Pilot's Operating Handbook

Maximum Weights ... ..... .. ... .. ... .. ..... ... .. .. Standard Airplane Weights .. ... ..... .. .... ... .. .. .. Baggage Space ....... .. .... ... ..... ........ . ... ... Specific Loadings . .. .... ............ ... ... .... ..... Symbols, Abbreviations and Terminology .. ... . ...... . Conversion Factors . ... ...... .. ..... .. . ........ , . ... 1 - 1 1-3 1-3 1-4 1-4 1-5 1-5 1-5 1-5 1-6 1-12 1 1(I ! REPORT: VB -930 . . !. j: I , PIPER AIRCRAFT CORPORATION SECTION 1! PA-28RT-201, ARRO W IV G E N E RA L SECTION I GENERAL , 1.1 INTRODUCTION \i This Pilot’s Operating Handbook is designed for maximum utilization as an Operating guide for the pilot. It includes the material requircd to be fumished to the pilot by CAR 3 and FAR Part 21 Subpart J. It also contains supplemental data supplied by the airplane manufacturer. This handbook is not designed as a Substitute for adequate and compe- tent flight instruction, knowledge of current ainvorthiness directives, appli- cable 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 beused for operational purposes unless kept in a current Status. Assurance that the airplane is in an airworthy condition is the responsi- bility of the owner. The pilot in command is responsible for determining that the airplane is Safe for flight. The pilot is also responsible for remaining within the Operating limitations as outlined by instrument markings, placards, and 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 Operating reference. The pilot should study the entire handbook to familianze himself , with the limitations, Performance. procedures and operational handlin, 1 characteristics of the airplane before flight. \$ -. , 1 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 proce- dures, Performance and other sections to provide easier access to informa- tion that may be required in flight. The “Emergency Procedures” Section has been fumished 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: NOVEMBER 30,1978 REPORT: VB-930 1-1 GENEHAL YA-ZöK 1-2U1, AKKU W 1 V Wing Arca (sq. ft.) . 170.0 Min. Turning Radius (ft.) 31.0 (from pivot point to wingtip) THREE VIEW Figure 1 - 1 .. . ,‘.-.. ! REPORT: VB-930 1-2 ISSUED: NOVEMBER 30,1978 Pl’IPEIP AlHCRAFT COHYORATION PA-28RT-201, ARROW IV SECTION 1 GENERAL 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 _, (i) Engine Type 1.5 PROPELLERS McCAULEY (a) Number of Propellers (b) Propeller Manufacturer (c) Blade Model (d) Number qf Blades (e) Hub Model ( f ) Propeller Diameter (in.) ( I ) .Maximum (2) Minimum (8) Propeller Type ISSUED: NOVEMBER 30, 1978 REVISED: JULY 29. 19811 1 I Lycoming 200 2700 5.125 4.375 36 I 8.5: 1 Four Cylinder, Direct Opposed. Air Cooled and Fuel Injected 10-360-C I C6 I Drive, Horizontally . > 1 McCauley 90DHA- 16 2 B2D34C2 13 74 73 Constant Speed, Hydraulically Actuated U I 2 ) REPORT: VB-930 1-7 . _ - -- - GENERAL PA-28RT-201, ARRÖ W IV HARTZELL (a) Number of Propellers (b) Propeller Manufacturer (c) Blade Model (d) Number of Blades (e) Hub Model (f) Propeller Diameter (in.) (1) Maximum (2) Minimum (g) Propeller Type I j 1.7 FUEL (a) Fuel Capacity (U.S. gal.) (total) (b) Usable Fuel (U.S.gal.) (total) (c) Fuel Grade, Aviation ( I ) Minimum Octane (2) Specified Octane (3) Alternate Fuels 1.9 OIL (a) Oil Capacity (U.S.qts.) (b) Oil Specification (c) Oil Viscosity 1 H artzell 2 HC-CZYK-l( ) F F7666A-2R i 74 72 Constant Speed, Hydraulically Actuated 77 72 100/130 - G r t a 100 - Green, 100 LL - Blue or lOO/ 130 - Green Refer to latest revision Instruction 1070 I Of LyCOUlillg SeNiCe 8 Refer to latest issue of Lycoming Service Refer to Section 8 - Paragraph 8.19 Instruction 1014 ) i .., . I : REPORT: VB -930 ! 