbook supplements are presented in Section9, Supplements. These procedures are provided to supply information on procedures which are not the same for allairplanesand as a source of reference and review. Pilots should familiarizethemselves with these procedures to become proficientinthe normal operationof the airplane. This section is divided into two parts.The firstpart is a short form checklistsupplying an action reaction sequence for normal procedures with little emphasis on the operationof the systems.Numbers in parentheses aftereach checklistsectionindicatethe paragraph where the conesponding amplifiedprocedure can be found. The second part of this section contains the amplified normal procedures which provide detailedinformation and explanations of the procedures and how to perform them. This portion of the section is not intended foruse as an inflightreferencedue to the lengthlyexplanation.The shortform checklistsshould be used on the ground and in ifight.Numbers in parentheses after each paragraph titleindicate where the corresponding checklistcan be found. ISSUED: JULY 12,1995 REPORT: VB-1612 Page: 4-1-(0) Issued: JULY 12, 1995 4-1 SECTION 4 NORMAL PROCEDURES PA-28R-201, ARROW 4.3 AIRSPEEDS FOR SAFE OPERATIONS The following airspeeds are those which are significantto the safe operationof the airplane.These figuresare for standard airplanesflown at grossweight under standardconditionsatsea level. Performance for a specificairplane may vary from published figures depending upon the equipment installed,the condition of the engine, airplaneand equipment, atmospheric conditionsand pilotingtechnique. (a) Best Rate ofClimb Speed gearup, flapsup 90 KIAS geardown, flapsup 78 ICLAS (1,)Best Angle of Climb Speed gearup, flapsup 78KIAS gear down, flapsup 72 KIAS Cc) TurbulentAir OperatingSpeed (See Subsection2.3) 118 KIAS (d) Maximum Flap Speed 103 KIAS Ce) Landing FinalApproach Speed (Flaps40°) 75 KIAS (f) Maximum Demonstrated Crosswind Velocity 17 KTS 0 REPORT: VB-1612 ISSUED: JULY 12,1995 Page: 4-2-(0) Issued: JULY 12, 1995 4-2 PA-28R-201, ARROW SECTION 4 NORMAL PROCEDURES WALK-AROUND Figure4-1 4.5 NORMAL PROCEDURES CHECKLIST 4.5a PreflightChecklist(4.9) CAUTION The flap position should be noted before boarding the airplane.The flapsmust be placed in the UP position before they will lock and supportweight on thestep. COCKPIT (4.9a) ControlWheel releaserestraints Gear Handle DOWN Parking Brake SET Avionics OFF All Switches OFF Mixture IDLE CUT-OFF Magneto Switch OFF BATE MASTR Switch ON ISSUED: JULY 12,1995 REPORT: VB-1612 4-3 Page: 4-3-(0) Issued: JULY 12, 1995 4-3 SECTION 4 NORMAL PROCEDURES PA-28R-201, ARROW 4.5a PreflightChecklist(4.9)(continued) COCKPIT (4.9a)(continued) Fuel Gauges check QUANTITY AnnunciatorPanel CHECK BATT MASTR Switch OFF Primary FlightControls PROPER OPERATION Flaps PROPER OPERATION Trim NEUTRAL Pitotand StaticSystems DRAIN Windows check CLEAN Required Papers and POH check ON BOARD Tow Bar and Baggage STOW PROPERLY SECURE Baggage Door CLOSE and SECURE RIGHT WING (4.9b) SurfaceCondition CLEAR of ICE, FROST, SNOW Flap and Hinges CHECK Aileronand Hinges CHECK StaticWicks CHECK SECURE Wing Tip and Lights CHECK Fuel Tank CHECK supply visually SECURE cap FuelTank Vent CLEAR CAUTION When drainingany amount of fuel,care should be taken to ensure that no firehazard exists beforestartingengine. Fuel Tank Sump DRAIN and CHECK forwater,sediment, and properfuel Tie Down and Chock REMOVE Main Gear Strut PROPER INFLATION (2.0+1-0.25 