Pilot’s Operating Handbook

thru and Supplement 11. 9-72 ChristinaL. Marsh 9-73 Added pages thru and Supplement 12. Sep. 14, 2000 9-74 Date Rev. 6 vi Added Rev. 6 to L of R page. (PROOI 221) 9-i Revised T of C. 9-75 Added pages ChristinaL. Marsh thru and Supplement 13. 9-76 Dec 21. 2000 Date Rev. 7 vi Added Rev. 7 to L of R page. (PR010129) 2-7 Revised para.2.23. ChristinaL. Marsh Jan. 29, 2001 Date Rev. 8 vi Added Rev. 8 to L of R page. (PR011220) 9-i Revised T of C. 9-77 Added pages A1b’rt J.Mill thru and Supplement 14. 9-86 Dec. 20, 2001 Date REPORT: VB-1612 ISSUED: JULY 12, 1995 vi REVISED: DECEMBER 20, 2001 HB-PQY, Page: 0-0-(6) Revision: 8, DECEMBER 20, 2001 vi PA-28R-201, ARROW PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Rev. 10 (PR0403 10) Rev. II (PRO4 1007) 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,to page iv, Moved info,from page iii. Added page and Rev. 9 to L of R. Added page. Revised para.2.23. Revised para.2.23. Moved info,to page 8-lb and revised para. 8.1. Added page and revised para.8.1. Added page and moved info. from pages 8-1 and 8-2. Moved info,to page 8-lb and revised para. 8.3. Revised T of C. Revised Section 1. Added pages and Supplement 15. Added Rev. IOtoLofR. Revised para.3.5b. Revised para. 3.5e. Revised para.4.5a. Revised para.4.5a. Added Rev. 11 to L of R. Added Rev. II toLofR. Revised Figure 7-2 1. Revised T of C. Added pages and Supplement 16. Jan. 5, 2004 Date Albert J.Mill March 10, 2004 Date ISSUED: JULY 12, 1995 REVISED: OCTOBER 7, 2004 REPORT: VB-1612 Revision Number and Code Revised Pages Description of Revisions FAA Approval Signature and Date Rev. 9 (PRO4OIO5) 111 Albert J.Mill vi-a 3-3 3-5 4-4 4-5 vi-a vi-b 7-21 9-i 9-91 thru 9-108 vi-a HB-PQY, Page: 0-0-(7) Revision: 11, OCTOBER 7, 2004 vi-a PA-28R-201, ARROW PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision Number and Code Revised Pages Description of Revisions FAA Approval Signature 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. (PRO5OI 17) 2-7 Revised and reorganized thru para.2.23 Placards. 2-10 9-96 Revised Section 3. 9-98 Revised Section 3. 9-100 Revised Section 3. 9-108 Revised Section 7. Linda J.Dicken Jan. 17, 2005 Rev. 13 vi-b Added Rev. 13 to L of R. (PR050523) 9-i RevisedTofC. 9-91 Revised Supplement 16. thru 9-118 9-1 19 Revised page numbers. thru Linda J.Dicken 9-122 May 23, 2005 Rev. 14 vi-b Added Rev. 14 to L 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 revised Section 2. Sept. 12,2005 Rev. 15 vi-b Added Rev. 15 to L of R. (PRO5 1128) 9-96 Revised Section 3. 9-99 Revised Section 3. 9-101 Revised Section 3. l.cL___9-103 l.cL___9-103 Revised Section 3. LindJ. Dicken 9-104 Revised Section 3. Nov. 28, 2005 REPORT: VB-1612 ISSUED: JULY 12, 1995 vi-b REVISED: NOVEMBER 28, 2005 HB-PQY, 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 Description of 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. .4zzr (PR06041 1) 9-111 Revised Section 7A. Linda 3. 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. Linda 3.Dicken 9-158 May 22, 2006 Rev. 19 vi-c Added Rev 19 to L of R. (PRO9O 121) 9-li Added Supplements 19 and 2OtoTofC. AllrtJMill 9-159 Added Supplements 19 and January 21, 2009 thru 20. 9-172 Rev. 20 vi-c Added Rev. 20 to L of R. (PR090510) 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. (PR090930) 4-20 Revised Para. 4.13d 8-lb Revised wording in General Section. Albert 3 Mill September 30,2009 ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: SEPTEMBER 30, 2009 Vl-C HB-PQY, Page: 0-0-(9) Revision: 21, SEPTEMBER 30, 2009 vi-c PA-28R-201, ARROW PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) 4-iv 4-7 4-8 4-9 4-10 4-11 4-12 4-13 4-18 4-1 8a 4-18b 4-20 7-29 7-32 9-il 9-107 9-144 9-173 thru 9-184 Added Rev. 22 to L of R Added Note to Para. 2.23 Revised TOC. Relocated text to pg. 4-u. Added textfrom pg. 4-i. Revised TOC, Relocated text to pg. 4-ui. Added textfrom pg. 4-u. Revised TOC. Relocated textto pg. 4-iv. Added textfrom pg. 4-ui. Revised Para.4.5c.Relocated textto pg. 4-8. Added textfrom pg. 4-7. Relocated textto pg. 4-9. Added textfrom pg. 4-8. Relocated text topg. 4-10. Added textfrom pg. 4-9. Relocated textto pg. 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 Section 4. Revised Note in Section 4. Added Supplement 21. Revision FAA Approval Number and Revised Description of Revisions Signature Code Pages and Date Rev. 22 (PR100512) vi-d 2-8 4-i 4-u 4-ui REPORT: VB-1612 Wayne E. Gaulzetti May 12, 2010 ISSUED: JULY 12, 1995 REVISED: MAY 12, 2010 vi-d HB-PQY, Page: 0-0-(10) Revision: 22, MAY 12, 2010 vi-d PA-28R-201, ARROW PILOT’S OPERATING HANDBOOK LOG OF REVISIONS Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 23 ii Updated copyright dates. (PR1011OI) vi-e Added Page. Added Rev. 23 toLofR. vi-f Added Page. Albert J.Mill 9-18 1 Revised Section 4. November 1,2010 Rev. 24 ii Updated copyright date. (PRII.l024) vi-e Added Rev. 24 to L of R. 9-u Revised T of C. 9-185 Added page. Added Supplement 22. Wayne E. Gaulzetti 9-186 Added page. October 24, 2011 Rev. 25 ii Updated copyright date. (PR121031) vi-e Added Rev. 25 to L of R. 4-10 Revised Para. 4.5g. 4-12 Revised Para. 4.5k. 4-22 Revised Para. 4.21. 4-25 Revised Para. 4.29. 4-27 Revised Para. 4.39. Wayne E. Gaulzetti 7-6 Revised Para. 7.11. October 31, 2012 Rev. 26 ii Updated publicationinfo (PRI6O1 12) and copyright date. vi-e Added Rev. 26 to L of R. 9-u Revised T of C. 9-187 Added Supplements 23 thru thru 25. 9-194 Added pages. January 12, 2016 Rev. 27 vi-e Added Rev. 27 to L of R. (PR 160226) 7-2 Revised Para. 7.5. Wrigll 7-16 Revised Para. 7.17. February 26, 2016 ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: FEBRUARY 26,2016 vi-e HB-PQY, Page: 0-0-(11) Revision: 27, FEBRUARY 26, 2016 vi-e PA-28R-201, ARROW PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 28 vi-f Added Rev. 28 to L of R. (PR16041 1) 7-2 Revised Para. 7.5. 7-16 Revised Para. 7.17. 9-u Added Supp. 26 to Section 9 TOC. 9-195 Added Supp. 26 to thru Section 9. 9-196 April 11,2016 Rev. 29 ii Updated copyright. (PR18OI1I) vi-f AddedRev. 29toLofR. 2-6 Added Para. 2.22. 2-i RevisedTofC. 2-9 Revised Para. 2.23. 9-185 Revised Supplement 22. January 11, 2018 Rev. 30 vi-f Added Rev. 30 to L of R. (PR180223) 8-7 Revised Para. 8.13. 9-il Added Supps. 27, 28, 29 to Section 9 TOC. 9-185 Revised Supplement 22. 9-197 Added Supps. 27, 28, 29 to thru Section 9. 9-202 February 23, 2018 REPORT: VB-1612 ISSUED: JULY 12, 1995 vi-f REVISED: FEBRUARY 23, 2018 HB-PQY, Page: 0-0-(12) Revision: 30, FEBRUARY 23, 2018 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 TEE AIRPLANE AND ITS SYSTEMS SECTION 8 AIRPLANE HANDLING, SERVICING AN]) MAINTENANCE SECTION 9 SUPPLEMENTS SECTION 10 OPERATING TIPS ISSUED: JULY 12, 1995 REPORT: VB-1612 HB-PQY, Page: 0-0-(13) Issued: JULY 12, 1995 vii PA-28R-201, ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: ‘111-1612 ISSUED: JULY 12, 1995 v1u HB-PQY, Page: 0-0-(14) Issued: JULY 12, 1995 viii SECTION 1 PA-28R-201, ARROW GENERAL TABLE OF CONTENTS SECTION 1 GENERAL ParagTaph 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 Airplane Weights 1-5 1.15 BaggageSpace 1-5 1.17 SpecificLoadings 1-5 1.19 Symbols, Abbreviations and Terminology 1-6 0 ISSUED: JULY 12,1995 REPORT: VB-1612 HB-PQY, Page: 1-0-(1) Issued: JULY 12, 1995 1-i SCT1ON 1 GENERAL PA-28R-201, ARROW C) THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 1-il HB-PQY, Page: 1-0-(2) Issued: JULY 12, 1995 1-ii SECTION 1 PA-28R-20i, ARROW GENERAL SECTION I GENERAL Li INTRODUCTION This Pilot’sOperating Handbook is designed for maximum utilization as an operating guide for the pilot.It includes the material required to be furnished to the pilot by the Federal Aviation Regulations and additional information provided by the manufacturer and constitutes the FAA Approved Airplane Flight Manual. This handbook is not designed as a substitute for adequate and competent flightinstruction,knowledge of current airworthiness directives, applicable federal air regulations or advisory circulars.Itis not intended to be a guide for basic flightinstructionor a trainingmanual and should not be used for operational purposes unless kept in a current status. Assurance that the airplane is in an airworthy condition is the responsibility of the owner. The pilot in command is responsible for determining that the airplane is safe for flight.The pilot is also responsible for remaining within the operating limitations as outlined by instrument markings, placards, and thishandbook. Although the arrangement of this handbook is intended to increase its in-flightcapabilities,itshould not be used solely as an occasional operating reference.The pilot should study the entirehandbook to familiarizehimself with the limitations, performance, procedures and operational handling characteristicsof the airplane before flight. The handbook has been divided into numbered (arabic) sections,each provided with a finger-tiptab divider for 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 deliberate omission of certainparagraph numbers, figure numbers, item numbers and pages noted as being intentionallyleftblank. ISSUED: JULY 12, 1995 REPORT: VB-1612 I I HB-PQY, Page: 1-1-(0) Issued: JULY 12, 1995 1-1 I GENERAL THREE VIEW Figure 1-1 PA-28R-2O, ARROW 170.0 31.0 LW REPORT: VB-1612 1-2 ISSUED: JULY 12, 1995 HB-PQY, Page: 1-2-(0) Issued: JULY 12, 1995 1-2 SECTEON 1 PA-28R-201, ARROW GENERAL 1.3 ENGINES (a) Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model Number IO.360-C1C6 (d) Rated Horsepower 200 (e) Rated Speed (rpm) 2700 (I) Bore(in.) 5.125 (g) Stroke (in.) 4.375 (h) Displacement (cu.in.) 361 (I) 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 (d) Number of Blades 2 (e) Hub Model B2D34C213 (f) Propeller Diameter (in.) (1) Maximum 74 (2) Minimum 73 (g) Propeller‘I’pe Constant Speed, HydraulicallyActuated ISSUED: JULY 12,1995 REPORT: VB-161 HB-PQY, Page: 1-3-(0) Issued: JULY 12, 1995 1-3 SECTION 1 GENERAL PA-28R-201, ARROW 1.5 PROPELLERS (continued) HARTZELL (a) Number of Propellers (b) PropellerManufacturer Hartzell (c) Blade Model F7666A-2R (d) Number of Blades 2 (e) Hub Model HC-C2YK-1( )F1 (f) PropellerDiameter (in.) (1) Maximum 74 (2) Minimum 72 (g) PropellerType Constant Speed, HydraulicallyActuated 1.7 FUEL (a) Fuel Capacity (U.S. gal.)