1 - 4 ISSUED: NOVEMBER 30,1978 PIPER AIRCRAFT CORPORATION PA-28RT-201, ARRO W IV SECTION.1 GENERAL ' 1.11 MAXIMUM WEIGHTS (a) Maximum Takeoff Weight (lbs.) (b) Maximum Landing Weight (lbs.) (c) Maximum Weights in Baggage Compartment 1.13 STANDARD AIRPLANE WEIGHTS* (a) Standard Empty Weight (lbs.): Weight of a Standard airplane including unusable fuel, full Operating fluids and full oil. (b) Maximum Useful Load (lbs.): The difference between the Maximum Takeoff Weight and the Standard Empty Weight. 1.15 BAGGAGE SPACE (a) Compartment Voiume (Cu. ft.) (b) Entry Width (in.) (c) Entry Height (in.) 1.17 SPECIFIC LOADINGS (a) Wing Loading (Ibs. per sq. ft.) (b) Power Loading (lbs. per hp) 2750 2750 200 1627 1123 24 22 20 16.18 13.75 *These values are approximate and vary from one aircraft to anothcr. Refcr to Figure 6-5 for the Standard Empty Weight value and the Useful Load value to be used for C.G. calculations for the aircraft specified. ISSUED: NOVEMBER 30,1978 REPORT: VB-930 1-5 Sir;LIlUN 1 GENERAL r x n n n a n L n n r A LWRL w n r a a a ~ ~ v PA-28RT-201, ARROW IV 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY i h e following definitions are of Symbols, abbreviations and termi- nology used throughout the handbook and those which may be of added operationai significance to the Pilot. (a) General Airspeed Terminology and Symbols CAS Calibrated Airspeed means the indicated Speed of an aircraft, corrected for Position and instrument error. Calibrated airspeed is equai to true airspeed in Standard atmosphere at sea leveL KCAS Caiibrated Airspeed expressed in "Knots." GS IAS Ground Speed is the Speed of an airplane relative to the ground. Indicated Airspeed is the Speed of an ak- craft as shown On the airspeed indicator when corrected for instrument error. IAS values published in this handbook assume Zero instrument error. KIAS Indicated Airspeed expressed in "Knots." M TAS VA VFE REPORT: VB-930 * 1-6 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 aerodynamic control will not overstress the airplane. Maximum Flap Extended Speed is the highest Speed permissible with wing flaps in a prescribed extended Position. ISSUED: NOVEMBER 30,1978 PIPER AIRCRAFT CORPORATION SECTIOM 1 PA-28RT-201, ARRO W IV GENERAL VLE VLO 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. VNE/MNE Never Exceed Speed .or Mach Number is the Speed limit that may not be exceeded at any time. VNO vs vso vx VY 6, , thr' 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-Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance. Best Rate-of-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time. 1 b. ISSUED: NOVEMBER 30,1978 REPORT: VB-930 . L ) GENEKAL l'A-ZöKl-ZU1, AKKUW 1 V I i (b) Meteorological Terminology ISA OAT Indicated 'Pressure Altitude Pressure Altitude Station Pressure Wind REPORT: VB-930 1-8 - . . International Standard Atmosphere in which: i h e air is a dry perfect gas; The temperature at sea level is 15O Celsius (59" Fahrenheit); The pressure at sea level is 29.92 inches Hg (1013 mb); The tempera- ture gradient from sea