in.) Tire CHECK Brake Block and Disc CHECK FreshAir Inlet CLEAR REPORT: VB-1612 ISSUED: JULY 12,1995 4.4 REVISED: MARCH 10,2004 Page: 4-4-(0) Revision: 10, MARCH 10, 2004 4-4 SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES 4.5a PreflightChecklist(continued) NOSE SECTION (4.9c) General Condition CHECK Cowling SECURE Oil CHECK QUANTITY Dipstick PROPERLY SEATED OilFillerCap SECURE Engine BaffleSeals CHECK Windshield CLEAN Propellerand Spinner CHECK Air Inlets CLEAR AlternatorBelt CHECK TENSION Landing Light CHECK Chock REMOVE Nose Gear Strut PROPER INFLATION (2.75+1-0.25 in.) Nose Wheel Tire CHECK CAUTION When drainingany amount of fuel,care should be taken to ensure that no fire hazard exists beforestarting engine. Fuel Strainer DRAIN LEFT WING (4.9d) SurfaceCondition CLEAR ofICE,.FROST, SNOW StallWarning Vane CHECK Fuel Tank CHECK Supply visually SECURE CAP Fresh Air Inlet CLEAR Chock REMOVE Main Gear Strut PROPER INFLATION (2.0+1-0.25 in.)I Tire CHECK Brake Block and Disc CHECK Fuel Tank Vent CLEAR CAUTION When drainingany amount of fuel,care should be taken to ensure that no firehazard exists beforestartingengine. ISSUED: JULY 12,1995 REPORT: VB-1612 REVISED: MARCH 10,2004 4-5 Page: 4-5-(0) Revision: 10, MARCH 10, 2004 4-5 SECTION 4 NORMAL PROCEDURES PA-28R-201, ARROW 4.Sa PreflightChecklist(continued) LEFT WING (4.9d)(continued) Fuel Tank Sump DRAIN and CHECK forwater,sediment, and properfuel Tie Down REMOVE PitotMast REMOVE COVER HOLE CLEAR Wing Tip and Lights CHECK Aileron and Hinges CHECK Flap and Hinges CHECK StaticWicks CHECK SECURE FUSELAGE (4.9e) Antennas CHECK Left StaticVent CLEAR Fresh Air Inlet CLEAR Empennage CLEAR of ICE, FROST, SNOW Stabilatorand Trim Tab CHECK Tie Down REMOVE Right StaticVent CLEAR BATE MASTR Switch ON Cockpit Lighting CHECK Navigationand StrobeLights CHECK Landing Light CHECK StallWarning CHECK PitotHeat CHECK All Switches OFF BAIT MASTR Switch OFF Passengers BOARD Cabin Door CLOSE and SECURE SeatBeltsand Harness FASTEN CHECK inertiareel 4.5b Before StartingEngine Checklist(4.11) BEFORE STARTING ENGINE (4.11) Brakes SET CircuitBreakers IN AlternateAir OFF Propeller FULL INCREASE RPM Avionics OFF Fuel Selector DESIRED TANK REPORT: VB-1612 ISSUED: JULY 12, 1995 4-6 Page: 4-6-(0) Issued: JULY 12, 1995 4-6 SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES 4.5c Engine Start Checklist (4.13) ENGINE START GENERAL (4.13) CAUTION Do not attempt flightifthere is no indicationof primary alternatoroutput. CAUTION If a positive oil pressure is not indicated within 30 seconds following an engine start,stop the engine and determine the trouble.In cold weather itwilltake a few seconds longer to get a positiveoilpressureindication. NOTE Startermanufacturer recommends startercranking periods be limited to 10 seconds with a 20 second rest period between cranking attempts.Maximum of 6 startperiods allowed. If startis not achieved on sixth attempt allow starterto cool for 30 minutes before attemptingadditional starts. NORMAL START COLD ENGINE (4.13) Throttle 1/2 INCH OPEN ALTR Switch ON BATT MASTR Switch ON ElectricFuel Pump ON Mixture RICH thenIDLE CUT-OFF Propeller CLEAR Starter ENGAGE Mixture FULL RICH Throttle ADJUST Oil Pressure CHECK ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12, 2010 4-7 Page: 4-7-(0) Revision: 22, MAY 12, 2010 4-7 SECTION 4 NORMAL PROCEDURES PA-28R-201, ARROW 4.5c Engine Start Checklist (4.13)(continued) NORMAL START HOT ENGINE (4.13b) Throttle 1/2 INCH OPEN ALTR Switch