(total) 77 (b) Usable Fuel (U.S. gal.)(total) 72 (c) Fuel Grade, Aviation (1) Minimum Octane 1001130- Green or 10011-Blue AviationGrade (2) AlternateFuels Refer to latestrevision of Lycoming Service Instruction1070, except alcohol isnot approved for use in this airplane.MIL-I-27686D isapproved. 1.9 OIL (a) Oil Capacity (U.S. qts.) 8 (b) Oil Specification Refer to latestissue of Lycoming Service Instruction1014 (c) Oil Viscosity Refer to Section 8 paragraph 8.19 REPORT: VB-1612 ISSUED: JULY 12, 1995 1-4 HB-PQY, 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) Standard Empty Weight (lb.): Weight of a standard airplaneincluding unusable fuel,fulloperating fluidsand 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 to be used for C.G. calculationsfor the aircraftspecified. ISSUED: JULY 12, 1995 REPORT: VB-1612 HB-PQY, 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 operational significanceto the pilot. (a) General Airspeed Terminology and Symbols CAS Calibrated Airspeed means the indicated speed of an aircraft,corrected for position and instrument error.Calibrated airspeed is equal to true airspeed in standard atmosphere atsea level. KCAS Calibrated Airspeed expressed in Knots. OS Ground Speed is the speed of an airplane relativeto the ground. 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 this handbook assume zero instrument error. KIAS IndicatedAirspeed expressed in Knots. M Mach Number is the ratio of true airspeed to the speed of sound. TAS True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude, temperature and compressibility. VA Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstressthe airplane. Vra Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribedextended position. REPORT: VB-1612 ISSUED: JULY 12, 1995 1-6 HB-PQY, Page: 1-6-(0) Issued: JULY 12, 1995 1-6 SECTION 1 PA-28R-201, ARROW GENERAL 1.19 SYMBOLS, ABBREVIATLONS, AND TERMINOLOGY (continued) VLE Maximum Landing Gear Extended Speed is the maximum speed at which an aircraftcan be safely flown with the landing gear extended. VL0 Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safelyextended orretracted. Vr’nfMNE Never Exceed Speed or Mach Number isthe speed limitthat may not be exceeded at any time. VNO Maximum StructuralCruising Speed is the speed that should not be exceeded except in smooth airand then only with caution. Vs StallingSpeed or the minimum steady flight speed at which the airplaneiscon- trollable. Vso StallingSpeed or the minimum steady flight speed at which the airplaneis con- trollable in the landing configuration. Vx Best Angle-of-Climb Speed is the airspeed which deliversthe greatestgain of altitude in the shortestpossiblehorizontaldistance. Best Rate-of-Climb Speed is the airspeed which deliversthe greatestgain in altitudein the shortestpossibletime. ISSUED: JtiLY 12,1995 REPORT: VB-1612 HB-PQY, Page: 1-7-(0) Issued: JULY 12, 1995 1-7 SECTION 1 GENERAL PA-28R-201, ARROW 1.19 SYMBOLS, ABBREVIATIONS, AN]) TERMINOLOGY (continued) (b) Meteorological Terminology ISA International StandardAtmosphere in which: (I) Theairisadiyperfectgas. (2) The temperature at sea levelis 15° Celsius Celsius (59° Fahrenheit). (3) The pressure atsea levelis29.92 inches Hg (1013.2mb). (4) The temperature gradientfrom sea level to the altitudeat which the temperature is -56.5°C (-69.7°F) is 0.00198°C (-0.003564°F) per foot and zero above thataltitude. OAT Outside Air Temperature is the freeairstatic temperature, obtained either from inflight temperature indications or ground meteorological sources, adjusted for instrument instrument errorand compressibilityeffects. Indicated The number actually read from an PressureAltitude altimeterwhen the barometric subscale has been set to 29.92 inches of merculy (1013.2 millibars). Pressure Altitude Altitude measured from standard sea-level pressure (29.92 in. Hg) by a pressure or barometric altimeter. It is the indicated pressure altitudecorrected for positionand instrument error. In this handbook, altimeter instrument errors are assumed to be zero. StationPressure Actual atmospheric pressure at field elevation. Wind The wind velocitiesrecorded as variables on the charts of this handbook are to be understood as the headwind or tailwind components of the reportedwinds. REPORT: VB-1612 ISSUED: JULY 12, 1995 1-8 HB-PQY, Page: 1-8-(0) Issued: JULY 12, 1995 1-8 SECTION 1 PA-28R-201, ARROW GENERAL 1.19 SYMBOLS, ABBREVIATIONS, AND TERMINOLOGY (continued) Cc) Power Terminology Takeoff Power Maximum power permissible for takeoff. Maximum Con- Maximum power permissible continuously tinuous Power 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) Airplane Performance and Flight Planning Terminology Climb Gradient The demonstrated ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval. Demonstrated The demonstrated crosswind velocityis the Crosswind velocityof the crosswind component for Velocity which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests. Accelerate-Stop The distance required to accelerate an air- Distance plane to a specified speed and, assuming failureof an engine at the instantthatspeed isattained,to bring the airplaneto a stop. Minimum en route1FR altitude. Route Segment A part of a route. Each end of that part is identifiedby: (1) a geographical location; or (2) a point at which a definiteradio fix can be established. ISSUED: JULY 12,1995 REPORT: VB-1612 HB-PQY, Page: 1-9-(0) Issued: JULY 12, 1995 1-9 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 usually given in terms of distance from the reference datum. Arm The horizontal distance from the reference datum to the center of gravity (C.G.) of an item. Moment The product of the weight of an item multiplied multiplied by its arm. (Moment divided by a constant is used to simplify balance calculations calculations by reducing the number of digits.) CenterofGravity Thepoint at which an airplane would (C.G.) balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. C.G. Arm The arm obtained by adding the airplane’s individualmoments and dividing the sum by the totalweight. C.G. Limits The extreme center of gravity locations within which the airplanemust be operated at a given weight. Usable Fuel Fuel availablefor ifightplanning. Unusable Fuel Fuel remaining aftera runout testhas been completed in accordance with governmental governmental regulations. Standard Empty Weight of a standard airplane including Weight unusable fuel,fulloperating fluidsand full oil. REPORT: VB-1612 ISSUED: JULY 12, 1995 1-10 HB-PQY, 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 if applicable,and basic empty weight. MaximumRamp Maximumweight approved for ground Weight maneuver. (Itincludes weight of start,taxi and run up fuel.) Maximum Maximum weight approved for the start of Takeoff Weight the takeoffrun. Maximum Maximum weight approved for the landing Landing Weight touchdown. Maximum Zero Maximum weight exclusive of usable fuel. Fuel Weight 0 ISSUED: JULY 12,1995 REPORT: VB-1612 HB-PQY, Page: 1-11-(0) Issued: JULY 12, 1995 1-11 SECTION 1 GENERAL PA.28R-201, ARROW r THJS PAGE INTENTIONALLY LEFF BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 1-12 HB-PQY, Page: 1-12-(0) Issued: JULY 12, 1995 1-12 SECTION 2 PA-28R-201, ARROW LIMITATIONS TABLE OF CONTENTS SECTION 2 LIMITATIONS Paragraph No. 2.1 General 2-1 2.3 Airspeed Limitations 2-1 2.5 Airspeed Indicator Markings 2-2 2.7 Power Plant Limitations 2-3 2.9 Power Plant Instrument Markings 2-4 2.11 Weight Limits 2-5 2.13 Center of Gravity Limits 2-5 2.15 Maneuver Limits 2-5 2.17 Flight Load Factors 2-6 2.19 Types of Operalions 2-6 2.21 Fuel Limitations 2-6 2.22 Smoking 2-6 2.23 Placards 2-8 ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: JANUARY 11, 2018 2-1 HB-PQY, Page: 2-0-(1) Revision: 29, JANUARY 11, 2018 2-i SECTION 2 LThIITATIONS PA-28R-201, ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 2-li HB-PQY, 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, instrument markings, color coding and basic placards necessary for the safe operation of 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 K.IAS KCAS Never Exceed Speed (‘iNn) Do not exceed thisspeed in any operation. 183 186 Maximum StructuralCruising Speed (VNO) Do not exceed thisspeed except in smooth airand then only with caution. 146 148 Design Maneuvering Speed (VA) Do not make fullor abrupt controlmovements above thisspeed. At27501bs.G.W. 118 120 At 1865 lbs.G.W. 96 96 CAUTION Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced. Linear interpolationmay be used for intermediate gross weights. Maneuvering speed should not be exceeded while operatingin rough ak ISSUED: JULY 12, 1995 REPORT: VB-1612 HB-PQY, Page: 2-1-(0) Issued: JULY 12, 1995 2-1 SECTION 2 LIMITATIONS PA-28R-201, ARROW Z3 AIRSPEED LIMITATIONS (continued) SPEED KIAS KCAS Maximum Flaps Extended Speed (VFE) Do not exceed thisspeed with the flaps extended. 