Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual

Deleted info. Moved text from 7-32 ...\"~~I04Moved text to 7-31. Revised para 8.15. D. H. Trompler Revised para 8.19. Revised para 8.21b. Allr. 26,1920 Correct footer Date Added Revision 5 to Log of Revisions Revised para 2.9 Revised para 3.5m Revised para 3.15b Revised para 3.31 Revised para 5.5 (a) Revised para 5.5 (e, f, & g) Added Page & Fig. 5-1a Revised Fig. 5-23 Added Page & Fig. 5-23a Revised Fig. 5-25 Added Page & Fig. 5-25a ISSUED: SEPTEMBER 15, 1988 REVISED: MAY 8, 1995 ( ( ( Rev. 5 (Cont’d) 5-25b Added Page & Fig. 5-25b. 5-26 Revised Fig. 5-27. 5-26a Added Page & Fig. 5-27a. 5-26b Added Page & Fig. 5-27b. 5-26c Added Page & Fig. 5-27c. 5-27 Revised Fig. 5-29. 5-27a Added Page & Fig. 5-29a. 5-27b Added Page & Revised Fig. 5-31. 5-28 Added Fig. 5-31a. 5-29 Revised Fig. 5-33. 5-29a Added Page & Fig. 5-33a. 5-29b Added Page & Fig. 5-33b. Peter E. Peck 5-29c Added Page & Fig. 5-33c. 9-7 Revised Title Page May 8, 1995 9-25 Revised Para. (d) Date Rev. 6 vi-a Added Revision 6 to Log (PR950518) of Revisions. Peter E. Peck vi Corrected Errors on Log vi-a of Revisions pages vi & vi-a. May 18, 1995 Date Rev. 7 iii Added Warning and moved (PR040607) info. to page iv. iv Moved info. from page iii. vi-a Added Rev. 7 to L of R. vi-b Added Rev. 7 to L of R. 7-21 Revised Fig. 7-21 callouts. 8-1 Moved info. to page 8-1b and revised para. 8.1. 8-1a Added page and revised para. 8.1. Revision FAA Approval Number and Revised Description of Revisions Signature Code Pages and Date pilot’s operating handbook log of revisions (cont) piper airCraft Corporation pa-28r-201, arroW issUed: septeMber 15, 1988 report: vb-1365 vi-a revised: jUne 7, 2004 Rev. 7 8-1b Added page and moved info. (PR040607) from pages 8-1 and 8-2. (continued) 8-2 Moved info. to page 8-1b Albert J. Mill and revised para. 8.3. June 7, 2004 Date Rev. 8 vi-b Added Rev. 8 to L of R. (PR050912) 2-5 Revised para. 2.15. Linda J. Dicken Sept. 12, 2005 Rev. 9 vi-b Added Rev. 9 to L of R. (PR060424) 4-4 Revised para. 4.5a. Linda J. Dicken 4-5 Revised para. 4.5a. April 24, 2006 Rev. 10 vi-b Added Rev. 10 to L of R. (PR090510) 4-9 Revised para. 4.5f. 4-20 Removed text and added note to para. 4.13d. Moved text from Para. 4.17 to pg. 4-21. 4-21 Added text to Para. 4.17 from pg. 4-20. Changed text in Para. 4.19. 7-18 Revised text in Para. 7.19. Albert J. Mill 8-1b Revised text in Para. 8.1. May 10, 2009 Rev. 11 ii Added copyright. (PR121031) vi-b Added Rev. 11 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 Revision FAA Approval Number and Revised Description of Revisions Signature Code Pages and Date pilot’s operating handbook log of revisions (cont) piper airCraft Corporation pa-28r-201, arroW report: vb-1365 issUed: septeMber 15, 1988 vi-b revised: oCtober 31, 2012 PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW SECTION 1 SECTION 2 SECTION 3 SECTION 4 SECTION 5 SECTION 6 SECTION 7 SECTION 8 SECTION 9 SECTJON 10 TABLE OF CONTENTS GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT AND BALANCE DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS AIRPLANE HANDLING, SERVICING AND MAINTENANCE SUPPLEMENTS OPERATING TIPS ISSUED: SEPTEMBER 15, 1988 REPORT: VB-1365 vii PIPER AIRCRAFT CORPORATION SECTION 1 PA-28R-201, ARROW EMERGENCY PROCEDURES Paragraph No. TABLE OF CONTENTS SECTION 1 GENERAL Page No. !.I Introduction ...................................... I-I 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 Baggage Space.................... ................ 1-5 1.17 Specific Loadings ............................. , .... 1-5 1.19 Symbols, Abbreviations and Terminology. . . . . . . . . . . . . 1-6 ISSUED: SEPTEMBER 15, 1988 REPORT: VB-1365 l-i PIPER AIRCRAF:r CORPORATION PA-18R-201, ARROW SECTION I GENERAL 1.1 INTRODUCTION SECTION 1 GENERAL This Pilot's Operating 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 flight instruction, knowledge of current airworthiness directives, applicable federal air regulations or advisory circulars. It is not intended to be a guide for basic flight instruction or a training manual 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 opemting limitations as outlined by instrument markings, placards, and this handbook. Although the arrangement of this handbook is intended to increase its in-flight capabilities, it should not be used solely as an occasional opemting reference. The pilot should study the entire handbook to familiarize himself with the limitations, performance, procedures and operational handling characteristics of the airplane before flight. The handbook has been divided into numbered (arabic) sections, each provided with a finger-tip tab 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 certain paragraph numbers, figure numbers, item numbers and pages noted as being intentionally left blank. ISSUED: SEPTEMBER 15,1988 REPORT: VB-1365 1-1 SECTION 1 GENERAL S· 3.00- PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW Wing Area (sq. ft.) 170.0 Min. Turning Radius (ft) (from pivot point to wing tip) 31.0 " .." "I ~<=?-<..t_ G 0·· 1-10· 5.64----1 REPORT: VB-136S 1-2 THREE VIEW Figure I-I ISSUED: SEPTEMBER 15,1988 ( ( ( PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW 1.3 ENGINES (a) Number of Engines (b) Engine Manufacturer (c) Engine Model Number (d) Rated Horsepower (e) Rated Speed (rpm) (f) Bore (in.) (g) Stroke (in.) (h) Displacement (cu. in.) (i) Compression Ratio G> Engine Type I.S PROPELLERS McCAULEY (a) Number of Propellers (b) Propeller Manufacturer (c) Blade Model (d) Number of Blades (e) Hub Model (f) Propeller Diameter (in.) (I) Maximum (2) Minimum (g) Propeller Type ISSUED: SEPTEMBER IS, 1988 SECTION I GENERAL Lycoming IO-360-C IC6 200 2700 5.125 4.375 361 8.7:1 Four Cylinder, Direct Drive, Horizontally Opposed, Air Cooled and Fuel Injected McCauley 90DHA-16 2 B2D34C213 74 73 Constant Speed, Hydraulically Actuated REPORT: VB-136S 1-3 SECTION i GENERAL 1.5 PROPELLERS (continued) HARTZELL (a) Number of Propellers (b) Propeller Manufacturer (c) Blade Model (d) Number of Blades (e) Hub Model (f) Propeller Diameter (in.) ( I) Maximum (2) Minimum (g) Propeller Type 1.7 FlJEL PIPER AIRCRAFT CORPORATION 'PA-28R-201, ARROW Hartzell F7666A-2R 2 HC-C2YK-I( )F/ 74 72 Constant Speed. Hydraulically Actuated (a) Fuel Cupacity (U.S. gal.) (total) 77 (b) Usable Fuel (U.S. gal.) (total) ( c) Fuel Grade. Aviation (I) Minimum Octane (2) Alternate Fuels 1.9 OIL (a) Oil Capacity (U.S. qts.) (0) Oil Specification (c) Oil Viscosity REPORT: VB-1365 1-4 72 100/130 - Green or 100 LL - Blue Aviation Grade Refer to la test revision of Lycoming Service Instruction 1070, except alcohol is not approved for use in this airplane. MIL-I-27686D is approved. 8 Refer to latest issue of Lycoming Service Instruction 1014 Refer to Section 8 - paragraph 8.19 ISSUED: SEPTEMBER 15, 1988 ( ( ( PIPER AIRCRAFT ('OR PO RATION PA-28R-201, ARROW 1.11 MAXIMUM WEIGHTS (a) Maximum Takeoff Weight (lb.) (b) Maximum Landing Weight (lb.) (c) Maximum Weights in Baggage Compartment 1.13 STANDARD AIRPLANE WEIGHTS'" (a) Standard Empty Weight (lb.): Weight of a standard airplane including unusable fuel. full operating fluids and full oil. (b) Maximum Useful Load (lb.): The difference between the Maximum Takeoff Weight and the Standard Empty Weight. 1.15 BAGGAGE SPACE (a) Compartment Volume (cu. ft.) (b) Entry Width (in.) (c) Entry Height (in.) 1.17 SPECIFIC LOADINGS (a) Wing Loading (lb. per sq. ft.) (b) Power Loading (lb. per hp) SECTION I (a~NlmAL 2750 2750 200 1603 1147 24 22 20 16.18 13.75 "'These values are approximate and vary from one aircraft to another. Refer to Figure 6-5 for the Standard Empty Weight value and the Useful Load value to be used for e.G. calculations for the aircraft specified. ISSUED: SEPTEMBER 15, 1988 REPORT: VB-J365 1-5 SECTION I GENERAL PIPER AIRCRAFT CORPORATION 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 significance to the pilot. (a) General Airspeed Terminology and Symbols CAS KCAS GS lAS KIAS M TAS VA VFE REPORT: VB-1365 1-6 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 at sea level. Calibrated Airspeed expressed in Knots. Ground Speed is the speed of an airplane relative to the ground. Indicated Airspeed is the speed of an air- craft as shown on the airspeed indicator when corrected for instrument error. lAS values published in this handbook assume zero instrument error. Indicated Airspeed expressed in Knots. Mach Number is the ratio of true airspeed to the speed of sound. True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude, temperature and compressibility. Maneuvering Speed is the maximum speed at which application of full available aerod ynamic control will not overstress the airplane. Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. ISSlJED: SEPTEMBER 15, 1988 ( ( PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW SECTION 1 GENERAt 1.19 SYMBOLS, ABBREVIATIONS, AND TERMINOLOGY (continued) VLE VLO VNE/MNE VNO Vs VSO Vx Vy Maximum Landing Gear Extended Speed is the maximum speed at which an aircraft can be safely flown with the landing gear extended. Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safely extended or retracted. Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time. Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution. Stalling Speed or the minimum steady flight speed at which the airplane is con- trollable. Stalling Speed or the minimum steady flight speed at which the airplane is con- trollable in the landing configuration. Best Angle-of-C1imb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance. Best Rate-or-Climb Speed is the airspeed which.delivers the greatest gain in altitude in the shortest possible time. ISSUED: SEPTEMBER IS, 1988 REPORT: VB-136S 1-7 SECTION I GENERAL PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW 1.19 SYMBOLS, ABBREVIATIONS, AND TERMINOLOGY (continued) (b) Meteorological Terminology ( ISA OAT Indicated Pressure Altitude Pressure Altitude Station Pressure Wind REPORT: VB-1365 1-8 International Standard Atmosphere In which: (I) The air is a dry perfect gas. (2) The temperature at sea level is 15° Celsi- us (590 Fahrenheit). . (3) The pressure at sea level is 29.92 inches Hg (1013.2mb). (4) The temperature gradient from sea level to the altitude at which the temperature is -56.5°C (-69.7°F) is 0.00198°C (-0.003564° F) per foot and zero above that altitude. Outside Air Temperature is the free air static temperature, obtained either from inflight temperature indications or ground meteorological sources, adjusted for in- ( strument error and compressibility effects. The number actually read from an altimeter when the barometric subscale has been set to 29.92 inches of mercury (1013.2 millibars). Altitude measured from standard sea-level pressure (29.92 in. H g) by a pressure or barometric altimeter. It is the indicated pressure altitude corrected for position and instrument error. In this handbook, altimeter instrument errors are assumed to be zero. Actual atmospheric pressure at field elevation. The wind velocities recorded as variables ( on the charts of this handbook are to be understood as the headwind or tailwind components of the reported winds. ISSUED: SEPTEMBER 15, 1988 PIPER AIRCRAFT CORPORATION PA·28R·201, ARROW SECTION I GENERAL 1.19 SYMBOl,S, ABBREVIATIONS, AND TERMINOLOGY (continued) (c) (d) (e) 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. Engine Instruments EGT Gauge Exhaust Gas Temperature Gauge Airplane Performance and Flight Planning Terminology Climb Gradient Demonstrated Crosswind Velocity Accelerate-Stop Distance MEA Route Segment The demonstrated ratio of the change in height during a portion of a climb. to the horizontal distance traversed in the same time interval. The demonstrated crosswind velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests. Tbe distance required to accelerate an air- plane to a specified speed and. assuming fai lure of an engine at the instantthat speed is attained. to bring the airplane to a stop. Minimum en route IFR altitude. A part of a route. Each end of that pa rt is identified by: (I) a geographical location; or (2) a point at which a definite radio fix can be established. ISSUED: SEPTEMBER 15, 1988 REPORT: V8-1365 1-9 SECTION I GENERAL PIPER AIRCRAFT CORPORATION ·PA·28R-20., ARROW 1.19 SYMBOLS, ABBREVIATIONS, AND TERMINOLOGY (continued) (f) Weight and Balance Terminology ( Reference Datum Station Arm Moment Center of Gravity (CG.) C.G. Arm c.G. Limits Usable Fuel Unusable Fuel Standard Empty Weight REPORT: VB-1365 1-10 An imaginary vertical plane from which all horizontal distances are measured for balance purposes. A location along the airplane fuselage usually given in terms of distance from the reference datum. The horizontal distance from the reference datum to the center of gravity (C.G.) of an item. The product of the weight of an item multi- plied by its arm. (Moment divided by a constant is used to simplify balance calcu- lations by reducing the number of digits.) The point at which an airplane would ( balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. The arm obtained by adding the airplane'S individual moments and dividing the sum by the total weight. The extreme center of gravity locations within which the airplane must be operated at a given weight. Fuel available for flight planning. Fuel remaining after a runout test has been completed in accordance with govern- mental regulations. ( Weight of a standard airplane including unusable fuel, full operating fluids and full oil. ISSUED: SEPTEMBER 15, 1988 PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW SECTION 1 GENERAL 1.19 SYMBOLS, ABBREVIATIONS, AND TERMINOLOGY (continued) Basic Empty Weight Payload Useful Load Maximum Ramp Weight Maximum Takeoff Weight Maximum Landing Weight Maximum Zero Fuel Weight Standard empty weight plus optional equipment. Weight of occupants. cargo and baggage. Difference between takeoff weight. or ramp weight if applicable. and basic empty weight. Maximum weight approved for ground maneuver. (It includes weight of start. taxi and run up fuel.) Maximum weight approved for the start of the takeoff run. Maximum weight approved for the landing touchdown. Maximum weight exclusive of usable fuel. ISSUED: SEPTEMBER 15, 1988 REPORT: VB-1365 1-11 SECTION I GENERAL PIPER AIRCRAFT CORPORATION PA-28R-20I, ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1365 1-12 ISSUED: SEPTEMBER IS, 1988 ( ( PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW SECTION 2 LIMITATIONS TABLE OF CONTENTS SECTION 2 LIMIT ATIONS Paragraph No. 2.1 2.3 2.5 2.7 2.9 2.11 2.13 2.15 2.17 2.19 2.21 2.23 General Airspeed Limitations .............................. . Airspeed Indicator Markings ....................... . Power Plant Limitations ..........•................. Power Plant Instrument Markings .................. . Weight Limits .................................... . Center of Gravity Limits ........................... . Maneuver Limits ................................. . Flight Load Factors ............................... . Types of Operations .............................. . Fuel Limitations .................................. . Placards ......................................... . Page No. 2-1 2-\ 2-2 2-3 2-4 2-5 2-5 2-5 2-6 2-6 2-6 2-8 ISSUED: SEPTEMBER 15, 1988 REPORT: VB-1365 2-j PIPER AIRCRAFT CORPORATION PA-28R-20t, ARROW SECTION 2 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 airplane and its systems. Limitations associated with those optional systems and equipment which require handbook supplements can be found in Section 9 (Supplements). 2.3 AIRSPEED UMIT ATIONS SPEED Never Exceed Speed (VNE) - Do not exceed this speed in any operation. Maximum Structural Cruising Speed (VNO) - Do not exceed this speed except in smooth air and then only with caution. Design Maneuvering Speed (V A) - Do not make full or abrupt control movements above this speed. At 2750 Ibs. G.W. At 1865 lbs. G.W. CAUTION KlAS 183 146 118 96 Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced. Linear interpolation may be used for intermediate gross weights. Maneuvering speed should not be exceeded while operating in rough air. KCAS 186 148 120 96 ISSUED: SEPTEMBER 15, 1988 REPORT: VB-1365 2-1 SECTION 2 LIMITATIONS PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW 2.3 AIRSPEED UMIT ATIONS (continued) SPEED KIAS KCAS Maximum Flaps Extended Speed (VFE) - Do not exceed this speed with the flaps extended. 103 103 Maximum Landing Gear Extension Speed - Do not exceed this speed when extending the landing gear. 129 130 Maximum Landing Gear Retraction Speed - Do not exceed this speed when retracting the landing gear. 107 \07 Maximum Landing Gear Extended Speed (VLE) - Do not exceed this speed 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 KTS White Arc (Flap Down) SS KTS to 103 KTS REPORT: VB-B65 2-2 ISSlJED: SEPTEMBER 15,1988 ( ( ( PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW 2.7 POWER PLANT LIMITATIONS (a) Number of Engines (b) Engine Manufacturer (c) Engine Model No. (d) Engine Operating Limits (1) Maximum Horsepower (2) Maximum Rotation Speed (RPM) (3) Maximum Oil Temperature (e) Oil Pressure Minimum (red line) Maximum (red line) (t) Fuel Flow/Pressure Maximum (red line) (g) Fuel Grade (minimum octane) (h) Number of Propellers (i) Propeller Manufacturer (j) Propeller Hub and Blade Model (1) McCauley (2) Hartzell (k) Propeller Diameter (1) McCauley Minimum Maximum (2) Hartzell Minimum Maximum (1) Blade Angle Limits (1) McCauley Low Pitch Stop High Pitch Stop (2) Hartzell Low Pitch Stop High Pitch Stop (m) RPM Restriction (McCauley Propeller Only) ISSUED: SEPTEMBER 15, 1988 SECTION 2 LIMITATIONS 1 Lycoming IO-360-CIC6 200 2700 245°F 25 PSI 100 PSI 21.4 GPHl12 PSI 100 or 100LL Aviation Grade 1 McCauley or Hartzell B2D34C213/90DHA-16 HC-C2YK-l( )FI F7666A-2R 73 74 72 74 12.5 + 0.2° 27.5 + 0.5° 14.0 + 0.2° 29.0+ 2.0° Avoid continuous operation between 1500 and 1950 rpm below 15 inches manifold pressure. REPORT: VB-1365 2-3 SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA-28R-201, ARROW 2.9 POWER PLANT INSTRUMENT MARKINGS (a) Tachometer Green Arc (Normal Operating Range) 500 to 2700 RPM Red Line (Maximum Continuous Power) 2700 RPM (b) Oil Temperature Green Arc (Normal Operating Range 75° to 245°F Red Line (Maximum) 245°F (c) Oil Pressure Green Arc (Normal Operating Range 60 PSI to 90 PSI Yellow Arc (Caution Range) (Idle) 25 PSI to 60 PSI Yellow Arc (Caution Range) (Start and 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 GPHlO.05 PSI to 21.3 GPHl12 PSI Red Line (Maximum) 21.3 GPHl12 PSI REPORT: VB-1365 2-4 ISSUED: SEPTEMBER 15, 1988 REVISED: MAY 8, 1995 ( ( PIPER AIRCRAFT CORPORATION PA.28R.201, ARROW SECTION 2 LIMITATIONS 2.11 WEIGHT LIMITS (a) Maximum Weight (b) Maximum Baggage NOTE Refer to Section 5 (Performance) for maximum weight as limited by performance. 2.13 CENTER OF GRAVITY LIMITS 2750 LBS. 200LBS. Weight Pounds Forward Limit Inches Aft of Datum Rearward Limit Inches Aft of Datum 2750 2375 and Below 88.9 82.0 NOTES Straight line variation between points given. 