ON BAIT MASTR Switch ON ElectricFuel Pump ON Mixture IDLE CUT-OFF Propeller CLEAR Starter ENGAGE Mixture ADVANCE Throttle ADJUST Oil Pressure CHECK ENGINE START WHEN FLOODED (4.13c) Throttle FULL OPEN ALTR Switch ON BATI’ MASTR Switch ON ElectricFuel Pump OFF Mixture IDLE CUT-OFF Propeller CLEAR Starter ENGAGE Mixture ADVANCE Throttle RETARD Oil Pressure CHECK ENGINE START WITH EXTERNAL POWER SOURCE (4.13d) BATT MASTR Switch OFF ALTR Switch OFF All ElectricalEquipment OFF Terminals CONNECT ExternalPower Plug INSERT in receptacle Proceed with normal start. Throttle LOWEST POSSIBLE RPM ExternalPower Plug REMOVE from receptacle BATE MASTR Switch ON ALTR Switch ON CHECK AMMETER Oil Pressure CHECK REPORT: VB-1612 ISSUED: JULY 12, 1995 4-8 REVISED: MAY 12, 2010 Page: 4-8-(0) Revision: 22, MAY 12, 2010 4-8 SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES 4.5c Engine Start Checklist (4.13)(continued) ENGINE START WITH EXTERNAL POWER SOURCE (4.13d) (continued) CAUTION Itis possibleto use the ship’sbatteryin parallel by turning only the batterymaster switch ON. This will give longer cranking capabilities, but will not increase the amperage. Care should be exercised because if the ship’sbatteryhas been depleted, the external power supply can be reduced to the level of the ship’s battery.This can be testedby turningonly the batterymaster switch ON momentarily while the starteris engaged. If cranking speed increases,the ship’s battery is at a higher level than the external power supply. NOTE For all normal operations using the PEP jumper cables, the battery master and alternatorswitches should be OFF. 4.5d Warm-Up Checklist (4.15) WARM-UP (4.15) Throttle 1400 to 1500 RPM 4.5e Taxiing Checklist (4.17) TAXIING (4.17) Taxi Area CLEAR Parking Brake RELEASE Propeller HIGH RPM Throttle APPLY SLOWLY Brakes CHECK Steering CHECK 4.5f Ground Check Checklist (4.19) GROUND CHECK (4.19) Parking Brake SET Propeller FULL INCREASE Throttle 2000 RPM ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12, 2010 4-9 Page: 4-9-(0) Revision: 22, MAY 12, 2010 4-9 SECTION 4 NORMAL PROCEDURES PA-28R-201, ARROW 4.5f Ground Check Checklist (4.19)(continued) GROUND CHECK (4.19)(continued) Magnetos CHECK max. drop 175 RPM -max.diff.50 RPM Vacuum 4.8 to 5.1 inchesHg Oil Temperature CHECK Oil Pressure CHECK Ammeter CHECK Annunciator Panel PRESS-TO-TEST Propeller EXERCISE then FULL INCREASE AlternateAir CHECK Engine is warm for takeoffwhen throttlecan be opened without engine faltering. ElectricFuel Pump OFF Fuel Pressure CHECK Throttle RETARD 4.5g Before Takeoff Checklist (4.21) BEFORE TAKEOFF (4.21) BATI’ MASTR Switch ON ALTR Switch ON FlightInstruments CHECK Fuel Selector PROPER TANK ElectricFuel Pump ON Engine Gauges CHECK AlternateAir CLOSED Seat Backs ERECT Mixture SET Propeller SET Belts/Harness FASTENED/CHECK Empty Seats SEAT BELTS SNUGLY FASTENED Flaps SET Trim SET Controls FREE Doors LATCHED Air Conditioner OFF REPORT: VB-1612 ISSUED: JULY 12, 1995 4-10 REVISED: MAY 12,2010 Page: 4-10-(0) Revision: 22, MAY 12, 2010 4-10 SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES 4.5h Takeoff Checklist (4.23) NORMAL TECHNIQUE (4.23a) Flaps SET Trim SET Accelerateto 65 to 75 KIAS. Control Wheel back pressureto ROTATE smoothly toCLIMB ATI’ITLJDE SHORT FIELD, OBSTACLE CLEARANCE TECHNIQUE (4.23b) Flaps 25° (second notch) Accelerateto 50 to 60 KIAS depending on aircraftweight. ControlWheel back pressureto ROTATE to CLIMB ATTITUDE Afterbreaking ground, accelerateto 55 