103 103 Maximum Landing Gear Extension Speed Do not exceed thisspeed when extending the landing gear. 129 130 Maximum Landing Gear RetractionSpeed Do not exceed thisspeed when retracting the landing gear. 107 107 Maximum Landing Gear Extended Speed (VLE) Do not exceed thisspeed with the landing gear extended. 129 130 2.5 AIRSPEED INDICATOR MARKINGS MARKING lAS Red Radial Line (Never Exceed) 183 KTS Yellow Arc (Caution Range Smooth Air Only) 146 KTS to 183 KTS Green Arc (Normal Operating Range) 60 KTS to 146 KTh White Arc (Flap Down) 55 US to 103 KTS REPORT: VB-1612 ISSUED: JULY 12, 1995 2-2 HB-PQY, 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 (b) Engine Manufacturer Lycoming (c) Engine Model No. 10-360-C 1C6 (d) Engine Operating Limits (1) Maximum Horsepower 200 (2) Maximum Rotation Speed (RPM) 2700 (3) Maximum Oil Temperature 245°F (e) Oil Pressure Minimum (red line) 25 PSI Maximum (redline) 100 PSI (f) Fuel Flow/Pressure Maximum (redline) 21.4 GPHII2 PSI (g) Fuel Grade (minimum octane) 100 or IOOLL Aviation Grade (h) Number of Propellers I (I) PropellerManufacturer McCauley or Hartzell ) PropellerHub and Blade Model (1) McCauley B2L)34C213190DHA-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 Pitch Stop 12.5 + 0.2° High Pitch Stop 27.5 + 0.5° (2) Hartzell Low Pitch Stop 14.0 + 02° High Pitch Stop 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: VE-1612 2.3 HB-PQY, Page: 2-3-(0) Issued: JULY 12, 1995 2-3 LIMITATIONS PA-28R-201, ARROW 2.9 POWER PLANT INSTRUMENT MARKINGS (a) Tacbometer Green Arc (Normal Operating Range) 500 to 2700 RPM Red Line (Maximum Continuous Power) 2700 RPM (b) Oil Temperature Green Arc (Normal Operating Range 750 to 245°F Red Line (Maximum) 245°F (c) Oil Pressure Green Arc (Normal Operating Range 60 PSI to90 PSI Yellow Arc (Caution Range) (Idle) 25 PSI to 60 PSI Yellow Arc (Caution Range) (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 Operating Range 2 GPHIO.05 PSI to 21.4 GPHI12 PSI Red Line (Maximum) 21.4 GPH)12 PSI REPORT: VB-1612 ISSUED: JULY 12,1995 2.4 HB-PQY, 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 limited by 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 Straight line variationbetween 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 responsibility of 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 acrobatic maneuvers including spins. 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 HB-PQY, Page: 2-5-(0) Revision: 14, SEPTEMBER 12, 2005 2-5 SECTION 2 LIMITATIONS PA-28R-201, ARROW 2.17 FLIGHT LOAD FACTORS (a) Positive Load Factor (Maximum) 3.8 G (b) Negative Load Factor (Maximum) No inverted maneuvers approved 2.19 TYPES OF OPERATIONS The airplane is approved for the following operations when equipped in accordance with FAR 91 or FAR 135. (a) Day V.F.R. (b) Night V.F.R. (c) Day I.F.R. (d) Night I.F.R. (e) Non Icing 2.21 FUEL LIMITATIONS (a) Total Capacity 77 U.S. GAL. (b) Unusable Fuel 5 U.S. GAL. The unusable fuel for this airplane has been determined as 2.5 gallons in each wing lank in criticalflight attitudes. (c) Usable Fuel 72 U.S. GAL. The usable fuel in this airplane has been determined as 36.0 gallons in each wing lank. (ci) Fuel remaining when the quantity indicators indicators read zero cannot be used safely in flight 2.22 SMOKING Smoking is not permitted in the aircraft. REPORT: VB-1612 ISSUED: JULY 12, 1995 2-6 REVISED: JANUARY 11, 2018 HB-PQY, Page: 2-6-(0) Revision: 29, JANUARY 11, 2018 2-6 PA-28R-201, ARROW SECTION 2 LIMITATIONS 2.23 PLACARDS In fullview of the pilot: On the instrument panel in full view of the pilot(not required if Avidyne Entegra is installed): NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED Above fuelquantity gauges (not required ifAvidyne Entegra is installed): FUEL REMAINING WHEN THE QUANTITY INDICATORS READ ZERO CANNOT BE USED SAFELY IN FLIGHT. On the instrument panel in fullview of the pilot (not required if Avidyne Entegra isinstalled): WARNING TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY TO GROUND OR DURING FLIGHT THROUGH CLOUD, FOG OR HAZE. On the instrument panel in fullview of the pilot: GEAR DOWN GEAR UP EXTENDED ISSUED: JULY 12, 1995 REVISED: JANUARY 17, 2005 129 KIAS (MAX.) 107 KIAS (MAX.) 129 KIAS (MAX.) REPORT: VB-1612 2-7 LMIIAIIU!N5 TH1S AIRCRAFT APPROVED FOR NIGHT I.F.R.,NON-ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 9? OR FAR 35. NO ACROBATIC MANEUVERS, INCLUDING SPINS,AFPROVED. THIS AIRCRAFT MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LINITATIONS STATED IN THE FORM OF PLACARDS. MARKINGS AND MANUALS. FUEL REMAINING WHEN THE QUANTITY INDICATORS READ ZERO CANNOT BE USED SAFELY IN FLIGHT. INFO??NATION OIL COOLER WINTERIZATION WINTERIZATION PLATE TO BE REMOVED WHEN AMBIENT TEMPERATURE EXCEEDS 50’F. WARNING TORN OFF STROBE LIGHTO WHEN IIICLOSE PROXIMITO TO CROUND OR BORING FLIGHT 1000060 CLOUD. FOG OR HAZE,,, HB-PQY, 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 following Takeoff and Landing Checklists willbe installed: TAKEOFF CHECKLIST Fuel on Proper Tank Fasten Belts/Harness ElectricFuel Pump On Flaps Set Engine Gauges Checked Trim Tab Set Alternate Air Closed Controls Free Seat Backs Erect Doors Latched Mixture Set Air Conditioner Off Propeller Set LANDING CHECKLIST Propeller Set Gear Down Flaps Set (White Arc) Air Conditioner Off The Air Conditioner Off item in the above Takeoff and Landing Checklists is mandatory for airconditioned aircraftonly. On the instrument panel in fullview of the pilot(not required if Avidyne Entegra isinstalled): MANEUVERING SPEED 118 KIAS AT 2750 LBS. (SEE P.O.H.) On the instrument panel in fullview of the pilot(not required if Avidyne Entegra isinstalled): DEMONSTRATED CROSSWIND COMPONENT 17 KTS On the instrument panel in fullview of the pilot(only required ifAvidyne Entegra is installed): VA- 118 KIAS AT 2750#(SEE POH) DEMO. X-WIND 17 KTS. NOTE Demonstrated crosswind values are NOT limitations. REPORT: VB-1612 ISSUED: JULY 12, 1995 REVISED: MAY 12, 2010 Fuel on Proper Tank Seat Backs Erect Fasten Belts/Harness ElectricFuel Pump On Mixture Rich 2-8 HB-PQY, Page: 2-8-(0) Revision: 22, MAY 12, 2010 2-8 SECTiON 2 PA-28R-201, ARROW LIMITATIONS 2.23 PLACARDS (continued) On the instrument panel in full view of the pilot in aircraft with McCauley propeller installations only: AVOID CONTINUOUS OPERATIONS BETWEEN 1500 AND 1950 RPM BELOW IT’ MANIFOLD PRESSURE. In full view of pilot: CAUTION COMPASS CAL. MAY BE IN ERROR WITH ELECT. EQUIPMENT OTHER THAN AVIONICS ON In full view of the pilot, in (he area of the air conditioner controls, when the air conditioner is installed: WARNING AiR CONDITIONER MUST BE OFF TO INSURE NORMAL TAKEOFF CLIMB PERFORMANCE. Near emergency gear lever: EMERGENCY DOWN Near gear selector switch: GEAR UP 107 KIAS MAX. DOWN 129 KIAS MAX. ISSUED: JULY 12, 1995 REPORT: VB.1612 REVISED: JANUARY 11,2018 2.9 HB-PQY, Page: 2-9-(0) Revision: 29, JANUARY 11, 2018 2-9 SECTION 2 LIMITATIONS PA-28R-201, ARROW 2.23 PLACARDS (continued) On the aftbaggage closeout: MAXIMUM BAGGAGE 200 LBS. NO HEAVY OBJECTS ON HAT SHELF. Adjacent to upper 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 to fueltank fillercaps: AVGAS ONLY GRADE GRADE IOOLL 100 REPORT: VB-1612 ISSUED: JULY 12, 1995 2-10 REVISED: JANUARY 17, 2005 HB-PQY, Page: 2-10-(0) Revision: 12, JANUARY 17, 2005 2-10 —, / 414 ‘i-/ff-’-i’ (HB-2008-135R1) 4AI (Lç / ATTN: Solomon Hecht, Aerospace Engineer, Boston ACO, 12 New England Executive Park, Burlington, MA 01803; telephone: (781) 238-7159; fax: (781) 238-7170. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PT) in the FAA Flight Standards District Office (FSDO), or lacking a PT, your local FSDO. Additional Information (g) For the service alertreferenced in this AD, contact Avidyne Corporation, 55 Old Bedford Road, Lincoln, MA 01773; telephone: (781) 402-7400; fax: (781) 402-7599. Appendix to AD 2008-06-28 Ri Limitations Regarding Avidyne Primary Flight Displays (PFDs) Before conducting flight operations, pilots must review and be familiar with the Crosscheck Monitor section of the Avidyne Primary Flight Display Pilot’sGuide and all limitations contained in the airplane flightmanual, pilot’soperating handbook, or aircraft operating handbook. As a normal practice, allpilots should be vigilant in conducting proper preflight and in-flight checks of instrument accuracy, including: • Preflight check of the accuracy of both the primary and backup altimeter against known airfield elevation and against each other. • Verification of airspeed indications consistent with prevailing conditions at startup, during taxi, and prior to takeoff. • “Airspeed alive” check and reasonable indications during takeoff roll. • Maintenance of current altimeter setting in both primary and backup altimeters. • Cross-check of primary and backup altimeters at each change of altimeter setting and prior to entering instrumentmeteorological conditions (IMC). • Cross-check of primary and backup altimeters and validation against other available data, such as glideslope intercept altitude,prior to conducting any instrument approach. • Periodic cross-checks of primary and backup airspeed indicators, preferably in combination with altimeter cross-checks. For flightoperations under instrument flightrules (IFR) or in conditions in which visual reference to the horizon cannot be reliably maintained (that is IMC, night operations, flight operations over water, in haze or smoke) and the pilot has reasons to suspect that any source (PFD or back-up instruments) of attitude,airspeed, or altitudeis not functioning properly, flight under IFR or in these conditions must not be initiated(when condition is determined on the ground) and further flight under IFR or in these conditions isprohibited until equipment is serviced and functioning properly. Operation of aircraftnot equipped with operating backup (or standby) attitude,altimeter, and airspeed indicators that are located where they are readily visible to the pilot is prohibited. Pilots must frequently scan and cross-check flight instruments to make sure the information depicted on the PFD correlates and agrees with the information depicted on the backup instruments. Issued in Kansas City, Missouri, on April 4, 2008. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-7802 Filed 4-11-08; 8:45 am] HB-PQY, 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 Fire During 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 3.5d Power Off Landing (3.15) 3-4 Gear Down Emergency Landing (3.15a) 3-4 Gear Up Emergency Landing (3.lSb) 3-5 3.5e Fire In Flight(3.17) 3-5 3.5f Loss Of Oil Pressure (3.19) 3-6 3.5g Loss Of Fuel Flow/Pressure (3.21) 3-6 3.5h High Oil Temperature (3.23) 3-6 3.5i ElectricalFailure(325) 3-6 3.5j ElectricalOverload (327) 3-6 3.5k PropellerOverspeed (3.29) 3-7 3.5m Emergency Landing Gear Extension (3.31) 3-S 3.5n Spin Recovery (3.33) 3-9 3.5o Open Door (3.35) 3-9 3.5p Engine Roughness (3.37) 3-9 ISSUED: JULY 12, 1995 REPORT: VB-1612 2: HB-PQY, Page: 3-0-(1) Issued: JULY 12, 1995 3-i SECTION 3 EMERGENCY PROCEDURES PA-28R-201, ARROW TABLE OF COITENTS SECTION 3 EMERGENCY PROCEDURES (cont) Paragraph Page No No. 3.7 Amplified Emergency Procedures (General) 3-11 3.9 Engine Fire During 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 Power Off Landing (3.5d) 3-13 3.15a Gear Down Emergency Landing (3.5d) 3-14 3.lSb Gear Up Emergency Landing (3.5d) 3-14 3.17 FirelnFlight(3.5e) 3-15 3.19 Loss of Oil Pressure (3.51) 3-15 3.21 Loss of Fuel Flow/Pressure (3.5g) 3-16 3.23 High Oil Temperature (3.5h) 3-16 3.25 ElectricalFailure(3.5i) 3-16 3.27 ElectricalOverload (3.5j) 3-17 3.29 PropellerOverspeed (3.5k) 3-18 3.31 Emergency Landing Gear Extension (3.Sm) 3-18 3.33 Spin Recovery(3.5n) 3-19 3.35 Open Door (3.5o) 3-19 3.37 Engine Roughness (3.Sp) 3-19 REPORT: VB-1612 ISSUED: JULY 12, 1995 3-il HB-PQY, 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 various emergency or criticalsituations.All of the emergency procedures required by the FAA as well as those necessary for operation of the airplane, as determined by the operating and design features of the airplane, are presented. Emergency procedures associated with optional systems and equipment which require handbook supplements are presented in Section 9, Supplements. This section is divided into two basic parts.The firstpart contains the emergency procedures checklists. These checklists supply an immediate action sequence to be followed during criticalsituationswith littleemphasis on the operation of systems. The numbers located in parentheses aftereach checklist heading indicate where the corresponding paragraph in the amplified procedures can be found. The second part of the section provides amplified emergency procedures corresponding to the emergency procedures checklist items. These amplified emergency procedures contain additional information to provide the pilot with a more complete description of the procedures so they may be more easily understood. The numbers located in parentheses after each paragraph heading indicates the corresponding checklistparagraph. Pilots must familiarize themselves 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 for coping with the particularsituationor condition described. They are not a substitutefor sound judgment and common sense. Most basic emergency procedures are a normal part of pilot training. The information presented in this section is not intended to replace this training.This information is intended to provide a source of reference for the procedures which arc applicable to thisairplane.The pilot should review standard emergency procedures periodicallyto remain proficientin them. ISSUED: JULY 12,1995 REPORT: VB.1612 1-i HB-PQY, 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 MA1EUVERING SPEEDS 27501bs 118 KIAS 1865 lbs 96KIAS 3.3c NEVER EXCEED SPEED Never Exceed Speed 183 KIAS 3.3d POWER OFF GLIDE SPEED 2750 lbs (Gear Up, 0 Flap) 79 KIAS (H REPORT: VTh.1612 ISSUED: JULY 12, 1995 3-2 HB-PQY, 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 sufficientrunway remains for a normal landing, leave gear down and land straightahead. Ifarea ahead isrough or ifitisnecessary to clearobstructions: Gear SelectorSwitch UP Ifsufficientaltitudehas been gamed to attempt a restart: Maintain safeairspeed. Fuel Selector SWITCH to tank containing fuel ElectricFuel Pump CHECK ON Mixture CHECK RICH AlternateAir OPEN Ifpower isnot regained, proceed with power off landing (3.5d). 3.5c ENGINE POWER LOSS IN FLIGHT (3.13) Ifat low altitude: Airspeed MAINTAIN 79 KIAS minimum Prepare for power off landing (3.5d). Ifaltitudepermits: Fuel Selector SWITCH to tank containing fuel ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MARCH 10, 2004 3-3 HB-PQY, 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 for indication of cause of power loss Ifno fuelflow/pressureisindicated,check tank selectorpositionto be sure itison a tank containing fuel. When power isrestored: AlternateAir CLOSE ElectricFuel Pump OFF Ifpower isnot restored,prepare for power off landing. Trim for 79 KIAS. 3.Sd POWER OFF LANDING (3.15) Trim for 79 KIAS. Locate suitablefield. Establishspiralpattern. 1000 ft. above field at downwind position for normal landing approach. When fieldcan be easilyreached, slow to72 KIAS for shortestlanding. Gear Down Emergency Landing (3.15a) Touchdowns should normally be made atthe lowest possibleairspeed with fullflaps. When committed to landing: Landing Gear Selector DOWN Flaps AS DESIRED Throttle CLOSE Mixture IDLE CUT-OFF Ignition OFF BATf MASTR Switch OFF ALTR Switch OFF Fuel Selector OFF Seat Belts and Harness TIGHT NOTE If batterymaster switch is OFF, the landing gear cannot be retracted. REPORT: VB.1612 ISSUED: JULY 12, 1995 3-4 HB-PQY, 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.lSb) In the event a gear up landing isrequired,proceed as follows: Flaps AS DESIRED Throttle CLOSE Mixture IDLE CUT-OFF Ignition OFF BATT MASTR Switch OFF ALTR Switch OFF Fuel Selector OFF Seat Belt and Harness TIGHT Contact surfaceatminimum possibleairspeed. 3.5e FIRE IN FLIGHT (3.17) Source of Fire CHECK ElectricalFire (Smoke in Cabin): BAiT MASTR Switch OFF ALTR Switch OFF Vents OPEN Cabin Heat OFF Land as soon as possible. Engine Fire: Fuel Selector OFF Throttle CLOSED Mixture IDLE CUT-OFF ElectricFuel Pump CHECK OFF Heater and Defroster OFF Proceed with power offlanding procedure (3.5d). NOTE The possibility of an engine fire in flight is 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 HB-PQY, 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 investigatecause. Prepare for power off landing. 3.5g LOSS OF FUEL FLOW/PRESSURE (3.21) ElectricFuel Pump ON Fuel Selector CHECK on tank containing fuel 3.5h HIGH OIL TEMPERATURE (3.23) Land at nearestairportand investigatethe problem. Prepare for power off landing. 3.51 ELECTRICAL FAILURE (3.25) ALT annunciator lightilluminated: Ammeter CHECK to VERIFY mop, alt. Ifammeter shows zero: ALTR Switch OFF Reduce electricalloads to minimum: ALTNTR. FIELD CircuitBreaker CHECK and RESET as required ALTR Switch ON Ifpower not restored: ALTR Switch OFF If alternator output cannot be restored, reduce electricalloads and land as soon as practical.The battery is the only remaining source of electricalpower. 3.5j ELECTRICAL OVERLOAD (Alternator over 20 amps above known electricalload) (3.27) BAT!’ MASTR Switch OFF REPORT: VB-1612 ISSUED: JULY 12, 1995 3-6 HB-PQY, 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 known electricalload) (3.27)(Continued) Ifammeter reading does NOT decrease; ALTR Switch OFF Land as soon as possible. Use Emergency Landing Gear Extension (3.5m) to lower landing gear. If ammeter reading DOES decrease: BATf MASTR Switch ON Ammeter MONITOR Ifammeter reading does NOT begin to decrease within five minutes: BATI’ MASTR Switch OFF Land as soon as possible. CAUTION If the battery is depleted,the landing gear must be lowered using the emergency extension procedure. The gear position lights will be inoperative. NOTh 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 electrical system failure. If ammeter reading DOES begin to decrease within fiveminutes: Proceed with flight. Ammeter .MONITOR 3.5k PROPELLER OVERSPEED (3.29) Throttle RETARD Oil Pressure CHECK ISSUED: JULY 12,1995 REPORT: VB-1612 1-., HB-PQY, Page: 3-7-(0) Issued: JULY 12, 1995 3-7 SECTION 3 EMERGENCY PROCEDURES PA-28R-201, ARROW 3.5k PROPELLER OVERSPEED (continued) PronellerControl FULL DECREASE rpm, then set ifany controlavailable. REDUCE Throttle AS REQUIRED to remain below 2700 rpm 3.Sm EMERGENCY LANDING GEAR EXTENSION (3.31) NOTE Refer to paragraph 4.39 for differences when emergency gear extension isbeing performed for trainingpurposes. Priorto emergency extension procedure: BAT!’ MASTR Switch CHECK ON ALTR Switch CHECK ON CircuitBreakers CHECK NAV LIGHT Switch OFF (indaytime) Gear IndicatorBulbs CHECK Iflanding gear does not check down and locked: Airspeed REDUCE BELOW 87 KIAS Landing Gear SelectorSwitch GEAR DOWN POSITION If gear has stillfailedto lock down, move and hold the emergency lever down to the Emergency Down position. If gear has stillfailedto lock down, yaw the airplaneabruptly from side to side with the rudder. If the nose gear willnot lock down using the above procedure, slow the aircraftto the lowest safespeed attainableusing the lowest power settingrequired forsafe operationand accomplish the following: Landing Gear SelectorSwitch GEAR DOWN PosmoN Iflanding gear does not check down, recycle gear through up position and then selectgear DOWN. REPORT: VB-1612 ISSUED: JULY 12, 1995 3.8 HB-PQY, Page: 3-8-(0) Issued: JULY 12, 1995 3-8 SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES 3.Sn SPIN RECOVERY (3.33) Rudder FULL OPPOSITE to DIRECT[ON of ROTATION Control Wheel FULL FORWARD WHILE NEUTRALIZING AILERONS Throttle IDLE Rudder NEUTRAL (when rotationstops) Control Wheel AS REQUIRED to SMOOTHLY REGAIN LEVEL FLIGHT AlTITUDE 3.5o OPEN DOOR (3.35) Ifboth upper and side latchesare open, the door will trailslightlyopen and airspeedswillbe reduced slightly. To close the door in flight: Slow airplaneto 87 KIAS. Cabin Vents Storm Window Ifupper latchisopen LATCH Ifside latchisopen PULL on ARMREST while moving Latch Handle to LATCH position If both latches are open LATCH SIDE LATCH then TOP LATCH 3.Sp ENGINE ROUGHNESS (3.37) Mixture ADJUST for maximum smoothness AlternateAir OPEN ElectricFuel Pump ON Fuel Selector SWITCH TANKS CICK .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 at the firstavailable airport. Ifroughness persists,prepare for a precautionary landing. ISSUED: JULY 12,1995 REPORT: VB-1612 20 HB-PQY, Page: 3-9-(0) Issued: JULY 12, 1995 3-9 SECTION 3 EMERGENCY PROCEDURES PA-28R-201, ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12,1995 3-10 HB-PQY, 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 pilot with a more complete understanding of the recommended course of action and probable cause of an emergency situation. 3.9 ENGINE FiRE DURING START (3.Sa) Engine firesduring startare usually the resultof overpriming. The first attempt to extinguish the tireis to try to startthe engine and draw the excess fuelback into the induction system. If a fire is present before the engine has started, move the mixture control to idle cut-off,open the throttleand crank the engine. This is an attempt to draw the fireback into the engine. If the engine has started,continue operating to try to pull the fireinto the engine. In eitherof the above cases,iffirecontinues for more than a few seconds, the fireshould be extinguished by the best availableexternalmeans. The fuel selectorvalves should be OFF and the mixture at idle cut-offif an externalfireextinguishingmethod isto be used. 3,11 ENGINE POWER LOSS DURING T4KEOFF (3.Sb) The proper action to be taken ifloss of power occurs during takeoffwill depend on the circumstances of the particularsituation. If sufficientrunway remains to complete a normal landing, leave the landing gear down and land straightahead. If the area ahead isrough, or ifitis necessary to clear obstructions,move the gear selectorswitch tothe UP position. If sufficientaltitudehas been gained to attempt a restart,maintain a safe airspeed and switch the fuel selector to a tank containing fuel. Place the electricfuel pump to ON. Check that the mixture is RICH. The alternateair should be open. ISSUED: JULY 12,1995 REPORT: VB-1612 3-il HB-PQY, Page: 3-11-(0) Issued: JULY 12, 1995 3-11 SECTION 3 EMERGENCY PROCEDURES PA-28R-201, ARROW .ii ENGINE POWER LOSS DURING TAKEOPF (35b) (continued) If engine failure was caused by fuel exhaustion, power will not be regained afterswitching fuel tanks untilthe empty fuellines are filled.This may requireup to ten seconds. If power is not regained, proceed with the Power Off Landing procedure (referto the emergency checklistand paragraph 3.15). 3.13 ENGINE POWER LOSS IN FLIGUT (3.Sc) Complete engine power loss is usually caused by fuel flow interruption and power will be restored shortly afterfuel flow is restored.If power loss occurs at a low altitude,the firststep isto prepare for an emergency landing (refer to paragraph 3.15). An airspeed of at least 79 KIAS should be maintained. If altitudepermits, switch.the fuel selector to another tank containing fueL and turn the electricfuel pump to ON. Move the mixture control to RICH and the alternate air 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 containing fuel. When power is restored move the alternateair to the CLOSED position and turnOFF the electricfuelpump. If the preceding steps do not restore power, prepare for an emergency landing. If time permits, turn the ignition switch to L, then to R, then back to BOTH. Move the throttleand mixture control levers to different settings. This may restorepower ifthe problem is too rich or too lean a mixture or if there isa partialfuel system restriction.Try the other fueltank. Water in the fuelcould take some time to be used up, and allowing the engine to windmill may restore power. If power loss is due to water, fuel flow/pressure indicationswillbe normal. REPORT: VB-1612 ISSUED: JULY 12, 1995 342 HB-PQY, Page: 3-12-(0) Issued: JULY 12, 1995 3-12 SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES 3.13 ENGINE POWER LOSS.IN RJGRT (3.Sc)(continued) If engine failure was caused by fuel exhaustion power will not be restored after switching fuel tanks until the empty fuel lines are filled.This may requireup to ten seconds. Ifpower is not regained, proceed with the Power Off Landing procedure (referto emergency checklistand paragraph 3.15).Trim for 79 KIAS. 3.15 POWER OFF LANDING (3.5d) If loss of power occurs at altitude,thin the aircraftfor best glidingangle (79 KIAS, air conditioner off)and look for a suitablefield.Ifmeasures taken to restorepower are not effective,and iftime permits, check your charts for airportsin the immediate vicinity;itmay be possible to land at one if you have sufficientaltitude.At best gliding angle, with the engine windmilling, and the propeller control in fullDECREASE rpm, the aircraftwill travel approximately 1.6 miles for each thousand feet of altitude.If possible,notify the FAA by radio of your difficulty and intentions. If another pilot or passenger isaboard, lethim help. When you have located a suitablefield,establisha spiralpatternaround thisfield.Try to be at 1000 feet above the fieldat the downwind position,to make a normal landing approach. When the field can easily be reached, slow to 72 KIAS with flaps down for the shortestlanding. Excess altitudemay be lostby widening your pattern,using flaps or slipping,or a combination of these. Whether to attempt a landing with gear up or down depends on many factors.If the 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 large obstacles in the field,the gear in the down position will betterprotect the occupants of the aircraft.If,however, the fieldis suspected to be excessively soft or short,.or when landing in water of any depth. a wheels-up landing willnormally be saferand do lessdamage tothe airplane. Touchdown should normally be made atthe lowest possibleairspeed. ISSUED: JULY 12, 1995 REPORT: VB-1612 3.13 HB-PQY, Page: 3-13-(0) Issued: JULY 12, 1995 3-13 SICE1ON 3 EMERGENCY PROCEDURES PA-28R-201, ARROW 3.15 POWER (WE LANDING (3.Sd)(continzzéd) 3.15a Gear Down Emergency Landing (3.Sd) When committed to a gear down emergency landing,selectlanding gear DOWN. Flaps may be used as desired.Close the throttlecontrol and move the mixture control to idle cut-off.Shut OFF the ignition,batterymaster (BATT MASTR), and alternator(ALTR) switches.Turn the fuelselectorvalve t OFE The seat belts and shoulder harness should he tightened.Touchdown should normally be made atthe lowest possibleairspeed. NOTh If the battery master switch is OFF the landing gear cannot be retracted. 3.15b 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 ignition,battery master (BATT MASTR), and alternator(ALTR) switches.Turn OFF the.fuelselectorvalve. Seat belts and shoulder harness should be tightened. Touchdown should normally be made atthe lowest possibleairspeed with fullflaps. REPORT: VB-1612 ISSUED: JULY 12, 1995 3-14 HB-PQY, Page: 3-14-(0) Issued: JULY 12, 1995 3-14 SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES 3.17 FIRE IN FLIGHT (3.Se) The presence of fireis noted through smoke, smell and heat in the cabin. It is essential that the source of the fire be promptly identified through instrument readings, character of the smoke, or other indications since the action tobe taken differssomewhat in each case. Check forthe source of the firefirst. If smoke in the cabin indicates an electricalfire,turn the batterymaster (BATT 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 as possible. Ifan engine fireis present,switch the fuel selectorto OFF and close the throttle.The mixture should be at idle cut-off.Turn the electricfuel pump OFF. In all cases, the heater and defroster should be OFF. If radio communication is not required select the battery master (BATI’ MASTR) and alternator (ALTR) switches OFF. If the terrain permits, a landing should be made immediately. NOTE The possibility of an engine fire in flight is extremely.remote. 