level to the altitude at which the temperature is -56.5OC (-69.7"F) is -0.00198°C (-0.003566OF) 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 barometnc s u b s d e has been set to 29.92 inches of mercury (1013 millibars). Altitude measured from Standard sea-level pressure (29.92 in. Hg) by a pressurc or barometnc altimeter. It is the indicated pressure altitude corrected for Position and instrument error. In this handbook, altimeter instrument crrors are assumed to be Zero. I '. --. Actual atmospheric pressure at field elevation. The wind velocities recorded as variables on the Charts of this handbook are to be under,stood as the headwind or tailwind components of the reported Winds. ISSUED: NOVEMBER 30,1978 I PIPER AIRCRA&1 C'OHPO R ATI Oh' PA-28RT-201, ARRO W IV SECTION 1 GENERAL (c) Power Terminology Takeoff Power Maximum Con- tinuous Power Maximum Climb Power Maximum Cruise Power Maximum power permissible for takeoff. Maximum power permissible continuously during flight. Maximum power permissible during climb. Maximum power permissible during. cruise. P (d) Engine Instruments EGT Gauge Exhaust Gas Temperature Gauge (e) Airplane Performance and Flight Planning Terminology Climb Gradient The demonstrated ratio of the changc in height during a Portion of a climb, to the horizontal distance traversed in the Same time interval. Demonstrated Crosswind Velocity The demonstrated crosswind velocity is the velocity of the crosswind component for which adequate control of thc airplane during takeoff and landing was actuaiiy demonstrated during ceriification tests. Accelerate -Sto p Distance plane to a specified Speed and, assuming , The distance required to accelerate an air- failure of an engine a t t h t instant that specd is attained, to bring the airplane to a stop. MEA Minimum en route IFR aititude. Route Segment A p a n of a route. Each end of that part is identified by: ( I ) a geographical location; or (2) a Point at which a definite radio fnc can be estabiished. ISSUED:NOVEMBER 30,1978 REPORT: VB-930 1-9 r 1 r L K AIKLKAP I LUKYUKAllON PA-28RT-201, ARROW IV ( f ) Weight and Balance Terminology Reference Datum Station Moment Center of Gravity (C.G.) C.G. Arm C.G. Limits . ,. Usable Fuel Unusabie Fuel Standard Empty Weight REPORT: VB-930 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. i h e 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: NOVEMBER 30,1978 6.. , PIPER AIRCRAFT CORPORATION SECTION 1 PA-28RT-201, ARRO W IV GENERAL Basic Empty Standard empty weight plus optional Weight equipment. Payload Useful Load Maximum Ramp Weight Maximum Takcoff Weight Maximum Landing Weight 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 Zero Fuel Weight Maximum weight exclusive of usable fuel. ISSUED: NOVEMBER 30, 1978 REPORT: VB -930 1-11 SECTION .I GENERAL PiPEH ALRCRAFT CORPORATION PA-28RT-201, ARROW IV 1.21 CONVERSION FACTORS M ULTIPLY acres atmospheres (atm) bars (bar) British Thermal Unit (BTU) centimeters (cm) ' centimeters of mercury at . 