91.5 91.5 The datum used is 78.4 inches ahead of the wing leading edge at the intersection of the straight and 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: SEPTEMBER 15, 1988 REVISED: SEPTEMBER 12, 2005 REPORT: VB·1365 2·5 SECTION 2 LIMITATIONS 2.17 FLIGHT LOAD FACTORS PIPER AIRCRAFT CORPORATION PA·28R·201, ARROW (a) Positive Load Factor (Maximum) (b) Negative Load Factor (Maximum) 3.8 G 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 VF.R. (b) Night VF.R. (c) Day LF.R. (d) Night LF.R. (e) Non Icing 2.21 FUEL LIMITATIONS (a) Total Capacity (b) Unusable Fuel The unusable fuel for this airplane has been determined as 2.5 gallons in each wing tank in critical flight attitudes. (c) Usable Fuel The usable fuel in this airplane has been determined as 36.0 gallons in each wing tank. (d) Fuel remaining when the quantity indi- cators read zero cannot be used safely in flight. 77 U.S. GAL. S U.S. GAL. 72 U.S. GAL. REPORT: VB·1365 2·6 ISSUED: SEPTEMBER 15, 1988 ( PIPER AIRCRAFT CORPORATION PA-28R-lOl, ARROW 2.23 PLACARDS In full view of the pilot: SECTION 2 LIMITATIONS THIS AIRPLANE MUST BE OPERATED AS A NOR- MAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS. MARKINGS AND MANUALS. THIS AIRCRAFT APPROVED FOR NIGHT I.F.R. NON-ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 91 OR FAR 135. In full view of the pilot. the following Takeoff and Landing Checklists will be installed: TAKEOFF CHECKLIST Fuel on Proper Tank Electric Fuel Pump On Engine Gauges Checked Alternate Air Closed Seat Backs Erect Mixture Set Propeller Set Fasten Belts/ Harness Flaps Set Trim Tab Set Controls Free Doors Latched Air Conditioner Off LANDING CHECKLIST Fuel on Proper Tank Seat Backs Erect Fasten Belts/ Harness Electric Fuel Pump On Mixture Rich Propeller Set Gear Down Flaps Set (White Arc) Air Conditioner Off The Air Conditioner Off it.:m in the above Takeoff and Landing Checklists is mandatory for air c,mditioned aircraft only. ISSUED: SEPTEMBER 15, 1988 REPORT: VB-I365 2-7 Sf:CTlON 2 UMITATIONS 2.23 PLACARDS (continued) PIPER AIRCRAFT CORPORATION PA·28R·201. ARROW On the instrument panel in full view of the pilot: MANEUVERING SPEED 118 KIAS AT 2750 LBS. (SEE P.O. H.) On the instrument panel in full view of the pilot: DEMONSTRATED CROSSWIND COMPONENT 17 KTS On the instrument panel in full view of the pilot: NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED On the instrument panel in full view of the pilot: GEAR DOWN GEAR UP EXTENDED Near emergency gear lever: 129 KIAS (MAX.) 107 KIAS (MAX.) 129 KIAS (MAX.) EMERGENCY DOWN Near gear selector switch: GEAR UP DOWN 107 KIAS MAX. 129 KIAS MAX. Adjacent to upper door latch (front and rear doors): ENGAGE LATCH BEFORE FLIGHT On the instrument panel in full view of the pilot: WARNING TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY TO GROUND OR DURING FLIGHT THROUGH CLOUD, FOG OR HAZE. REPORT: VD·136S 2-8 ISSUED: SEPTEMBER IS. 1988 ( ( ( PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW 2.23 PLACARDS (continued) SECTION 2 LIMITATIONS In full view of the pilot. in the area of the air conditioner controls when the air conditioner is installed: WARNING AIR CONDITIONER MUST BE OFF TO INSURE NORMAL TAKEOFF CLIMB PERFORMANCE. On inside of baggage compartment door: BAGGAGE MAXIMUM 200 LBS. SEE WEIGHT AND BALANCE DATA FOR BAGGAGE LOADING BE- TWEEN 150 LBS. AND 200 LBS. Adjacent to fuel tank filler caps: AVGAS ONLY "GRADE 100LL Above fuel quantity gauges: GRADE 100 FUEL REMAINING WHEN QUANTITY INDICATOR READS ZERO CANNOT BE USED SAFELY IN FLIGHT. ISSUED: SEPTEMBER 15, 1988 REPORT: VB-136S 2-9 SECTION 2 LIMITATIONS 2.23 PLACARDS (<<;ontinued) PIPER AIRCRAFT CORPORATION .PA.28R-201, ARROW On the instrument panel in full view of the pilot in aircraft with McCauley ( propeller installations only: AVOID CONTINUOUS OPERATION BETWEEN 1500 AND 1950 RPM BELOW 15" MANIFOLD PRESSURE. On the aft baggage closeout: MAXIMUM BAGGAGE 200 LBS. NO HEAVY OBJECTS ON HAT SHELF. In full view of pilot: IREPORT: VB·1365 2-10 CAUTION COMPASS CAL. MAY BE IN ERROR WITHELECf. EQUIPMENT OTHER THAN AVIONICS ON ISSUED: SEPTEMBER 15, 1988 REVISED: APRIL 9, 1990 ( PIPER AIRCRAFT CORPORATION SECTION 3 PA-18R-10l, ARROW EMERGENCY PROCEDURES T ABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph No. 3.1 3.3 3.5 3.5a 3.5b 3.5c 3.5d 3.5e 3.5f 3.5g 3.5h 3.5i 3.5j 3.5k 3.5m 3.5n 3.50 3.5p General Airspeeds For Safe Operation ...................... . Emergency Procedures Checklist .................... . Engine Fire During Start (3.9) ..................... . Engine Power Loss During Takeoff (3.11) .......... . Engine Power Loss In Flight (3.13) ................ . Power Off Landing (3.15) ..................... ".... . Gear Down Emergency Landing (3.15a) ........... . Gear Up Emergency Landing (3.15b) .............. . Fire In Flight (3.17) .............................. . Loss Of Oil Pressure (3.19) ....................... . Loss Of Fuel Flow! Pressure (3.21) ................. . High Oil Temperature (3.23) ...................... . Electrical Failure (3.25) ........................... . . Electrical Overload (3.27) ......................... . Propeller Overspeed (3.29) ........................ . Emergency Landing Gear Extension (3.31) .......... . Spin Recovery (3.33) ............................. . Open Door (3.35) ................................ . Engine Roughness (3.37) .......................... . Page No. 3-1 3-2 3-3 3-3 3-3 3-3 3-4 3-4 3-5 3-5 3-6 3-6 3-6 3-6 3-6 3-7 3-8 3-9 3-9 3-9 ISSUED: SEPTEMBER IS, 1988 REPORT: VB-136S 3-i SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28R-201, ARROW Paragraph No. TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES (cont) Page No. 3.7 Amplified Emergency Procedures (General) ............ 3-11 3.9 Engine Fire During Start (3.5a).. .................... 3-11 3.11 3.13 3.15 3.15a 3.15b 3.17 Engine Power Loss During Takeoff (3.5b) ........... . Engine Power Loss In Flight (3.5c) ................. . Power Off Landing (3.5d) ......................... .. Gear Down Emergency Landing (3.5d) .•............ Gear Up Emergency Landing (3.5d) ................ . Fire In Flight (3.5e) ............................... . 3-11 3-12 3-13 3-14 3-14 3-15 3.19 Loss of Oil Pressure (3.5f) .......................... 3-15 3.21 Loss of Fuel Flow/ Pressure (3.5g) .. ...... ... .•... ... 3-16 3.23 High Oil Temperature (3.5h) . . . . . . . . . . . . . . . . . . . • • . . . 3-16 3.25 Electrical Failurt: (3.5i) . . . .. . . . . . . . . . . . . . . . . . . . . . . . . 3-16 3.27 3.29 3.3\ 3.33 3.35 3.37 Electrical Overload (3.5j) .......................... . Propeller Overspeed (3.5k) ........................ .. Emergency Landing Gear Extension (3.5m) .......... . Spin Recovery(3.5n) •.............................. Open Door (3.50) ................................. . Engine Roughness (3.5p) •.•..•..••................. 3-17 3-18 3-18 3-19 3-19 3-19 REPORT: VB-136S 3-11 ISSUED: SEPTEMBER IS, 1988 ( ( PIPER AIRCRAFT CORPORATION SECTION 3 PA-18R-10l, ARROW EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES 3.1 GENERAL This section provides the recommended procedures for coping with various emergency or critical situations. All of the emergency procedures required by the FAA as well as those necessary for operation oftheairplane. 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 first part contains the emergency procedures checklists. These checklists supply an immediate action sequence to be followed during critical situations with little emphasis on the operation of systems. The numbers located in parentheses after each 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 checklist paragraph. Pilots must familiarize themselves with the procedures given in this section and must be prepared to take the appropriate action should an emergency situation arise. The procedures are offered as a course of action for coping with the pa rticula r situation or condition described. They a re not a substitute for 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 proced ures which are applicable to this airplane. The pilot should review standard emergency procedures periodically to remain proficient in them. ISSUED: SEPTEMBER 15,1988 REPORT: VB-1365 3-1 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28R-201, ARROW 3.3 AIRSPEEDS FOR SAFE OPERATION 3.3a STALL SPEEDS 2750 Ibs (Gear Up, 0° Flap) ........................... 60 KIAS 2750 lbs (Gear Down, 400 Flap) ........................ 55 KIAS 3.3b MANEUVERING SPEEDS 2750 Ibs ............................................ 118 KIAS 1865 Ibs ............................................. 96 KIAS 3.3c NEVER EXCEED SPEED Never Exceed Speed ................................. 183 KIAS 3.3d POWER OFF GLIDE SPEED 2750 Ibs (Gear Up, 00 Flap) ........................... 79 KIAS REPORT: VB-1365 3-2 ISSUED: SEPTEMBER IS, 1988 ( ( PIPER AIRCRAFT CORPORATION PA-28R-201. ARROW, SECTION 3 EMERGENCY PROCEDURES 3.5 EMERGENCY PROCEDURES CHECKLIST 3.5a ENGINE FIRE DURING START (3.9) Starter ........................................................................CRANK ENGINE Mixture ......................................................................... IDLE CUT~OFF Throttle .........................................................................................OPEN Electric Fuel Pump ..........................................................................OFF Fuel Selector....................................................................................OFF Abandon if fire continues. 