to 65 KIAS depending on aircraftweight. Gear UP Accelerate to best gear up angle of climb speed 78 KIAS, slowly retractthe flapsand climb past theobstacle. Accelerateto best gear up rateof climb speed 90 KIAS. SOFT FIELD TECHNIQUE (4.23b) Flaps 25° (second notch) Accelerateto 50 to 60 KIAS depending on aircraftweight. Control Wheel hack pressureto ROTATE to CLIMB ATTiTUDE After breaking ground, accelerate to 55 to 65 KIAS depending on aircraftweight. Gear UP Accelerateto bestgear up rateof climb speed 90 KIAS. Flaps RETRACT SLOWLY ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12,2010 4-11 Page: 4-11-(0) Revision: 22, MAY 12, 2010 4-11 SECTION 4 NORMAL PROCEDURES PA-28R-201, ARROW 4.51 Climb Checklist (4.25) CLIMB (4.25) Best Rate (2750 lb.)(Gear Up, Flaps Up) 9OKIAS Best Rate (2750 lb.)(Gear Down, Flaps Up) 78 KIAS Best Angle (2750 lb.)(Gear Up, Flaps Up) 78KIAS Best Angle (2750 lb.)(Gear Down, Flaps Up) 72 KIAS En Route 104 KIAS ElectricFuel Pump OFF atdesired altitude 4.5j Cruise Checklist (4.27) CRUISE (4.27) Reference performance charts,Avco-Lycoming Operators Manual and power settingtable. Normal Maximum Power 75% Power SET per power table Mixture ADJUST 4.5k Approach And Landing Checklist (4.29) APPROACH AND LANDING (4.29) Fuel Selector PROPER TANK Seat Backs ERECT Belts/Harness FASTEN ElectricFuel Pump ON Mixture SET Propeller FULL INCREASE Gear DOWN 129 KIAS max Flaps SET 103 KIAS max Air Conditioner OFF Trim to 75 KIAS REPORT: VB-1612 ISSUED: JULY 12, 1995 4-12 REVISED: MAY 12, 2010 Page: 4-12-(0) Revision: 22, MAY 12, 2010 4-12 SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES 4.5m Stopping Engine Checklist (4.31) STOPPING ENGINE (4.31) CAUTION The flapsmust be placed in the UP positionfor the flap step to support weight. Passengers should be cautionedaccordingly. Flaps RETRACT ElectricFuel Pump OFF Air Conditioner OFF Avionics OFF ElectricalSwitches OFF Propeller FULL INCREASE Throttle CLOSED Mixture IDLE CUT-OFF Magnetos OFF ALTR Switch OFF BATI’ MASTR Switch OFF 4.5n Mooring Checklist (4.33) MOORING (4.33) Parking Brake SET Flaps FULL UP Control Wheel SECURED with belts Wheel Chocks TN PLACE Tie Downs SECURE ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12,2010 4-13 Page: 4-13-(0) Revision: 22, MAY 12, 2010 4-13 SECTION 4 NORMAL PROCEDURES .PA-28R-201, ARROW THIS PAGE INTENTIONALLY LEFT BLANI( REPORT: VB-1612 ISSUED: JULY 12,1995 444 Page: 4-14-(0) Issued: JULY 12, 1995 4-14 SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES 4.7 AMPLIFIED NORMAL PROCEDURES (GENERAL) The following paragraphs are provided to supply detailedinformation and explanationsof the normal procedures necessary for the safe operation of the airplane. 4.9 PREFLIGHT CHECK (4.Sa) The airplane should be given a thorough preflightand walk-around check. The preflightshould include a check of the airplane’soperational status, computation of weight and C.G. limits, takeoff and landing distances,and in-flightperformance. A weather briefingshould be obtained for the intended flightpath, and any other factorsrelatingto a safe flight should be checked before takeoff. 