0°C (cm Hg) centimeters per second ,'fcm/ sec-) cubic centimeters (cm ; REPORT: VB-930 1-12 BY 0.4047 43560 0.0015625 76 29.92 1.0133 1.033 14.70 2116 0.98692 14.503768 0.2519958 0.3937 0.032808 0.01316 0.3937 0.1934 27.85 135.95 0.032808 1.9685 0.02237 0.03381 0.06102 3.531 x 10 -5 0.00 1 2.642 x 10 -' TO OBTAIN ha sq. ft. sq. mi. cm Hg in. Hg bar kg/cm 2 Ib./sq. in. lb./sq. ft. atm lb./sq. in. kg-cal in. f t atm in. Hg Ib./sq. in. lb./sq. ft. kglm ft. / sec. ft. / min. mPh fl. 02. CU. in. CU. ft. 1 U.S. gal. ISSUED: NOVEMBER 30,1978 M U LTIPLY cubic feet (CU. ft.) cubic feet per minute (CU. ft. / min.) <' ,, inches (CU. in.) cubic meters (rn 3) cubic meters per minute (m 3/ min.) cubic yards (CU.yd.) '*q ;s (arc) degiees per second ' d I (deg./sec.) drams, fluid (dr. fl.) drams, avdp. (dr. avdp.) ISSUED:NOVEMBER 30,1978 BY 28317 0.0283 17 1728 0.037037 7.48 1 28.32 0.472 0.0283 17 16.39 1.639 x 10 - 5 5.787 x 10 -4 0.5541 0.01639 0.01732 6 1024 1.308 35.3147 264.2 35.3147 4.329 x 10 - 3 27 0.7646 202 0.01745 0.0 1745 0.125 0.0625 TO OBTAIN cm 3 m 3 CU. in. CU. yd. . . u.s; gal. ' 1 1 /sec. m 3 / min. cm 3 m 3 CU. ft. fl. 0% 1 . , . U.S. gal. U.S. qt. CU. in. CU. yd. CU. ft. U.S. gaL CU. ft./min.. I CU. ft. .rn 3 U.S. gal. . ', radians radianslsec. fl. 02. oz. avdp. REPORT: VB-930 . ' .I-13 , .,,.,-' . . . . . . . , . . SLCi’iON 1 GENERAL YiYEH AIHCRAFT CORPORATION PA-28RT-201, ARROW IV MULTIPLY feet (ft.) feet per minute (ft./ min.) feet per second (ft. / sec.) foot-Pounds (ft.-lb.) foot-Pounds per minute (ft.-lb./ min.). foot-Pounds per second (ft.-lb./sec.) gallons, Imperial (Imperial gal.) gallons, U.S. dry (U.S.gal. dry) REPORT: VB-930 1 - 14 BY 30.48 0.3048 12 0.33333 0.060606 1 1.894 x 10 -4 1.645 x 10 -4 0.01 136 0.0 1829 0.508 0.00508 0.6818 1.097 30.48 0.5921 0.138255 3.24 x 10 -4 3.030 x 10 - 5 1.818 x 10 - 5 277.4 1.20 1 4.546 268.8 1.164 4.405 1.556 x 10 - 1 TO OBTAIN cm m in. Yd. rod mi. NM mph ,-- km/hr. L. cm/ sec. m/ sec. mPh km/ hr. an/sec. kts. m-kg kg-cal CU. in. U.S.gal. 1 CU. in. CU. ft. U.S. gal. 1 J ISSUED: NOVEMBER 30,1978 PIPEH AIHCRAE'T CUPPOWATION PA-28RT-201, ARRO W IV SECTION 1 GENERAL MULTIPLY BY T O OBTAIN 23 1 0.1337 4.951 x 10 -3 3785.4 3.785 x 10 -3 3.785 0.83268 128 CU. in. CU. ft. CU. yd. cm 3 m 3 1 Imperial gal. fl. 02. gallons, U.S. liquid (U.S.gal.) gailons per acre I ' (gai./ acre) 9.353 I / h a 0.001 0.3527 2.205 x 10 -3 kg 02. avdp. Ib. grams per centimeter (s/ cm) grams per cubic centimeter (g/cm 3) 0.1 6.721 x 10 -2 5.60k x 10 -3 kg/ m Ib./ft. Ib./in. kg/m lb./cu. in. Ib./cu. ft. 1000 0.03613 62.43 hectares (ha) 2.47 1 107639 10000 acres m 2 ' sq. ft. horsepower (hp) 1" -j 33000 550 76.04 1.014 ft.-lb./ min. ft.-lb. / sec. m - kg/ sec. metric hp 75 0.9863 horsepower, metric m-kg/sec. hP inches (in.) 25.40 2.540 0.0254 0.08333 0.027777 mm cm m ft. Yd. ISSUED: NOVEMBER 30, 1978 REPORT: VB-930 1-15 GENERAL PA-28RT-201, ARRO W IV M ULTIPLY BY TO OBTAIN inches of mercury at O°C (in. Hg) 0.033421 0.49 12 70.73 345.3 2.540 25.40 atm lb./sq. in. 1b.lsq. ft. kg/m cm Hg mm Hg inch-Pounds (in.-lb.) kilograms (kg) 0.01 1521 m-kg 2.204622 35.27 1000 lb. 02. avdp. g kilogram-calories (kg-cal) 3.9683 3087 426.9 BTU m-kg lb./cu. ft. ft.-lb. g/cm ’ kilograms per cubic meter (kg/m 3, (kg/ ha) kilograms per hectare kilograms per square centimeter (kg/cm 2) 0.06243 0.001 ! 