3.Sh ENGINE POWER LOSS DURING TAKEOFF (3.11) If sufficient runway remains for a normal landing, leave gear down and rand straight ahead. . If area ahead is rough or if it is necessary to clear obstructions: Gear Selector Switch .........................................................................UP If sufficient altitude has been gained to attempt a restart: Maintain safe airsp~d. Fuel Selector ................................................................SWITCH to tank containing fuel Electric Fuel Pump .............................................................CHECK ON Mixture ...........................................................................CHECK RICH Alternate Air .................................................................................OPEN as required If power is not regained. proceed with power off landing (3.Sd). I 3.Se ENGINE POWER LOSS IN FLIGHT (3.13) If at low altitude: Airspeed .........................................................................MAINTAIN 79 KIAS minimum Prepare for power off landing (3.Sd). If altitude permits: Fuel Selector ................................................................ SWITCH to tank ISSUED: SEPTEMBER 15, 1988 REVISED: MARCH 10, 1989 containing fuel REPORT: V8-1365 3-3 I SECTION 3 EMERGENCY PROCEDURES PIPER AlRCRAFf CORPORATION IJA-28R-201, ARROW 3.sc ENGINE POWER LOSS IN FLIGHT (3.13) (continued) Electric fuel pump .............................................................................ON Mixture ......................................................................................... RICH ( Alternate Air.................................................................................OPEN Engine Gauges ....................................................CHECK for indication of cause of power loss If no fuel flow/pressure is indicated. check tank selector position to be sure it is on a tank containing fuel. When power is restored: Alternate Air ..............................................................................CLOSE Electric Fuel Pump ..........................................................................OFF If power is not restored, prepare for power off landing. Trim for 79 KIAS. 3.Sd POWER OFF LANDING (3.15) Trim for 79 KIAS. Locate suitable field. Establish spiral pattern. 1000 ft. above field at downwind position for normal landing (' approach. When field can be easily reached. slow to 72 KIAS for shortest landing. Gear Down Emergency Landing (3.1sa) Touchdowns should be normally be made at the lowest possible airspeed wilh full flaps. When committed to landing: Landing Gear Selector................................................................DOWN Flaps ................................................................................ AS DESIRED Throttle ......................................................................................CLOSE Mixture ........................................................................ IDLE CUT-OFF Ignition ............................................................................................OFF BATT MASTR Switch ....................................................................OFF ALTR Switch ...................................................................................OFF Fuel Selector ....................................................................................OFF Seat Belts and Harness ................................................................TIGHT NOTE ( If battery master switch is OFF. the landing gear cannot be retracted. REPORT: VB-136S 3·4 ISSUED: SEPTEMBER 15,1988 REVISED: MARCH 10, 1989 PIPER AIRCRAFT CORPORATION SECTION 3 PA·28R.201, ARROW EMERGENCY PROCEDURES 3.Sd POWER OFF LANDING (3.15) (continued) Gear Up Emergency Landing (3.1Sb) In the event a gear up landing is required, proceed as follows: Flaps ............................................................................... AS DESIRED) Throttle ......................................................................................CLOSE Mixmre....................................................................... .IDLE CUT-OFF Ignition ............................................................................................OFF BAIT MASTR Switch .................................................................... OFF ALTR Switch ...................................................................................OFF Fuel Selector ....................................................................................OFF Seat Belt and Hruness .................................................................TIGHf Contact surface at minimum possible airspeed 3.Se FIRE IN FLIGHT (3.17) Source of Fire ............................................................................ClIECK Electrical Fire (Smoke in Cabin): BAIT MASTR Switch ....................................................................OFF IALTR Switch ...................................................................................OFF Vents ............................................................................................OPEN Cabin Heat .......................................................................................OFF Land as soon as practical Engine Fire: Fuel Selector ....................................................................................OFF Throttle ...................................................................................CLOSED Mixmre....................................................................... .IDLE CUT-OFF Electric Fuel Pump ............................................................ClIECK OFF Heater and Defroster .......................................................................OFF Proceed with power off landing procedure (3.Sd). 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: SEPTEMBER 15, 1988 REVISED: MARCH 10, 1989 REPORT: VB·1365 3·5 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28R-201, ARROW 3.Sf LOSS OF OIL PRESSURE (3.19) Land as soon as possible and investigate cause. Prepare for power off landing. 3.5g LOSS OF FUEL FLOW/PRESSURE (3.21) Electric Fuel Pump ...................................... ON Fuel Selector ................................ CHECK on tank 3.Sh HIGH OIL TEMPERATURE (3.23) Land at nearest airport and investigate the problem. Prepare for power off landing. 3.51 ELECTRICAL FAILURE (3.25) ALT annunciator light illuminated: containing fuel Ammeter ................................ CHECK to VERI FY inop. alt. If ammeter shows zero: AL TR Switch ......................................... OFF Reduce electrical loads to minimum: AL TNTR. FIELD Circuit Breaker .......................... CHECK and RESET as required ALTR Switch .......................................... ON If power not restored: ALTR Switch ......................................... OFF If alternator output cannot be restored, reduce electrical loads and land as soon as practical. The battery is the only remaining source of electrical power. ( ( 3.Sj ELECTRICAL OVERLOAD (Alternator over 20 &mps above known electrical load) (3.27) ( BATT MASTR Switch ................................. OFF REPORT: V8-1365 3-6 ISSUED: SEPTEMBER 15,1988 PIPER AIRCRAFT CORPORATION SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES 3.5j ELECTRICAL OVERLOAD (Alternator over 20 amps above known electrical load) (3.27) (Continued) If ammeter 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: BATT MASTR Switch .......................................................................... ON Ammeter ...................................................................................MONITOR If ammeter reading does NOT begin to decrease within five minutes: BATT 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. NOTE Due to increased system voltage and radio frequency noise, operation with ALTR switch ON and BATT switch OFF should be made only when required by an electrical system failure. If ammeter reading DOES begin to decrease within five minutes: Proceed with flight. Ammeter ................................................................................... MONITOR 3.5k PROPELLER OVERSPEED (3.29) Throttle ......................................................................................... RETARD Oil Pressure .................................................................................... CHECK ISSUED: SEPTEMBER 15, 1988 REPORT: VB-1365 3-7 SECTION 3 EMERGENCY PROCEDURES PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW 3.5k PROPELLER OVERSPEED (continued) Propeller Control .....................................................FULL DECREASE (' rpm, then set if any control available. Airspeed ..................................................................................REDUCE Throttle ....................................................................AS REQUIRED to remain below 2700 rpm 3.5m EMERGENCY LANDING GEAR EXTENSION (3.31) NOTE Refer to paragraph 4.39 for differences when emergency gear extension is being performed for training purposes. Prior to emergency extension procedure: BAIT MASTR Switch ....................................................... CHECK ON ALTR Switch ...................................................................... CHECK ON Circuit Breakers ........................................................................ CHECK NAV LIGHT Switch ................................................... OFF (in daytime) ( Gear Indicator Bulbs ................................................................. CHECK Iflanding gear does not check down and locked: Airspeed ...................................................................REDUCE BELOW 87 KIAS Landing Gear Selector Switch ........................................ GEAR DOWN POSITION If gear has still failed to lock down, move and hold the emergency lever down to the Emergency Down position. If gear has still failed to lock down~ yaw the airplane abruptly from side to side with the rudder. If the nose gear will not lock down using the above procedure, slow the aircraft to the lowest safe speed attainable using the lowest power setting required for safe operation and accomplish the following: Landing Gear Selector Switch ........................................ GEAR DOWN ( POSITION If landing gear does not check down, recycle gear through up position and then select gear DOWN. REPORT: VB-1365 3-8 ISSUED: SEPTEMBER 15, 1988 REVISED: MAY 8, 1995 PIPER AIRCRAFT CORPORATION SECTION 3 PA-28R-201, ARROW EMERGENCY PROCEDURES 3.50 SPIN RECOVERY (3.33) Rudder ................................ FULL OPPOSITE to DIRECTION of ROTATION Control Wheel .................... FULL FORWARD WHILE NEUTRALIZING AILERONS Throttle .............................................. IDLE Rudder ...................... NEUTRAL (when rotation stops) Control Wheel ................ AS REQUIRED to SMOOTHLY REGAIN LEVEL FLIGHT ATTITUDE 3.50 OPEN DOOR (3.35) If both upper and side latches are open, the door will trail slightly open and airspeeds will be reduced slightly. To close the door in flight: Slow airplane to 87 KIAS. Cabin Vents ......................................... CLOSE Storm Window ....................................... OPEN If upper latch is open ................................ LATCH If side latch is open ..................... PULL on ARMREST while moving Latch Handle to LATCH position If both latches are open .................................. LATCH SIDE LATCH then TOP LATCH 3.5p ENGINE ROUGHNESS (3.37) Mixture .................... ADJUST for maximum smoothness Alternate Air ......................................... OPEN Electric Fuel Pump ........... -........................... ON Fuel Selector .............................. SWITCH TANKS Engine Gauges ...................................... CHECK Magneto Switch ............................... L then R then BOTH If operation is satisfactory on either magneto, proceed on that magneto at reduced power, with full RICH mixture,toa landingatthe first available airport. If roughness persists, prepare for a precautionary landing. ISSUED: SEPTEMBER 15, 1988 REPORT: V8-1365 3-9 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28R-201, ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1365 3-10 ISSUED: SEPTEMBER IS, 1988 ( ( ( PIPER AIRCRAFT CORPORATION 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 fires during start are usually the result of overpriming. The first attempt to extinguish the fire is to try to start the engine and draw the excess fuel back into the induction system. If a fire is present before the engine has started, move the mixture control to idle cut-off, open the throttle and crank the engine. This is an attempt to draw the fire back into the engine. If the engine has started, continue operating to try to pull the fire into the engine. In either of the above cases, if fire continues for more than a few seconds, the fire should be extinguished by the best available external means. The fuel selector valves should be OFF and the mixture at idle cut-off if an external fire extinguishing method is to be used. 3.11 ENGINE POWER LOSS DURING TAKEOFF (3.Sb) The proper action to be taken if loss of power occurs during takeoff will depend on the circumstances of the particular situation. If sufficient runway remains to complete a normal landing, leave the landing gear down and land straight ahead. If the area ahead is rough, or if it is necessary to clear obstructions, move the gear selector switch to the UP position. If sufficient altitude has been gained to attempt a restart, maintain a safe airspeed and switch the fuel selector to a tank containing fuel. Place the electric fuel pump to ON. Check that the mixture is RICH. The alternate air should be open. ISSUED: SEPTEMBER 15, 1988 REPORT: V8-136S 3-11 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28R-201, ARROW 3.11 ENGINE POWER LOSS DURING TAKEOFF (3.Sb) (continued) If engine failure was caused by fuel exhaustion, power will not be ( regained after switching fuel tanks until the empty fuel lines are filled. This may require up to ten seconds. If power is not regained. proceed with the Power Off Landing proced ure (refer to the emergency checklist and paragraph 3.15). 3.13 ENGINE POWER LOSS IN FLIGHT (3.Se) Complete engine power loss is usually caused by fuel flow interruption and power will be restored shortly after fuel flow is restored. If power loss occurs at a low altitude. the first step is to prepare for an emergency landing (refer to paragraph 3.15). An airspeed of at least 79 KIAS should be maintained. If altitude permits. switch the fuel selector to another tank containing fuel and turn the electric fuel 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 alterna te air to the CLOSED position and turn OFF the electric fuel pump. 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 throttle and mixture control levers to different settings. This may restore power if the problem is too rich or too lean a mixture or if there is a partial fuel system restriction. Try the other fuel tank. Waterin the fuel could 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 in.dications will be normal. ( REPORT: VB-1365 3-12 ISSUED: SEPTEMBER 15, 1988 PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW SECTION 3 EMERGENCY PROCEDURES 3013 ENGINE POWER LOSS IN FLIGHT (305c) (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 require up to ten seconds. If power is not regained, proceed with the Power Off Landing procedure (refer to emergency checklist and paragraph 3.15). Trim for 79 KIAS. 3015 POWER OFF LANDING (305d) If loss of power occurs at altitude, trim the aircraft for best gliding angle (79 KIAS, air'conditioner oft) and look for a suitable field. If measures taken to restore power are not effective, and if time permits, check your charts for airports in the immediate vicinity; it may be possible to land at one if you have sufficient altitude. At best gliding angle, with the engine windmilling, and the propeller control in full DECREASE rpm, the aircraft will 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 is aboard, let him help. When you have located a suitable field, establish a spiral pattern around this field. Try to be at 1000 feet above the field at 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 shortest landing. Excess altitude may be lost by 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 field chosen is obviously 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 better protect the occupants of the aircraft. If, however, the field is suspected to be excessively soft or short, or when landing in water of any depth, a wheels-up landing will normally be safer and do less damage to the airplane. Touchdown should normally be made at the lowest possible airspeed. ISSUED: SEPTEMBER 15, 1988 REPORT: VB-1365 3-13 SECTION 3 EMERGENCY PROCEDURES PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW 3.15 POWER OFF LANDING (3.5d) (continued) 3.15a Gear Down Emergency Landing (3.5d) When committed to a gear down emergency landing, select landing gear DOWN. Flaps may be used as desired. Close the throttle control and move the mixture control to idle cut-off. Shut OFF the ignition, battery master (BATT MASTR), and alternator (ALTR) switches. Tum the fuel selector valve to OFF. The seat belts and shoulder harness should he tightened. Touchdown should normally be made at the lowest possible airspeed. NOTE If the battery master switch is OFF, the landing gear cannot be retracted. 3.15b Gear Up Emergency Landing (3.5d) ( 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. Tum OFF the. fuel selector valve. Seat belts and shoulder harness should be tightened. Touchdown should normally be made at the lowest possible airspeed with full flaps. REPORT: VB-1365 3-14 ISSUED: SEPTEMBER 15, 1988 REVISED:MAY 8, 1995 ( PIPER AIRCRAFT CORPORATION SECTION 3 PA-28R-10l, ARROW EMERGENCY PROCEDURES 3.17 FIRE IN FLIGHT (3.Se) The presence of fire is noted through smoke, smell and heat in thecabin. 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 to be taken differs somewhat in each case. Check for the source of the fire first. If smoke in the cabin indicates an electrical fire, turn the battery master (BAIT 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. If an engine fire is present, switch the fuel selector to OFF and close the throttle. The mixture should be at idle cut-off. Turn the electric fuel pump OFF. In all cases, the heater and defroster should be OFF. If radio communication is not required select the battery master (BAIT MASTR) and alternator (AL TR) 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 oil pressure may be either partial or complete. A partial loss of oil pressure usually indicates a malfunction in the oil pressure regulating system, and a landing should be made as soon as possible to investigate the cause and prevent engine damage. A c·omplete loss of oil pressure indication may signify oil exhaustion or may be the result of a faulty gauge. In either case, proceed toward the nearest airport, and be prepared for a forced landing. If the problem is nota pressure gauge malfunction, the engine may stop suddenly. Maintain altitude until such time as a dead stick landing can be accomplished. Don't change power settings unnecessarily, as this may hasten complete power loss. ISSUED: SEPTEMBER 15, 1988 REPORT: V8-1365 3-15 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28R-201, ARROW 3.19 LOSS OF OIL PRESSURE (3.Sf) (continued) Depending on the circumstances, it may be advisable to make an off ( airport landing while power is still available, particularlyif otherindications of actual oil pressure loss, such as sudden increases in temperatures, or oil smoke, are apparent, and an airport is not close. If engine stoppage occurs, proceed with Power Off Landing. 