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 oilpressure may be eitherpartialor complete. A partialloss of oil pressure usually indicates a malfunction in the oil pressure regulating system, and a landing should be made as soon as possible to investigatethe cause and prevent engine damage. A complete loss of oil pressure indicationmay signify oil exhaustion or may be the resultof a faultygauge. In eithercase, proceed toward the nearest airport,and be prepared for a forced landing.If the problem is not a pressure gauge malfunction, the engine may stop suddenly. Maintain altitudeuntil such time as a dead stick landing can be accomplished. Don’t change power settingsunnecessarily,as thismay hasten complete power loss. ISSUED: JULY 12,1995 REPORT: VB-1612 3-15 HB-PQY, 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 is stillavailable,particularlyifother indications of actual oil pressure loss,such as sudden increases in temperatures, or oil smoke, are apparent,and an airportisnot close. Ifengine stoppage occurs,proceed with Power Off Landing. 3.21 LOSS OF FUEL FLOWIPRESSURE (3.Sg) The most probable cause of loss of fuel flow/pressure is either fuel depletion in the fuel tank selected,or failureof the engine driven fuel pump. If loss,of fuel flow/pressure occurs, check thatthe fuel selectoris on a tank containing fueland turn ON the electricfuelpump. If the problem is not an empty tank, land as soon as practicaland have the engine driven fuel pump and fuel system checked. 3.23 K[GR OIL TEMPERATURE (3.5h) An abnormally high oil temperature indicationmay be caused by a low oil level,an obstructionin the oil cooler,damaged or improper baffleseals,a defective gauge, or other causes. Land as soon as practicalat an appropriate airportand have the cause investigated. A steady, rapid rise in oil temperature is a sign of trouble.Land at the nearest airport and let a mechanic investigate the problem. Watch the oil pressure gauge for an accompanying loss of pressure. 3.25 ELECTRICAL FAILURE (3.51) Loss of alternator output is detected through zero reading on the ammeter. Before executing the following procedure, ensure that the reading iszero, and not merely low, by actuatingan electrically powered device, such as the landing light.Ifno increase in the ammeter reading is noted, alternator failurecan be assumed. The electricalload should be reduced as much as possible.Check for an open alternatorfieldcircuitbreaker. Next, attempt to resetthe overvoltage relay by moving the ALTR switch to OFF for one second and then to ON. If the trouble was caused by a momentary overvoltage condition (16.5 volts and up) thisprocedure should return the ammeter to a normal reading. REPORT: VB-1612 ISSUED: JULY12, 1995 3-16 HB-PQY, Page: 3-16-(0) Issued: JULY 12, 1995 3-16 SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES 3.25 ELECTRICAL FAILURE (3.Si)(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 supplied by the battery. 3.27 ELECTRICAL OVERLOAD (Alternator over 20 amps above known electricalload) (3.5j) An abnormally high alternatoroutput may be caused by a low battery, batteryfault,or otherabnormal electricalload. Should an abnormally high alternator output be observed, turn the BATT MASTR (battery master) 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, after turning the BAU 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 BATT MASTR switch OFF and laud 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 BATE 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 after the BATT MASTR switch is turned ON, proceed with flight while continuing to monitor ammeter. ISSUED: JULY 12, 1995 REPORT: VB-1612 1.1’l HB-PQY, 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 is caused by a malfunction in the propellergovernor or low oilpressurewhich allows the propellerblades torotateto fulllow pitch. Ifpropeller overspeed should occur, retardthe throttleand check the oil pressure.The propellercontrol should be moved to fullDECREASE rpm and then set if any control is available.Airspeed should he reduced and throttle used to maintain 2700 rpm. 3.31 EMERGENCY LAM)ING GEAR EXTENSION (3.Sm) NOTE Refer to paragraph 4.39 for differences when emergency gear extension isbeing performed for trainingpurposes. Prior to initiatingthe emergency extension procedure, check to ensure that the battery master (BAIT MASTR) and alternator(ALTR) switches are ON, and that the circuitbreakers have not opened. if itis in daytime, the NAV LIGHT switch should be turned OFE Check the landing gear indicatorsfor faultybulbs. If the landing gear does not check down and locked, reduce the airspeed below 87 KIAS. Move the landing gear selectorswitch to the DOWN position. Ifthe gear has stillfailedto lock down, move and hold the emergency gear lever down to the EMERGENCY DOWN position. If the gear has stillfailedto lock down, yaw the airplaneabruptly from side to side with the rudder If the nose gear will not lock down using the above procedure, slow the airplane to the lowest safe speed attainable using the lçwest power setting required for safe operation.Move the landing gear selectárswitch to the gear DOWN position.if the landing gear does not check down, recycle the gear through the UP positionand then selectthe DOWN position. REPORT: YB-1612 ISSUED: JULY 12,1995 3-18 HB-PQY, Page: 3-18-(0) Issued: JULY 12, 1995 3-18 SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES 3.33 SPIN RECOVERY (33n) Intentionalspins are prohibited in thisairplane.If a spin isinadvertently entered, immediately apply fullrudder opposite to the direction of rotation. Move the control wheel full forward while neutralizing the 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 itsspringing open in flight at both the top and bottom are remote. However, should the upper latch be overlooked or the side latch not fullyengaged, the door may spring partially open. This will usually happen at takeoff or soon afterward. A partiallyopen door will not affect normal flightcharacteristics,and a normal landing can be made with the door open. If both upper and side latches are open, the door will trailslightlyopen, and airspeed will be reduced slightly. To close the door in flight,slow the airplaneto 87 KIAS, close the cabin vents and open the storm window. Ifthe top latch is open, latchit.If the side latch is open, pull on the armrest while moving the latch handle to the latched position.If both latches are open, close the side latch first,and then the top latch. 3.37 ENGINE ROUGHNESS (3.Sp) Engine roughness may be caused by dirt in the injector nozzles, induction system icing,or ignitionproblems. Firstadjust the mixture for maximum smoothness. The engine will run rough ifthe mixture is too rich or too lean. Move the alternateairto OPEN and then turn ON the electricfuel pump Switch the fuel selectorto another tank to see iffuel contamination isthe problem. Check the engine gauges for abnormal readings. If any gauge readings are abnormal proceed accordingly. ISSUED: JULY 12, 1995 REPORT: VB-1612 HB-PQY, Page: 3-19-(0) Issued: JULY 12, 1995 3-19 SECTION 3 EMERGENCY PROCEDURES PA-28R-201, ARROW 3.37 ENGINE ROUGHNESS (3.Sp) (Continued The magneto switch should then be moved L, then R, then back to• BOTH. If operation is satisfactory on 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. C) REPORT: VB-1612 ISSUED: JULY 12,1995 HB-PQY, 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 for Safe 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 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 HB-PQY, Page: 4-0-(1) Revision: 22, MAY 12, 2010 4-i SECTION 9 PA-28R-201, ARROW SUPPLEMENTS TABLE OF CONTENTS SECTION 4 NORIvIAL 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-il 4.5i Climb Checklist (4.25) 4-12 4.5j CruiseChecklist(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 HB-PQY, 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) Page No. 4.13a 4-18a 4.13b 4-19 4.13c 4-19 4.13d 4-19 4.15 4-20 4.17 4-20 4.19 4-21 4.21 4-22 4.23 4-22 4.23a 4-22 4.23b 4-22 4.25 4-23 4.27 4-23 4.29 4-25 4.31 4-25 4.33 4-26 4.37 4-26 4.37 4-27 Paragraph No. Normal Start Cold Engine (4.5c) Normal Start Hot Engine (4.5c) Engine StartWhen Flooded (4.5c) Engine StartWith External Power Source (4.5c) WARM-UP (4.5d) TAXIING (4.5e) GROUND CHECK (4.50 BEFORE TAKEOFF (4.5g) TAKEOFF (4.5h) Normal Technique (4.5h) Short Field,Obstacle Clearance And Soft Field Techniques (4.5h) CLIMB (4.5i) CRUISE(4.5j) APPROACH AND LANDING (4.5k) STOPPING ENGINE (4.5m) MOORING (4.5n) STALLS TURBULENT AIR OPERATION ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12, 2010 4-ill HB-PQY, 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 ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12, 2010 4-iv HB-PQY, 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 section provides the normal operating procedures for the PA-28R- 201, Arrow airplane.All of the normal operating procedures required by 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 features of the airplane,are presented. Normal operating procedures associated with optional systems and equipment which require handbook supplements are presented in Section 9, Supplements. These procedures are provided to supply information on procedures which are not the same for all airplanes and as a source of reference and review. Pilots should familiarize themselves with these procedures to become proficientin the normal operation of the airplane. This section is divided into two parts. The firstpart is a short form checklist supplying an action reaction sequence for normal procedures with littleemphasis on the operation of the systems. Numbers in parentheses aftereach checklist section indicate the paragraph where the corresponding amplified procedure can be found. The second part of this section contains the amplified normal procedures which provide detailed information and explanations of the procedures and how to perform them. This portion of the section is not intended for use as an inflightreference due to the lengthly explanation.