0.892 lb. / acre 0.9678 28.96 14.22 2048 atm in. Hg lb./sq. in. lb./sq. ft. kilograms per square meter (kg/m 2) 2.896 x 10 - 3 in. Hg 1.422 x 10 -3 lb./sq. in. 0.2048 lb./sq. ft. kilometers (km) 1 x 10-5 cm 3280.8 ft. 0.6214 mi. 0.53996 N M i ISSUED: NOVEMBER 30,1978 REPORT: VB - 930 1-16 MULTIPLY kilometers per hour (km / hr.) knots (kt) liters (1) liters per hectare (1/W (1 /sec.) liters per second meters (m) / meter-kilogram ( m - W ., meters per minute (mlmin.)i ISSUED: NOVEMBER 30,1978 BY 0.91 13 58.68 0.53996 0.6214 0.27778 16.67 1 1.689 1.1516 1.852 5 1.48 1000 6 1.02 0.0353 1 33.814 0.2641 72 0.2200 1.05669 13.69 0.107 2.12 39.37 3.280840 1.0936 0.198838 6.214 x 10 -4 5.3996 x 10 -4 7.23301 86.798 0.06 TO OBTAIN ft. / sec. ft. / min. kt mPh m /sec. m/ min. nautical mph ft./sec. statute mph km/ hr. m/ sec. cm’ CU. in. CU. ft. fl. 02. U.S. gaL Imperial gal. 9t. fl. oz./acre gal. / acrt CU. ft./min. in. ft. Y d. rod mi. NM ft.-lb. in.-lb. km/ hr. REPORT: VB-930 1-17 SECTION i GENERAL PlPEH AIHCKAFT CORPORATION PA-28RT-201, ARROW IV MULTIPLY BY TO OBTAIN ft. I sec. ft. I min. mPh km/ hr. meters per second (mlsec.) 3.280840 196.8504 2.237 3.6 microns miles, statute (mi.) 3.937 x 10 -5 in. 5280 1.6093 1609.3 0.8684 ft. km m NM miles per hour (mph) 44.7041 4.470 x 10 - 1 I .467 88 1.6093 0.8684 cml sec. m/sec. ft./sec. ft./ min. km/ hr. kt miles per hour Square (mlhr. sq.1 2.151 ft./sec. sq. millibars 2.953 x 10 -2 in. Hg millimeters (mm) 0.03937 in. millimeters of mercury at O°C (mm Hg) 0.03937 in. Hg " . ft. statute mi. m km g dr. avdp. nautical miles (NM) 6080 1.1516 1852 1.852 Ounces, avdp. (oz. avdp.) 28.35 16 I \ REPORT: VB - 930 1-18 ISSUED: NOVEMBER 30,1978 PIPER AIRCRAFT CORPORATION SECTION 1 PA-28RT-201, ARRO W IV GENERAL MULTIPLY Ounces, fluid (fl. 02.) BY TO OBTAIN 5 : dr. fl. cm 3 CU in. 1 U.S. gal. l / h a 8 29.57 1.805 0.0296 0.0078 Ounces, fluid per acre (fl. oz./acre) Pounds (Ib.) 0.073 0.453592 453.6 3.108 x 10 -2 kg slug g Pounds pcr acre (lb. I acre) Pounds per cubic foot (lb./cu ft.) (lb./cu in.) pounds per cubic inch 1.121 16.02 1728 27.68 lb./cu. ft. glcm Pounds per Square foot (lb./sq. ft.) 0.1414 4.88243 4.725 x 10 - 4 . . .. in. Hg kg/m atm Pounds per Square inch 5.1715 (Psi or lb./sq. in.) 2.036 0.06804 0.0689476 703.1 -, I' cm Hg in. Hg atm bar kg/m 1 CU. in. J quart, U.S. (qt.) 0.94635 57.749 radians 57.30 0.1592 deg. (arc) rev. radians per second (radiansl sec.) 57.30 0.1592 9.549 deg./sec. d rev. / sec. h' rPm i ISSUED: NOVEMBER 30,1978 REPORT: VB-930 i - * n ------ - --------.L-.V.. GENERAL PA-28RT-201, ARRO W IV MULTIPLY revolutions (rev.) revolutions per minute (rpm or rev./min.) revolutions per second (rev. /sec.) rod \ slug square centimeters (cm 2, Square feet (sq. ft.) Square inches (sq. in.) ' Square kilometers (km 9 Square meters (m 2) \ Square miles (sq. mi.) Square rods (sq. rods) square yards (sq, yd.) REPORT: VB-930 1-20 BY 6.283 0.1047 6.283 16.5 5.5 5.029 32.174 0.1550 0.00 1076 929 0.092903 144 0.1111 2.296 x 10 -5 6.45 16 6.944 x 10 -3 0.3861 10.76391 1.196 0.0001 2.590 640 30.25 0.8361 9 0.0330579 TO OBTAIN radians radiansl sec. radianslsec. ft. Yd. m Ib. sq. in. sq. ft. cm 2 m 2 sq. in. acrts sq. 'yd. cm 2 sq. ft. sq. mi. sq. ft. sq. yd. ha km 2 acrcs sq. yd. m 2 sq. rods sq. ft. ISSUED: NOVEMBER 30,1978 \ I ,J PIPER AIRCRAFT CORPORATION SECTION I PA-28RT-201, ARROW IV GENERAL M ULTIPLY yards (yd.) , )’ j ISSUED: NOVEMBER 30,1978 BY 0.9 144 3 36 0.181818 TO OBTAIN m ft. in. rod REPORT: VB-930 1-21 ,i . . ’- Paragraph No. 2.1 2.3 2.5 2.7 2.9 2.1 1 2.13 (’ 2.15 2.17 2.19 2.21 2.23 2.25. TABLE OF CONTENTS SECTION 2 LIMITATIONS Page No. General ... ......... ....... ........ ............... Ainpeed 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 .......... .... ........ ..... ....... . Noise Level . ........ .... .... ... .. ... .. ............ Placards.. ... .. .... ... .. .... .......... ....... ..?. . 2-1 2-1 2-2 2-3 2 4 . , 2-5 .: 2-5 2-5 2-6 2-6 2 -6 2-7 2 -8 I . . REPORT: VB-930 2-1 PIPE# AIRCRAFT CORPORATION SECTION 2 PA-28RT-201, ARRO W IV LIMITATIONS 2.1 GENERAL SECTION 2 LIMITATIONS This section provides the "FAA Approved " Operating limitations, instrument marfings, color coding and basic placards necessary for the Safe Operation of the airplane and its Systems. c Mtations associated with those opuonai Systems and equipment which rcquire handbook Supplements can be found in Section 9 (Supplements). 2 3 AIRSPEED LIMITATIONS SPEED KIAS KCAS Nevcr Exceed Speed (VNE) - Do not exceed this specd in any Operation. _> 190 186 'i Maximum Structural Cruising Speed (WO)- Do not excccd this speed except in smooth air and then only with caution. 149 148 I < . Design Maneuvenng Speed (VA) - Do not * 1 . ' make full or abrupt control movements w above this speed. At 2750 lbs. G.W. 121 121 ! At 1863 lbs. G.W. 96 97 . I CA UTION Maneuvenng speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced. Linear interpolation may be used for intermcdiate gross weights. Maneuver- ing speed should not be exceeded while opera- ting in rough air. i ISSUED: NOVEMBER 30,1978 REPORT: VB-930- - - SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA-28RT-201, ARROW IV SPEED KIAS KCAS Maximum Flaps Extended Speed (VFE)- extended. 108 104 f Do not exceed this speed with the flaps 1. Maximum Landing Gear Extension Speed - Do not exceed this speed when extending the landing gear. 130 130 Maximum Landing Gear Retraction Speed - Do not exceed this speed when retracting 3the landing gear. 109 109 Maximum Landing Gear Extended Speed (VLE)- Do not exceed this speed with the landing gear extended. 130 130 2.5 AIRSPEED INDICATOR MARKINGS MARKING Red Radial Line (Never Exceed) Yellow Arc (Caution Range - Smooth Air Only) . Green Arc (Normal Operating Range) White Arc (Flap Down) REPORT: VB-930 2-2 IAS 190 KTS 149 KTS to 190 KTS 58 KTS to 149 KTS 53 KTS to \ 108 KTS . 1 ISSUED: NOVEMBER 30,1978 PIPER AIRCRAFT CORYOXATION SECTION 2 PA-28RT-201. ARROW IV LIMITATIONS 2.7 PO WER PLANT LIMITATIONS I (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 I Minimum (red line) \ \ Maximum (red line) Minimum (red line) Maximum (red line) (0 Fuel Pressure (g) Fuel Grade (minimum octane) (h) Number of Propellers (i) Propeller Manufacturer Ci) Propeller Hub and Blade Model (1) McCauley (2) Hartzell i (k) Propeller Diameter ( I ) McCauley Minimum Maximum Minimum Maximum (1) Blade Angle Limits ( I ) McCauley Low Pitch Stop High Pitch Stop Low Pitch Stop High Pitch Stop (2) Hartzell (2) Hartzell 1 Lycoming 10-360-C1C6 I 200 2700 245" F 25 PSI 100 PSI I 14 PSI 45 PSI lOO/ 130 - Green 1 McCauley or Hartzell B2D34C213/90DHA-16 HC-C2YK-l( )F/ F7666A-2R 73 74 72 74 12.5 f 0.2" 27.5 f 0.5" 14.0 +, 0.2" 29.0 t 2.0" ISSUED: NOVEMBER 30,1978 REVISED: JULY 29,1980 REPORT: VB-930 2-3 LIMIXAXJONS YA-ZöKl-201, ARRO W IV (m) RPM Restrictions (McCauley Avoid Continuous Propeller Only) Operation Between 1500 and 1950 RPM Below 15 Inches Map. 