3.21 LOSS OF FUEL FLOW/PRESSURE (3.5g) The most probable cause of loss of fuel flow/pressure is either fuel depletion in the fuel tank selected, or failure of the engine driven fuel pump. If loss of fuel flow/ pressure occurs, check that the fuel selector is on a tank containing fuel and turn ON the electric fuel pump. If the problem is not an empty tank, land as soon as practical and have the engine driven fuel pump and fuel system checked. 3.23 HIGH OIL TEMPERATURE (3.Sh) An abnormally high oil temperature indication maybe caused bya low ( oil level, an obstruction in the oil cooler, damaged or improper baffle seals, a ' defective gauge, or other causes. Land as soon as practical atan appropriate airport and 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 (3.5i) Loss of alternator output is detected through zero reading on the ammeter. Before executing the following procedure, ensure that the reading is zero, and not mere\ylow, by actuating an electrically powered device, such as the landing light. If no increase in the ammeter reading is noted,aJterna tor failure can be assumed. The electrical load should be reduced as much as possible. Check foran open alternator field circuit breaker. Next, attempt to reset the overvoltage relayby 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) this procedure should return the ammeter to a normal reading. REPORT: V8-1365 3-16 ISSUED: SEPTEMBER IS, 1988 PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW SECTION 3 EMERGENCY PROCEDURES 3.25 ELECTRICAL FAILURE (3.5i) (continued) If the ammeter continues to indicate ZERO output, or if the alternator will not remain reset, turn off the ALTR switch, maintain minimum electrical load and land as soon as practical. All electrical load is being supplied by the battery. 3.27 ELECTRICAL OVERLOAD (Alternator over 20 amps above known elec.tricalload) (3.5j) An abnormally high alternator output may be caused by a low battery, battery fault, or other abnormal electrical load. 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 BATT 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 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. NOTE Due to increased system voltage and radio frequency noise, operation with ALTR switch ON and BATT 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: SEPTEMBER 15, 1988 REPORT: VB-1365 3-17 SECTION 3 EMERGENCY PROCEDURES PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW 3.29 PROPELLER OVERSPEED (3.5k) Propeller overspeed is caused by a malfunction in the propeller governor or low oil pressure which allows the propeller blades to rotate to full low pitch. ( If propeller overspeed should occur. retard the throttle and check the oil pressure. The propeller control should be moved to full DECREASE rpm and then set if any control is available. Airspeed should he reduced and throttle used to maintain 2700 rpm. 3.31 EMERGENCY LANDING GEAR EXTENSION (3.5m) NOTE Refer to paragraph 4.39 for differences when emergency gear extension is being performed for training purposes. Prior to initiating the emergency extension procedure, check to ensure that the battery master (BAIT MASTR) and alternator (ALTR) switches are ON, and that the circuit breakers have not opened. If it is in daytime, the NAV ( LIGHT switch should be turned OFF. Check the landing gear indicators for faulty bulbs. If the landing gear does not check down and locked, reduce the airspeed below 87 KIAS. Move the landing gear selector switch to the DOWN position. I If the gear has still failed to lock down, move and hold the emergency gear lever down to the EMERGENCY DOWN position. If the gear has still failed to lock down, yaw the airplane abruptly from side to side with the rudder. !f the nose gear will not lock down using the above procedure, slow the airplane to the lowest safe speed attainable using the lowest power setting required for safe operation. Move the landing gear selector switch to the gear DOWN position. If the landing gear does not check down, recycle the gear I through the UP position and then select the DOWN position. \ REPORT: VB-1365 3-18 ISSUED: SEPTEMBER 15, 1988 REVISED: MAY 8, 1995 PIPER AIRCRAFT CORPORA nON SECTION 3 PA-18R-l0t, ARROW EMERGENCY PROCEDURES 3.33 SPIN RECOVERY (3.5n) Intentional spins are prohibited in this airplane. If a spin is inadvertently entered. immediately apply full rudder opposite to the direction of rotation. Move the control wheel full forward while neutralizing the ailerons. Move the throttle to IDLE. When the rotation stops. neutralize the rudder and ease back on the control wheel as required to smoothly regain a level flight attitud~. . 3.35 OPEN DOOR (3.50) The cabin door is double latched. so the chances of its springing open in flight at both the top and bottom are remote. However. should the upper latch be overlooked or the side latch not fully engaged, the door may spring partially open. This will usually happen at takeoff or soon afterward. A partially open door will not affect normal flight cha racteristics. and a normal landing can be made with the door open. . If both upper and side latches are open. the door will trail slightly open, and airspeed will be reduced slightly .. _ To close the doorin flight, slow the airplane to 87 KIAS, close the cabin vents and open the storm window. If the top latch is open, latch it. 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 la tch. 3.37 ENGINE ROUGHNESS (3.Sp) Engine roughness may be caused by dirt in the injector nozzles, induction system icing, or ignition problems. First adjust the mixture for maximum smoothness. The engine will run rough if the mixture is too rich or too lean. Move the alternate air to OPEN and then turn ON the electric fuel pump Switch the fuel selector to another tank to see if fuel contamination is the problem. Check the engine gauges for abnormal readings. If any gauge readings are abnormal proceed accordingly. ISSUED: SEPTEMBER 15, 1988 REPORT: VB-136S 3-19 SECTION 3 PIPER AIRCRAFT CORPORATION 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 ( ROTH. If operation is satisfactory on either magneto. proceed on that magneto at reduced power with full RICH mixture to a landing at the first available airport. If roughness persists. prepare for a precautionary landing at pilot's discretion. REPORT: VB-136S 3-20 ISSUED: SEPTEMBER 15,1988 ( ( PIPER AIRCRAFT CORPORATION PA-28R-10l, ARROW SECTION 4 NORMAL PROCEDURES Paragraph No. T ABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Page No. 4.1 General 4-1 4.3 Airspeeds for Safe Operations. . . . . . . . . . . . . . . . . . . . . . . 4-2 4.S Normal Procedures Checklist. . . . . . . . . . . . . . . . . . . . . . . . 4-3 4.Sa Preflight Checklist (4.9) ........................... 4-3 4.Sb Before Starting Engine Checklist (4.11) . . . . . . . . . . . . . . 4-6 4.5c Engine Start Checklist (4.13) . . . . . . . . . . . . . . . . . . . . . . . 4-7 NORMAL START - COLD ENGINE (4.13a)....... 4-7 NORMAL START - HOT ENGINE (4.13b) ... :.... 4-7 ENGINE START WHEN FLOODED (4.13c).... ... 4-7 ENGINE START WITH EXTERNAL POWER SOURCE (4.13d) ....................... 4-7 4.5d Warm-Up Checklist (4.IS) ......................... 4-8 4.5e Taxiing Checklist (4.17) ........................... 4-9 4.5f Ground Check Checklist (4.19) . . . . . . . . . . . . . . . . . . . . . 4-9 4.5g Before Takeoff Checklist (4.21) . . . . . . . . . . . . . . . . . . . . . 4-9 4.5h . Takeoff Checklist (4.23) ........................... 4- 10 NORMAL TECHNIQUE (4.23a). ................. 4-10 SHORT FIELD, OBSTACLE CLEARANCE TECHNIQUE (4.23b) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-10 SOFT FIELD TECHNIQUE (4.23b). .............. 4-11 4.5i Climb Checklist (4.25) . . .. .. . .. . .. .. .. .. . .. . .. .. . .. 4-11 ISSUED: SEPTEMBER IS, 1988 REPORT: V8-1365 4-i SECTION 4 NORMAL PROCEDURES PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW Paragraph No. T ABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES (cont) 4.5j Cruise Checklist (4.27) 4.5k Approach And Landing Checklist (4.29) ............ . 4.5m Stopping Engine Checklist (4.31) .................. . 4.5n Mooring Checklist (4.33) ......................... . 4.7 AMPLIFIED PROCEDURES .................... .. 4.9 PREFLIGHT CHECK (4.5a) ..................... .. 4.9a Cockpit (4.5a) ................................... . 4.9b Right Wing (4.5a) .............................. .. 4.9c Nose Section (4.5a) .............................. . 4.9d Left Wing (4.5a) .... , ............................ . 4.ge Fuselage (4.5a) .................................. . 4.11 BEFORE STARTING ENGINE (4.Sb) .............. . 4.13 ENGINE START (4.5c) ........................... . 4.13a Normal Start - Cold Engine (4.5c) ................. . 4.13b Normal Start - Hot Engine (4.5c) .................. . 4./3c Engine Start When Flooded (4.5c) ................. . 