4.9a Cockpit (4.5a) CAUTION The flap position should be noted before boarding the airplane.The flapsmust be placed in the UP position before they will,lock and supportweight on the step. Upon entering the cockpit,release the seat beltssecuring the control wheel. Check thatthe landing gear selectorhandle isin the DOWN position and setthe parking brake.Ensure thatallavionicsand electrical switchesare OFE Check thatthe mixture isin the idlecut-offand the magneto switch is OFF. Turn ON the batterymaster (BATT MASTR) switch; check the fuel quantity gauges for adequate supply and check thatthe annunciator panel illuminates.Turn OFF the battery master (BATe MASTR) switch. Check the primary flightcontrolsand flapsforproper operationand setthe trim to neutral.Open the pitotand staticdrains to remove any moisture that has accumulated in the lines.Check the windows for cleanlinessand thatthe required papers and POH are on board. Properly stow the tow bar and baggage and secure.Close and securethebaggage door. 4.9b Right Wbg (4.Sa) Begin the walk-around atthe trailingedge of the rightwing by checking thatthe wing surfaceand controlsurfacesare clearof icefrost,snow or other extraneous substances.Check the flap,aileronand hinges for damage and operationalinterference. Staticwicks should be firmlyattachedand in good condition.Check the wing tipand lightsfordamage. ISSUED: JULY 12,1995 REPORT: VB-1612 A_1 Page: 4-15-(0) Issued: JULY 12, 1995 4-15 SECTION 4 NORMAL PROCEDURES PA-28R-201, ARROW 4.9 PREFLIGHT CHECK (4.5a)(continued) 4.9b Right Wing (4.Sa)(continued) Open the fuelcap and visuallycheck the fuelcolor.The quantityshould match theindicationthatwas on the fuelquantitygauge.Replace cap securely. The fueltank ventshouldbe clearof obstructions. CAUTION When drainingany amount of fuel,care should be taken to ensure that no fire hazard exists beforestarting engine. Drain a fuelsample from the fueltankintoa container,through the quick drain located at the lower inboard rear corner of the tank.Make sure that enough fuelhas been drainedtoensure thatallwater and sediment isremoved; check forproper fuel.The fuelsystem should be draineddailypriorto thefirst flightand aftereach refueling. Remove thetiedown and chock. Next, a complete check of the landinggear.Check thegear strutforproper inflation, thereshould be 2.0 +1-0.25 inches of strutexposure under a normal staticload.Check the tirefor cuts.wear, and proper inflation. Make a visual check of thebrake blockand disc. Check thatthefreshairinletisclearofforeignmatter. 4.9c Nose Section (4.5a) Check the generalconditionof the nose sectionand check for oilor fluid leakage and thatthecowling issecure.Check the oillevel;make surethatthe dipstickhas been properlyseatedand the oilcap properlysecured.Check the engine baffleseals.Check thewindshieldand cleanifnecessary.The prbpeller and spinnershould be checked for detrimentalnicks,cracks,or otherdefects. The airinletsshould be clearof obstructionsand check the alternatorbeltfor propertension.The landinglightshould be cleanand intact. Remove thechock and check the nose gear strutforproperinflation; there should be 2.75 +1- 0.25 inches of strutexposure under a normal staticload. Check thetireforcuts,wear,and proper inflation. REPORT: VB-1612 ISSUED: JULY 12,1995 4-16 Page: 4-16-(0) Issued: JULY 12, 1995 4-16 SECTION 4 PA.28R-201, ARROW NORMAL PROCEDURES 4.9 PREFLIGHT CHECK (4.Sa)(continued) 4.9c Nose Section (4.Sa)(continued) CAUTION When draining any amount of fuel,care should be taken to ensure that no fire hazard exists beforestartingengine. Open the fuel strainerlocated on the leftside of the firewalllong enough to remove any accumulation of water and sediment. 