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 ii HB-PQY, 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 significant to the safe operation of the airplane.These figures are for standard airplanesflown at gross weight under standard conditions at sea level. Performance for a specificairplane may vary from published figures depending upon the equipment installed, the condition of the engine, airplaneand equipment, atmospheric conditions and pilotingtechnique. (a) Best Rate of Climb Speed gear up, flapsup 90 KIAS gear down, flapsup 78 K[AS (b) Best Angle of Climb Speed gear up, flapsup 78 KIAS gear down, flapsup 72 KIAS (c) Turbulent Air Operating Speed (See Subsection 2.3) 118 KIAS (d) Maximum Flap Speed 103 KIAS (e) Landing Final Approach Speed (Flaps 400) 75 KIAS (t) Maximum Demonstrated Crosswind Velocity 17 KTS REPORT: VB-1612 ISSUED JULY 12, 1995 4.2 HB-PQY, Page: 4-2-(0) Issued: JULY 12, 1995 4-2 PA-28R-201, ARROW SECTION 4 NORMAL PROCEDURES 4.5 NORMAL PROCEDURES CHECKLIST 4.5a Preflight Checklist (4.9) CAUTION The flap position should be noted before boarding the airplane.The flaps must be placed in the UP position before they will lock and support weight on the step. COCKPIT (4.9a) Control Wheel releaserestraints Gear Handle DOWN Parking Brake SET Avionics OFF All Switches OFF Mixture IDLE CUT-OFF Magneto Switch OFF BATI’ MASTR Switch ON WALK-AROUND Figure 4-1 ISSUED: JULY 12, 1995 REPORT: VB-1612 4-3 HB-PQY, Page: 4-3-(0) Issued: JULY 12, 1995 4-3 SECTION 4 NORMAL PROCEDURES PA-28R-201, ARROW 4.5a Preflight Checklist (4.9)(continued) COCKPIT (4.9a)(continued) Fuel Gauges check QUANTITY Annunciator Panel 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) Surface Condition CLEAR of ICE, FROST, SNOW Flap and Hinges CHECK Aileron and Hinges CHECK StaticWicks CHECK SECURE Wing Tip and Lights CHECK Fuel Tank CHECK supply visually SECURE cap Fuel Tank Vent CLEAR CAUTION When draining any amount of fuel,care should be taken to ensure that no fire hazard exists before startingengine. Fuel Tank Sump DRAIN and CHECK for water,sediment, and proper fuel Tie Down and Chock REMOVE Main Gear Strut PROPER INFLATION (2.0+1- 0.25 in.) Tire CHECK Brake Block and Disc CHECK Fresh Air Inlet CLEAR REPORT: VB-1612 ISSUED: JULY 12, 1995 4-4 REVISED: MARCH 10, 2004 HB-PQY, Page: 4-4-(0) Revision: 10, MARCH 10, 2004 4-4 SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES 4.5a Preflight Checklist (continued) NOSE SECTION (4.9c) General Condition CHECK Cowling SECURE Oil CHECK QUANTITY Dipstick PROPERLY SEATED Oil FillerCap SECURE Engine Baffle Seals 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 draining any amount of fuel,care should be taken to ensure that no fire hazard exists before startingengine. Fuel Strainer DRAIN LEFT WING (4.9d) Surface Condition CLEAR of ICE,.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 0.25 in.)I Tire CHECK Brake Block and Disc CHECK Fuel Tank Vent CLEAR CAUTION When draining any amount of fuel,care should be taken to ensure that no fire hazard exists before startingengine. ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MARCH 10, 2004 4-5 HB-PQY, Page: 4-5-(0) Revision: 10, MARCH 10, 2004 4-5 SECTION 4 NORMAL PROCEDURES PA-28R-201, ARROW 4.5a Preflight Checklist (continued) LEFT WING (4.9d) (continued) Fuel Tank Sump DRAIN and CHECK for water,sediment, and proper fuel 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 BAIT MASTR Switch ON Cockpit Lighting CHECK Navigation and Strobe Lights CHECK Landing Light CHECK StallWarning CHECK PitotHeat CHECK All Switches OFF BAIT MASTR Switch OFF Passengers BOARD Cabin Door CLOSE and SECURE Seat Belts and Harness FASTEN CHECK inertiareel 4.5b Before Starting Engine 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 HB-PQY, 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 flightif there is no indication of 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 itwill take a few seconds longer to get a positiveoil pressure indication. 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 attempting additional starts. NORMAL START COLD ENGINE (4.13) Throttle 1/2 INCH OPEN ALTR Switch ON BAIT MASTR Switch ON ElectricFuel Pump ON Mixture RICH then IDLE 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 HB-PQY, 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 BATE 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) BAY MASTR Switch OFF ALTR Switch OFF All ElectricalEquipment OFF Terminals CONNECT External Power Plug INSERT in receptacle Proceed with normal start. Throttle LOWEST POSSIBLE RPM External Power 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 HB-PQY, 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 It is possible to use the ship’s battery in parallel by turning only the battery master switch ON. This will give longer cranking capabilities,but will not increase the amperage. Care should be exercised because if the ship’s battery has been depleted, the external power supply can be reduced to the level of the ship’s battery.This can be tested by turning only the battery master switch ON momentarily while the starter is 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 HB-PQY, Page: 4-9-(0) Revision: 22, MAY 12, 2010 4-9 SECTION 4 NORMAL PROCEDURES PA-28R-2Ol, ARROW 4.51 Ground Check Checklist (4.19) (continued) GROUND CHECK (4.19) (continued) Magnetos CHECK max. drop 175 RPM max. diff.50 RPM Vacuum 4.8 105.) inches Hg Oil Temperature CHECK Oil Pressure CHECK Ammeter CHECK Annunciator Panel PRESS-TO-TEST Propeller EXERCISE then FULL INCREASE Alternate Air CHECK Engine is warm for takeoff when 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) BA17 MASTR Switch ON ALTR Switch ON flight Instruments 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 Emergency Gear Extension Lever UP POSITION Controls FREE Doors LATCHED Air Conditioner OFF REPORT: VB-1612 ISSUED: JULY 12, 1995 4-10 REVISED: OCTOBER 31, 2012 HB-PQY, Page: 4-10-(0) Revision: 25, OCTOBER 31, 2012 4-10 SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES 4.5h Takeoff Checklist (4.23) NORMAL TECHNIQUE (4.23a) Flaps SET Trim SET Accelerate to 65 to 75 KIAS. Control Wheel back pressure to ROTATE smoothly to CLIMB ATTITUDE SHORT FIELD, OBSTACLE CLEARANCE TECHNIQUE (4.23b) Flaps 25° (second notch) Accelerate to 50 to 60 KIAS depending on aircraftweight. Control Wheel back pressure to ROTATE to CLIMB ATTITUDE After breaking ground, accelerateto 55 to 65 KIAS depending on aircraftweight. Gear UP Accelerate to best gear up angle of climb speed 78 KIAS, slowly retractthe flaps and climb past the obstacle. Accelerate to best gear up rate of climb speed 90 KIAS. SOFT FIELD TECHNIQUE (4.23b) Flaps 25° (second notch) Accelerate to 50 to 60 KIAS depending on aircraftweight. Control Wheel hack pressure to ROTATE to CLIMB ATTITUDE After breaking ground, accelerate to 55 to 65 KIAS depending on aircraftweight. Gear UP Accelerate to best gear up rate of climb speed 90 KIAS. Flaps RETRACT SLOWLY ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12, 2010 4-11 HB-PQY, 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) 90 KIAS 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) 72KIAS En Route 104 KIAS ElectricFuel Pump OFF at desired altitude 4.5j Cruise Checklist (4.27) CRUISE (4.27) Reference performance charts, Avco-Lycoming Operator’s 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 EREC1’ Belts/Harness FASTEN ElectricFuel Pump ON Mixture SET Propeller FULL INCREASE Emergency Gear Extension Lever UP POSITION Gear DOWN-l29KlASmax Flaps SET 103 KIAS max Air Conditioner OFF Trim to 75 KIAS REPORT: VB.1612 ISSUED: JULY 12, 1995 4-12 REVISED: OCTOBER 31, 2012 HB-PQY, Page: 4-12-(0) Revision: 25, OCTOBER 31, 2012 4-12 SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES 4.Sm Stopping Engine Checklist (4.31) STOPPiNG ENGINE (4.31) CAUTION The flaps must be placed in the UP position for the flap step to support weight. Passengers should be cautioned accordingly. 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 BAiT 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 IN PLACE Tie Downs SECURE ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12, 2010 4-13 HB-PQY, Page: 4-13-(0) Revision: 22, MAY 12, 2010 4-13 SECTION 4 NORMAL PROCEDURES PA-28R.201, ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12,1995 4-14 HB-PQY, 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 detailed information and explanations of the normal procedures necessary for the safe operation of the airplane. 