4. t 3d Engine Start With External Power Source (4.5c) ..... . 4.15 WARM-UP (4.5d) ............................... .. 4.17 TAXIING (4.5e) .................................. . 4.19 GROUND CHECK (4.50 ......................... . Page No. ( 4-11 4-12 4-12 4-13 4-/5 4-15 4-15 ( 4-15 4-16 4-17 4-17 4-18 4-18 4-18 4-19 4-19 4-19 4-20 4-20 ( 4-21 REPORT: VB-1365 4-ii ISSUED: SEPTEMBER 15, 1988 PIPER AIRCRAFT CORPORATION PA-28R-lOt, ARROW SECTION 4 NORMAL PROCEDURES T ABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES (cont) Paragraph No. 4.21 4.23 4.23a 4.23b 4.25 4.27 4.29 4.31 4.33 4.35 4.37 4.39 4.41 4.43 BEFORE TAKEOFF (4.5g) ....................... . TAKEOFF (4.Sh) ..............•.................. 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 OPERA nON ................. . LANDING GEAR ............................... . WEIGHT AND BALANCE ....................... . NOISE LEVEL ........... ; ...................... . Page No. 4-22 4-22 4-22 4-22 4-23 4-23 4-25 4-25 4-26 4-26 4-27 4-27 4-28 4-28 ISSUED: SEPTEMBER 15,1988 REPORT: VB-1365 4-iii SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28R-201, ARROW REPORT: VB-1365 ISSUED: SEPTEMBER 15, 1988 4-iv THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW SECTION 4 SECTION 4 NORMAL PROCEDURES NORMAL PROCEDURES 4.1 GENERAL This section provides the normal operating procedures for the PA-28 R- 20 I, 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 proficient in the normal operation of the airplane. This section is divided into two parts. The first part is a short form checklist supplying an action - reaction sequence for normal procedures with little emphasis on the operation of the systems. Numbers in parentheses after each 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 inflight reference due to the lengthly explanation. The short form checklists should be used on the ground and in flight. Numbers in parentheses after each paragraph title indicate where the corresponding checklist can be found. ISSUED: SEPTEMBER 15,1988 REPORT: VB-1365 4-1 SECTION 4 NORMAL PROCEDURES PIPER AIRCRAFT CORPORATION 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 airplanes flown at ( gross weight under standard conditions at sea level. Performance for a specific airplane may vary from published figures depending upon the equipment installed, the condition of the. engine, airplane and equipment, atmospheric conditions and piloting technique. (a) Best Rate of Climb Speed gear up, flaps up gear down, flaps up (b) Best Angle of Climb Speed gear up, flaps up gear down, flaps up (c) Turbulent Air Operating Speed (See Subsection 2.3) (d) Maximum Flap Speed (e) Landing Final Approach Speed (Aaps 4(0) (0 Maximum Demonstrated Crosswind Velocity 90 KIAS 78 KIAS 78 KIAS 72 KIAS liS KIAS 103 KIAS 75 KIAS 17 KTS REPORT: VB-1365 4-2 ISSUED: SEPTEMBER 15,1988 ( ( PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW SECTION 4 NORMAL PROCEDURES ......................: : :-. ---: : : j i: : ...........................................! !.I .......................~ ................: ; ; : i , : ! ~ i..............................................: :·................,.. ..,.H.................... ,,,.i : : i i1 • : : \ € [::::::::~ .....:.....:~.=.:] WALK-AROUND Figure 4-1 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 ................................................................... release restraints Gear Handle .................................................................................... DOWN Parking Brake ....................................................................................... SET Avionics ................................................................................................ OFF All Switches ......................................................................................... OFF Mixture ............................................................................. .IDLE CUT-OFF Magneto Switch ................................................................................... OFF BATT MASTR Switch ........................................................................... ON ISSUED: SEPTEMBER 15, 1988 REPORT: VB-1365 4-3 SECTION 4 NORMAL PROCEDURES PIPER AIRCRAFT CORPORATION 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 Flight Controls .........................................PROPER OPERATION Flaps ...................................................................... PROPER OPERATION Trim ...........................................................................................NEUTRAL Pitot and Static Systems .................................................................. 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 Static Wicks ................................................................. 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 starting engine. Fuel Tank Sump ......................................................... DRAIN and CHECK for water, sediment, and proper fuel Tie Down and Chock ..................................................................REMOVE Main Gear Strut ...................................................... PROPER INFLATION (2.0 +/- 0.25 in.) Tire ................................................................................................. CHECK Brake Block and Disc .................................................................... CHECK Fresh Air Inlet ................................................................................ CLEAR ( REPORT: VB·1365 4-4 ISSUED: SEPTEMBER 15, 1988 REVISED: APRIL 24, 2006 PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW 4.5a Preflight Checklist (continued) NOSE SECTION (4.9c) SECTION 4 NORMAL PROCEDURES General Condition .......................................................................... CHECK Cowling ........................................................................................SECURE Oil. ............................................................................ CHECK QUANTITY Dipstick .................................................................... PROPERLY SEATED Oil Filler Cap ................................................................................ SECURE Engine Baffle Seals ........................................................................ CHECK Windshield ..................................................................................... CLEAN Propeller and Spinner ..................................................................... CHECK Air Inlets ......................................................................................... CLEAR Alternator Belt ............................................................. CHECK TENSION Landing Light. ................................................................................ CHECK Chock ..........................................................................................REMOVE Nose Gear Strut ......................................................PROPER INFLATION (2.75 +/- 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 starting engine. Fuel Strainer ....................................................................................DRAIN LEFT WING (4.9d) Surface Condition ................................... CLEAR of ICE,.FROST, SNOW Stall Warning Vane ......................................................................... CHECK Fuel Tank .............................................................. CHECK supply visually -SECURECAP 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 starting engine. ISSUED: SEPTEMBER 15, 1988 REVISED: APRIL 24, 2006 REPORT: VB-1365 4·5 SECTION 4 NORMAL PROCEDURES PIPER AIRCRAFT CORPORATION 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 Pitot Mast. ..................................................................... REMOVE COVER -HOLECLEAR Wing Tip and Lights ...................................................................... CHECK Aileron and Hinges ........................................................................ CHECK Flap and Hinges ............................................................................. CHECK Static Wicks ................................................................. CHECK - SECURE FUSELAGE (4.ge) Antennas ........................................................................................ CHECK Left Static Vent ............................................................................... CLEAR Fresh Air Inlet ................................................................................ CLEAR Empennage ........................................................................ CLEAR of ICE, FROST,SNOW Stabilator and Trim Tab ................................................................. CHECK Tie Down ..................................................................................... REMOVE ( Right Static Vent. ............................................................................ CLEAR BATT MASTR Switch ........................................................................... ON Cockpit Lighting ............................................................................ CHECK Navigation and Strobe Lights ........................................................ CHECK Landing Light. ................................................... '" .......................... CHECK Stall Warning .................................................................................. CHECK Pitot Heat ....................................................................................... CHECK All Switches ......................................................................................... OFF BATT MASTR Switch ......................................................................... OFF Passengers ...................................................................................... BOARD Cabin Door............................................................... CLOSE and SECURE Seat Belts and Harness ................................................. FASTEN - CHECK 4.5b Before Starting Engine Checklist (4.11) BEFORE STARTING ENGINE (4.11) inertia reel Brakes ................................................................................................... SET Circuit Breakers ...................................................................................... .IN ( Alternate Air ......................................................................................... OFF Propeller .............................................................. FULL INCREASE RPM Avionics ................................................................................................ OFF Fuel Selector ...................................................................DESIRED TANK REPORT: VB·1365 4·6 ISSUED: SEPTEMBER 15, 1988 PIPER AIRCRAFT CORPORATION PA-28R.201, ARROW SECTION 4 NORMAL PROCEDURES 4.Sc Engine Start Checklist (4.13) NORMAL START· COLD ENGINE (4.13) Throttle........................................................................ 1(2 INCH OPEN ALTR Switch ....................................................................................ON BAIT MASTR Switch ......................................................................ON Electric Fuel Pump ............................................................................ON Mixture .....................................................................RICH - then IDLE . CUT-OFF Propeller..................................................................................... CLEAR I Starter... .................................................................................ENGAGE Mixture ............................................................................. .FULL RICH Throttle ....................................................................................ADJUST Oil Pressure ...............................................................................CHECK NORMAL START· HOT ENGINE (4.13b) Throttle ........................................................................ 1(2 INCH OPEN AL1R Switch ....................................................................................ON BAIT MASTR Switch .......................................................................ON Electric Fuel Pump ............................................................................ON Mixture ....................................................................... .IDLE CUT-OFF Propeller..................................................................................... CLEAR I Starter... ..~ ..............................................................................ENGAGE Mixture ................................................................................ ADVANCE Throttle....................................................................................ADJUST Oil Pressure ............................................................................... CHECK ENGINE START WHEN FLOODED (4.13c) Throttle.............................................................................FULL OPEN ALlR Switch ....................................................................................ON BAIT MASTR Switch ......................................................................ON Electric Fuel Pump ..........................................................................OFF Mixture ....................................................................... .IDLE CUT-OFF Propeller...............................................................................;..... CLEAR I Starter... .................................................................................ENGAGE Mixture ................................................................................ ADVANCE Throttle...................................................................................RETARD Oil Pressure ...............................................................................CHECK ENGINE START WITH EXTERNAL POWER SOURCE (4.13d) BAIT MASTR Switch .................................................................... OFF ALTR Switch ...................................................................................OFF All Electrical Equipment .................................................................OFF ISSUED: SEPTEMBER 15, 1988 REVISED: MARCH 10, 1989 REPORT: VB·1365 4-7 SECTION 4 NORMAL PROCEDURES PIPER AIRCRAFT CORPORATION PA-28R-201, ARROW 4.5c Engine Start Checklist (4.13) (continued) ENGINE START WITH EXTERNAL POWER SOURCE (4.13d) ( (continued) Terminals ....................................... CONNECT External Power Plug .................... INSERT in receptacle Proceed with normal start. Throttle .......................... LOWEST POSSIBLE RPM External Power Plug ................ REMOVE from receptacle BATT MASTR Switch .................................. ON ALTR Switch ..................... ON - CHECK AMMETER Oil Pressure ........................................ CHECK 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 alternator switches should be OFF. 4.5d Warm-Up Checklist (4.15) WARM-UP (4.15) Throttle ................................... 1400 to 1500 RPM REPORT: V8-1365 4·8 ISSUED: SEPTEMBER 15, 1988 ( ( PIPER AIRCRAFT CORPORATION SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES ISSUED: SEPTEMBER 15, 1988 REPORT: VB-1365 4-9 REVISED: MAY 10, 2009 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 Magnetos ........................................................................................ CHECK max. drop 175 RPM - max. diff. 50 RPM Vacuum ....................................................................... 4.8 to 5.2 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 throttle can be opened without engine faltering. Electric Fuel Pump............................................................................... OFF Fuel Pressure .................................................................................. CHECK Throttle .........................................................................................RETARD 4.5g Before Takeoff Checklist (4.21) BEFORE TAKEOFF (4.21) BATT MASTR Switch .......................................................................... ON ALTR Switch ......................................................................................... ON Flight Instruments .......................................................................... CHECK SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28R-201, ARROW REPORT: VB-1365 ISSUED: SEPTEMBER 15, 1988 4-10 REVISED: OCTOBER 31, 2012 4.5g Before Takeoff Checklist (4.21) (continued) BEFORE TAKEOFF (4.21) (continued) Fuel Selector .................................................................... PROPER TANK Electric Fuel Pump................................................................................. ON Engine Gauges ............................................................................... CHECK Alternate Air ................................................................................ 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 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 ..............................................................................25Þ (second notch) Accelerate to 50 to 60 KIAS depending on aircraft weight. Control Wheel ...................................................back pressure to ROTATE to CLIMB ATTITUDE After breaking ground, accelerate to 55 to 65 KIAS depending on aircraft weight. Gear .........................................................................................................UP Accelerate to best gear up angle of climb speed - 78 KIAS, slowly retract the flaps and climb past the obstacle. Accelerate to best gear up rate of climb speed - 90 KIAS. PIPER AIRCRAFT CORPORATION SECTION 4 PA-28R-201, ARROW NORMAL PROCEDURES ISSUED: SEPTEMBER 15, 1988 REPORT: VB-1365 4-11 REVISED: MARCH 10, 1989 4.5h Takeoff Checklist (4.23) (continued) SOFT FIELD TECHNIQUE (4.23b) Flaps ..............................................................................25Þ (second notch) Accelerate to 50 to 60 KIAS depending on aircraft weight. Control Wheel ...................................................hack pressure to ROTATE to CLIMB ATTITUDE After breaking ground, accelerate to 55 to 65 KIAS depending on aircraft weight. Gear .........................................................................................................UP Accelerate to best gear up rate of climb speed - 90 KIAS. Flaps .........................................................................RETRACT SLOWLY 4.5i 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) ................................................................................... 78 KIAS Best Angle (2750 lb.) (Gear Down, Flaps Up) ................................................................................... 72 KIAS En Route...................................................................................... 104 KIAS Electric Fuel Pump...............................................................OFF at desired altitude 4.5j Cruise Checklist (4.27) CRUISE (4.27) Reference performance charts, Avco-Lycoming Op