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) Red Line (Maximum) Green Arc (Normal Operating Range) Yellow Arc (Caution Range) (Idle) Red Line (Minimum) Red Line (Maximum) Green Arc (Normal Operating Range) Red Line (Minimum) Red Line (Maximum) (c) Oil Pressure (d) Fuel Pressure 75O to 245°F 245O F 60 PSI to 90 PSI 25 PSI to 60 PSI 25 PSI 100 PSI 14 PSI to 45 PSI 14 PSI 45 PSI I REPORT: VB-930 2-4 ISSUED:NOVEMBER 30,1978 REVISED: JULY 29,1980 IP#-28HT-201, ARRO W 1V LIMITATIONS Weight Pounds 2750 2400 2.11 WEIGHT LIMITS Forward Limit Reanvard Limit Inches Aft of Datum Inches Aft of Datum 90.0 93.0 85.5 93.0 (a) Maximum Weight (b) Maximum Baggage NOTE Refer to Section 5 (Performance) for maximum weight as limited by Performance. 2.13 CENTER OF GRAVITY LIMITSI 2750 LBS. 200 LBS. NOTES Straight line Variation between Points given. 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. 1 2.15 MANEUVER LIMITS ' No acrobatic maneuvers including Spins approved. ISSUED: NOVEMBER 30,1978 REPORT: VB-930 2-5 SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA-28RT-201, ARROW IV 2.17 FLIGHT LOAD FACTORS (a) Positive Load Factor (Maximum) (b) Negative Load Factor (Maximum) No inverted maneuvers ( 3.8 G approved 2.19 TYPES OF OPERATIONS The airplane is approved for the following Operations when equipped in accordance with FAR 91 or FAR 135. \ (a) Day V.F.R. (b) Night V.F.R. (c) Day I.F.R. (d) Night I.F.R. (e) Non Icing 2.21 FUEL LIMITATIONS (a) Total Capacity (b) Unusable Fuel 77 U.S. GAL. 5 U.S. GAL. The unusable fuel for this airplane has been determined as 2.5 gallons in each wing tank in critical flight attitudes. 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. (c) Usable Fuel 72 U.S. GAL. REPORT: VB-930 -, ISSUED: NOVEMBER 30, 1978 YlYYK AlKLKAb 1 LlJfirUtrAiiui.i PA-28RT-201, ARRO W 1V um%.b b W & . I LIMITATIONS 2.23 NOISE LEVEL The noise level of Chis aircraft is 75.5 d B(A). No determination has been made by the Federal Aviation Administra- tion that the noise levels of this airplane are or should be acccptable or unacceptable for Operation at, into, or out of, any airport. The above Statement not withstanding the noise level stated abovc has been verified by and approved by the Federal Aviation Administration in noise level test flights conducted in accordance with FAR 36, Noisc Standards - Aircraft Type and Ainvorthiness Certification. This aircra’ model is in compliance with all FAR 36 noise Standards applicable to th, tY Pe- ISSUED: NOVEMBER 30,1978 REPORT: VB-930 2-7 3 b b A l U i l L LIMITATIONS r l r L K A l K L K A P A LUKrtJRAAlUll PA-28RT-201, ARRO W IV 2.25 PLACARDS In full view of the Pilot: THIS AIRPLANE MUST BE OPERATED AS A NOR - MAL CATEGORY AIRPLANE IN COMPLIANCE WITH T H E OPERATING LIMITATIONS STATED IN THE FORM O F PLACARDS, MARKINGS AND MANUALS. THIS AIRCRAFT APPROVED FOR NIGHT I.F.R. NON - ICING F L I G H T WHEN E Q U I P P E D I N ACCORDANCE WITH FAR 91 OR FAR 135. 1 In full view of the Pilot, the following Takeoff and Landing Check Lists wili be installed: TAKEOFF CHECK LIST 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 CHECK LIST Fuel on Proper Tank Scat Backs Erect Gear Down Fasten Belts/ Harness Electric Fuel Pump - On Mixture - Rich Propeller - Set Flaps - Set (White Arc) Air Conditioner - Off The "Air Conditioner Off " item in the above Takeoff and Landing Check Lists is mandatory for air conditioned aircraft only. On the instrument panel in full view of the Pilot: MANEUVERING SPEED 121 KIAS AT 2750 LBS. (SEE A.F.M.) ' I I ; . . REPORT: VB-930 ISSUED:NOVEMBER 30,1978 2-8 B'A~?