4.9 PREFLIGHT CHECK (4.5a) The airplane should be given a thorough preflight and walk-around check. The preflight should include a check of the airplane’s operational status, computation of weight and C.G. limits, takeoff and landing distances,and in-flightperformance. A weather briefing should be obtained for the intended flightpath, and any other factors relating to 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 flaps must be placed in the UP position before they will lock and support weight on the step. Upon entering the cockpit, release the seat belts securing the control wheel. Check that the landing gear selectorhandle is in the DOWN position and set the parking brake. Ensure that allavionics and electricalswitches are OFF. Check thatthe mixture is in the idle cut-offand the magneto switch is OFF. Turn ON the battery master (BATT MASTR) switch; check the fuel quantity gauges for adequate supply and check that the annunciator panel illuminates.Turn OFF the battery master (BAiT MASTR) switch. Check the primary flightcontrols and flaps for proper operation and set the trim to neutral. Open the pitot and staticdrains to remove any moisture that has accumulated in the lines.Check the windows for cleanliness and that the required papers and POH are on board. Properly stow the tow bar and baggage and secure.Close and secure the baggage door. 4.9b Right Wing (4.Sa) Begin the walk-around at the trailingedge of the rightwing by checking thatthe wing surface and control surfaces are clear of ice frost,snow or other extraneous substances. Check the flap, aileron and hinges for damage and operationalinterference.Staticwicks should be firmly attached and in good condition.Check the wing tipand lightsfordamage. ISSUED: JULY 12,1995 REPORT: VE-1612 HB-PQY, 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 (4.5a)(continued) Open the fuel cap and visuallycheck the fuelcolor.The quantity should match the indicationthatwas on the fuel quantitygauge. Replace cap securely. The fueltank vent should be clear of obstructions. CAUTION When draining any amount of fuel,care should be taken to ensure that no fire hazard exists before startingengine. Drain a fuelsample from the fuel tank into a container,through the quick drain located at the lower inboard rear corner of the tank. Make sure that enough fuelhas been drained to ensure thatallwater and sediment isremoved; check for proper fuel.The fuelsystem should be drained daily priorto the first flightand aftereach refueling. Remove the tiedown and chock. Next, a complete check of the landing gear.Check the gear strutfor proper inflation,there should 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 the brake block and disc. Check thatthe fresh airinletisclear of foreign matter. 4.9c Nose Section (4.5a) Check the general condition of the nose sectionand check for oilor fluid leakage and thatthe cowling is secure. Check the oil level;make sure that the dipstickhas been properly seated and the oilcap properly secured. Check the engine baffleseals.Check the windshield and clean ifnecessary.The prbpeller and spinner should be checked for detrimentalnicks,cracks,or other defects. The air inletsshould be clearof obstructionsand check the alternatorbelt for proper tension.The landing lightshould be clean and intact Remove the chock and check the nose gear strutforproper inflation;there should be 2.75 +1- 0.25 inches of strutexposure under a normal staticload. Check the tirefor cuts,wear, and proper inflation. REPORT: VB-1612 ISSUED: JULY 12,1995 4.16 HB-PQY, 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) 4.9e Nose Section (4.5a) (continued) CAUTION When draining any amount of fuel, care should be taken to ensure that no fire hazard exists before startingengine. 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 surface should be clear of ice, frost,snow, or other extraneous substances. Check the stall warning vane for condition and freedom of movement. Open the fuel cap and visually check the fuel color.The quantity should match the indication that was on the fuel quantity gauge. Replace fuel cap securely. Check that the fresh air inlet is clear of foreign matter and remove the chock. Check the main gear strutfor proper inflation;there should be 2.0 ÷1- 0.25 inches of strut exposure under a normal staticload. Check the tirefor cuts, wear, aridproper inflation.Make a visual check 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 clear of obstructions.Drain enough fuel into a container to ensure that allwater 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 clear of obstructions. Check the wing tip and lightsfor damage Check the aileron,flap, and hinges for damage and operational interference and that the staticwicks are firmly attached and in good condition. 4.9e Fuselage (4.Sa) Check the condition and securityof the antennas and that the ports in the leftside staticpad are clear.The empennage should be clear of ice,frost,snow, or other extraneous substances. Check that the fresh airinleton the leftside of the fuselage is clear. Check the stabilator and trim tab for damage and operational interference;the trim tab should move in the same directionas the stabilator. Remove the tiedown. Check thatthe ports in the rightside staticpad are clear. ISSUED: JULY 12,1995 REPORT VB-1612 4-17 HB-PQY, 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 returning to the cockpit, an operational check of the interiorlights, exteriorlights,stallwarning system, and pitot heat should now be made. Turn the battery master switch and other appropriate switches ON. Check the panel lightingand the overhead flood light.Visually confirm that exteriorlightsare operational. Lift the stalldetector on the leading edge of the left wing and determine thatthe warning horn is activated.With the pitotheat switch ON the pilothead will be hot to the touch. After these checks are complete, the battery master (BAfl’ 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 function of the inertiareel by pulling sharply on the strap.Fasten seat beltson empty seats. ( REPORT: VB-1612 ISSUED: JULY 12, 1995 4-18 REVISED: MAY 12, 2010 HB-PQY, 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 attempt flightifthere is no indicationof alternator output. CAUTION: If a positiveoilpressure is not indicatedwithin 30 seconds following an engine start,stop the engine and determine the trouble. In cold weather it will take 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 start periods allowed. If start is not achieved on sixth attempt allow starterto cool for 30 minutes before attempting additional starts. 4.11 BEFORE STARTING ENGINE (4.Sb) Before startingthe engine, setthe parking brake ON. Check thatallcircuit breakers are in and that the alternateair is OFF. Move the propeller control to the fullINCREASE rpm position.Ensure that allavionics switches are OFF. Set the fuel selectorto the desired tank. 4.13 ENGINE START (4.5c) 4.13a Normal Start Cold Engine (4.5c) Open the throttlelever approximately 1/2 inch. Turn ON the alternatorand battery master switches, and the electricfuel pump. Move the mixture control to fullRICH untilan indicationis noted on the fuel flow meter. The engine is now primed. Move the mixture control to idle cut-off,check that the propeller area is clear,and engage the starterby rotatingthe magneto switch clockwise. When the engine fires,release the magneto switch, advance the mixture control to full RICH and move the throttleto the desired setting.Check the oilpressure. If the engine does not firewithin five to ten seconds, disengage the starter and reprime. ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: MAY 12, 2010 4-18a HB-PQY, Page: 4-18-(1) Revision: 22, MAY 12, 2010 4-18a SECTION 4 NORMAL PROCEDURES PA-28R-201, ARROW IHIS PAGE INtENtIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 4-l8b REVISED: MAY 12, 2010 HB-PQY, Page: 4-18-(2) Revision: 22, MAY 12, 2010 4-18b SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES 4.13 ENGINE START (4.Sc)(continued) 4.13b Normal Start Hot Engine (4.5c) Open the throttleapproximately 112 inch. Turn ON the alternator and batterymaster switches, and the electricfuel pump. The mixture control lever should be in idle cut-off.Check that the propeller area is clear,and engage the starterby rotating the magneto switch clockwise. When the engine fires, release the magneto switch, advance the mixture, and move the throttleto the desired setting.Check the oilpressure. 4.13c Engine Start When Flooded (4.5c) The throttlelever should he fullOPEN. Turn ON the alternatorand battery master switches, and turn OFF the emergency fuel pump. The mixture control lever should be in idle cut-off. Check that the propeller area is clear, and engage the starterby rotatingthe magneto switch clockwise. When the engine fires.release the magneto switch, advance the mixture, and retard the 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 operator to use an external battery to crank the engine without having to gain access to the airplane’sbattery. Turn OFF the alternator switch, the battery master switch,-and all electricalequipment. Connect the RED lead of the PEP kitjumper cable to the POSiTiVE (-i.)terminal of an external 12-volt battery and the BLACK lead to the NEGAflVE (-)terminal. Insertthe plug of the jumper cable into the 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 possible rpm and disconnect the jumper cable from the aircraft.Turn the alternatorand battery master switches ON. Check the alternatorammeter for an indicationof output. DONOT ATTEMPT FLIGHT IF THERE IS NO INDICATION OF ALTERNATOR OUTPUT CAUTION It is possible to use the ship’sbattery in parallel by turning only the battery master switch ON. This will give longer cranking capabilities,but will not increase the amperage. Care should be exercised because if the ship s b