4.9d Left Wing (4.5a) The wing surfaceshould be clearof ice,frost,snow, or other extraneous substances. Check the stallwarning vane for condition and freedom of movement. Open the fuel cap and visuallycheck the fuel color.The quantity should match the indicationthatwas on the fuel quantitygauge. Replace fuel cap securely. Check that the fresh air inletis clear of foreign matter and remove the chock. Check the main gear strutfor proper inflation;thereshould be 2.0 +1-0.25 inches of strutexposure under a normal staticload. Check the tirefor cuts, wear, and proper inflation. Malce a visualcheck of the brake block and disc. CAUTION When draining any amount of fuel,care should be taken to ensure that no fire hazard exists before startingengine. The fuel tank vent should be clearof obstructions.Drain enough fuelinto a containerto ensure thatallwater and sediment has been removed; check for proper fuel. Remove tie down and remove the cover from the pitot mast on the underside of the wing. Make sure the hole is open and clearof obstructions. Check the wing tipand lightsfor damage Check the aileron,flap,and hinges for damage and operationalinterferenceand thatthe staticwicks are firmly attachedand in good condition. 4.9e Fuselage (4.Sa) Check the condition and securityof the antennas and thatthe ports in the leftsidestaticpad are clear.The empennage should be clearof ice,frost,snow, or otherextraneous substances.Check thatthe freshairinleton the leftside of the fuselage is clear.Check the stabilatorand trim tab for damage and operationalinterference;the trim tab should move in the same directionas the stabilator. Remove the tiedown. Check thatthe portsin therightsidestaticpad are clear. ISSUED: JULY 12, 1995 REPORT ‘1)3-1612 4-17 Page: 4-17-(0) Issued: JULY 12, 1995 4-17 SECTION 4 NORMAL PROCEDURES PA-28R-201, ARROW 4.9 PREFLIGHT CHECK (4.5a)(continued) 4.9e Fuselage (4.5a)(continued) Upon returningto the cockpit,an operationalcheck of the interiorlights, exteriorlights,stallwarning system,and pitotheat should now be made. Turn the batterymaster switch and other appropriateswitches ON. Check the panel lightingand the overhead flood light Visuallyconfirm thatexteriorlightsare operational.Lift the stalldetectoron the leading edge of the leftwing and determine thatthe warning horn isactivated.With the pitotheat switch ON the pitothead willbe hot to the touch.After thesechecks arecomplete, the battery master (BATT MASTR) switch and allelectricalswitches should be turned OFF. Board the passengers and close and secure the cabin door.Fasten the seat beltsand shoulder harness and check the functionof the inertiareelby pulling sharplyon the strap.Fasten seatbeltson empty seats. REPORT: VB-1612 ISSUED: JULY 12, 1995 4-18 REVISED: MAY 12,2010 Page: 4-18-(0) Revision: 22, MAY 12, 2010 4-18 SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES 4.10 ENGINE START GENERAL CAUTION: Do not attemptflightifthereisno indicationof alternator output. CAUTION: Ifa positiveoilpressureis not indicatedwithin 30 seconds following an engine start,stop the engine and determine the trouble. In cold weather itwill take a few seconds longerto get a positiveoilpressureindication. NOTE: Startermanufacturer recommends startercranking periods be limited to 10 seconds with a 20 second rest period between cranking attempts.Maximum of 6 startperiods allowed. If startis not achieved on sixth attempt allow starterto cool for 30 minutes before attemptingadditional starts. 4.11 BEFORE STARTING ENGINE (4.5b) Before startingthe engine,setthe parking brake ON. Check thatallcircuit breakersare in and thatthe alternateairisOFF. Move the propellercontrolto the fullINCREASE rpm position.Ensure thatallavionics switches are OFF. Set the fuelselectorto the desiredtank. 4.13 ENGINE START (4.5c) 4.13a Normal Start Cold Engine (4.5c) Open the throttleleverapproximately 1/2 inch.Turn ON the alternatorand batterymaster switches,and the electricfuelpump. Move the mixture control to fullRICH untilan indicationis noted on the fuelflow meter.The engine is now primed. Move the mixture controlto idlecut-off,check thatthe propellerarea is clear,and engage the starterby rotatingthe magneto switch clockwise.When theengine fires,releasethe magneto switch,advance themixture controlto full RICH and move the throttleto the desiredsetting.Check the oilpressure. Ifthe engine does not firewithin fiveto ten seconds, disengage the starter and reprime. ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12,2010 4-18a Page: 4-18-(1) Revision: 22, MAY 12, 2010 4-18a SECTION 4 NORMAL PROCEDURES PA-28R-201, ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 4-18b REVISED: MAY 12, 2010 Page: 4-18-(2) Revision: 22, MAY 12, 2010 4-18b SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES 4.13 ENGINE START (4.5c)(continued) 4.13b Normal Start Hot Engine (4.5c) Open the throttleapproximately 112 inch. Turn ON the alternatorand batterymaster switches,and the electricfuelpump. The mixture controllever should be in idlecut-off.Check thatthe propellerarea isclear,and engage the starterby rotatingthe magneto switch clockwise. When the engine fires, releasethe magneto switch,advance the mixture, and move the throttleto the desiredsetting.Check the oilpressure. 4.13c Engine Start When flooded (4Sc) The throttlelevershould he fullOPEN. Turn ON the alternatorand battery master switches,and turn OFF the emergency fuelpump. The mixture control lever should be in idlecut-off.Check that the propeller area is clear,and engage the starterby rotatingthe magneto switch clockwise.When the engine fires.releasethe magneto switch,advance the mixture, and retardthe throttle. Check the oilpressure. 4.13d Engine Start With External Power Source (4.5c) An optional feature called the Piper External Power (PEP) allows the operatorto use an externalbatteryto crank the engine without having to gain access to the airplane’sbattery. Turn OFF the alternator switch, the battery master switch,-and all electrical equipment. Connect the RED lead of the PEP kitjumper cable to the POSITIVE (+) terminalof an external12-voltbatteryand the BLACK lead to the NEGATIVE (-)terminal.Insertthe plug of thejumper cable intothe socket located on the fuselage.Note that when the plug is inserted,the electrical system isON. Proceed with the normal starlingtechnique. After the engine has started.reduce power to the lowest possiblerpm and disconnect the jumper cable from the aircraft. Turn the alternatorand battery master switchesON. Check the alternatorammeter foran indicationof output. DONOT ATTEMPT FLIGHT IF THERE IS NO INDICATION OF ALThRNATOR OUTPUT. CAUTION Itis possibleto use the ship’sbatteryin parallel by turning only the batterymaster switch ON. This will give longer cranking capabihttes,but will not increase the amperage. Care should be exercised because if the ships batteryhas been depleted, the external power supply can be reduced to the levelof the ship’sbattery.This can be tested by turning only the battery master switch ON momentarily while the starteris engaged. If cranking speed increases,the ship’s battery is at a higher level than the external power supply. ISSUED: JULY 12,1995 REPORT: VB-1612 4-10 Page: 4-19-(0) Issued: JULY 12, 1995 4-19 SECTION 4 NORMAL PROCEDURES PA-28R-201, ARROW 4.13 ENGINE START (4.5c)(continued) 4.13d Engine Start With External Power Source (4.5c)(continued) NOTE For all normal operations using the PEP jumper cables, the battery master and alternatorswitches should be OFF. When the engine is firingevenly,advance the throttleto 800 rpm. If oil pressure is not indicatedwithin thirtyseconds, stop the engine and determine the trouble.In cold weather, it will take a few seconds longer to get an oil pressure indication.If the engine has failedto start,refer to the Lycoming Operating Handbook, Engine Troubles and Their Remedies. Startermanufacturer recommends startercranking periodsbe limitedto 10 seconds with a 20 second restperiodbetween cranking attempts.Maximum of 6 startperiodsallowed. Ifstartisnot achieved on sixthattemptallow starterto cool for30 minutes before attemptingadditionalstarts. 4.15 WARM-UP (4.5d) Warm-up the engine at 1400 to 1500 rpm. Avoid prolonged idlingat low rpm, as thispracticemay resultin fouled spark plugs. Takeoff may be made as soon as the ground check is completed, provided that the throttlemay be opened without backfiring or skipping, and without a reductionin engine oilpressure. Do not operate the engine at high rpm when running up or taxiingover ground containing loose stones,gravel or any loose material thatmay cause damage to the propellerblades. 4.17 TAXIING (4.5e) Before attempting to taxi the airplane, ground personnel should be instructed and approved by a qualified person authorized by the owner. Ascertain thatthe propellerback blastand taxiareasare clear. Release the parking brake and apply power slowly to startthe taxiroll. Taxi a few feetforward and apply the brakes to determine theireffectiveness. Taxi with the propeller set in low pitch,high rpm setting.While taxiing, make slightturnsto ascertainthe effectivenessof the steering. REPORT: VB-1612 ISSUED: JULY 12, 1995 4-20 REVISED: MAY 12, 2010 Page: 4-20-(0) Revision: 22, MAY 12, 2010 4-20 SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES 4.17 TAXIING (4.5e)(continued) Observe wing clearanceswhen taxiingnear buildingsor other stationary objects.Ifpossible,stationan observeroutsidetheairplane. Avoid holes and rutswhen taxiingover uneven ground. Do not operatethe engine at high rpm when running up or taxiingover ground containingloose stones,gravel or any loose materialthatmay cause damage to thepropellerblades; 4.19 GROIJ?ID CHECK (4Sf) Set the parking brake and check thatthe propellercontrolis setat high rpm. Advance the throttleto 2000 rpm for checking the magnetos. Drop off on eithermagneto should not exceed 175 rpm and the differencebetween the magnetos should not exceed 50 rpm. Operation on one magneto should not exceed 10 seconds. Check the vacuum gauge; the indicatorshould read between 4.8 and 5.1 inches Hg at 2000 rpm. Retard the throttle. Check both oiltemperature and oilpressure.The temperaturemay be low forsome time ifthe engine isbeing run forthe firsttime of the day.The engine iswarm enough fortakeoffwhen the throttlecan be opened without the engine faltering. Check the ammeter forproper alternatoroutput. Check the annunciator panel lightswith the press-to-test button.Also check the alternateair. The propellercontrol should be moved through itscomplete range to check for proper operation,and then placed in fullINCREASE rpm for takeoff.To obtain maximum rpm, pus