~.XA i H C K A k I' c 0ldk'ciiCt-t i iOi\ SECTION 2 PA-28RT-201, A R R O W IV I,IMITATIONS O n thc instrurnent panel in full vicw of rhe Pilot: D E M O N S T R A T E D C R O S S W I N D C O M P O N E N T 17 KTS O n the instrurnent panel in full view of the pilot: /-' NO A C R O B A T I C M A N E U V E R S . I N C 1 - U D I N G S P I N S . A P P R O V E D O n the instrurnent panel in full vicw of t h e pilot: G E A R D O W N 1.70 K l A S ( M A X . ) G E A R UP 109 K l A S ( M A X . ) E X T E N D E D 1.70 K l A S ( M A X . ) Near ernergency gear lever: E M E R G E K C Y D O W N Near ernergency gear lever (aircraft equipped with b a c k u p g e a r extender) I/-- O V E R R I D E E N G AG E D A U T O - E X T - O F F LOCK P I K ON S l D E TO E N G A G E O V E R R I D E : P U L L 1.EVER FU1.L U P . P U S H LOCK P I K TO R E L E A S E O V E R R I D E : PULL. L E V E R F U L L U P & R E L E A S E Near gear selector switch: G E A R U P 109 K l A S M A X . 1 D O W N 130 K I A S M A X . . . / Adjacent to upper d o o r latch: E N G A G E i . A T C H B E F O R E F I . I G H T ..- ISSI:ED: NOVEMBER 30, 1978 REVISED: J A N U A R Y 31. 1987 REPORT: VB - 930 2-9 SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA - 28RT - 201, ARROW IV O n the instrument panel in full view of the pilot: W A R N I N G T U R N OFF S T R O B E L I C H T S W H E N IN C L O S E P R O X I M I T Y TO G R O U N D O R D U R I N G F L I C H T T H R O U G H C L O U D , F O G OR HAZE. I n full view of the pilot, in the area of the air conditioner controls when the air conditioner is installed: W A R N I N G A I R C O N D I T I O N E R M U S T BE OFF TO I N S U R E N O R M A L T A K E O F F C L l M B P E R F O R M A N C E . O n inside of baggage compartment door: B A G G A G E M A X I M U M 200 LBS. S E E W E I C H T A N D T W E E N 150 LBS. A N D 200 LBS. B A L A N C E D A T A F O R B A G G A G E L O A D I N G BE- Adjacent to fuel tank filler caps: F U E L - iOO/ 130 AVlATlON G R A D E - MIN. USABLE C A P A C I T Y 36 GAL. U S A B L E C A P A C I T Y TO BOTTOM OF F I L L E R N E C K I N D I C A T O R 25 GAL. Above fuel quantity gauges: F U E L R E M A I N I N G W H E N QUANTITY I N D I C A T O R R E A D S Z E R O C A N N O T BE U S E D S A F E L Y IN F L I C H T . REPORT: VB - 930 2-10 ISSUED: NOVEMBER 30. 1978 PIYER AIRCRAFT CORYORATION SECTIt PA-28RT-201, ARROW IV LIMITATIl On the instrument panel in full view of the pilot in aircraft 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. ISSUED: NOVEMBER 30,1978 REPORT VB I TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Pa. . N o . No. 3.1 3.3 3.5 3.7 3.9 3.1 1 3.13 3.15 3.17 3.19 3.21 3.23 3.25 3.27 3.29 3.3 1 3.33 General .......................................... 3-1 3-2 Amplified Ernergency Procedures (General) ........... 3-9 3-9 3-9 Engine Power Loss In Flight ........................ 3-10 Power Off Landing ................................ 3-11 Fire In Flight ..................................... 3-13 Loss of Oil Pressure ............................... 3-13 Loss of Fuel Pressure .............................. 3-14 High Oil Temperature .............................. 3-14 Alternator Failure ................................. 3-14 Propeller Overspeed .................................. 3-15 Emergency Landing Gear Extension .................. 3-15 Spin Recovery .................................... 3-16 Open Door ....................................... 3-16 Engine Roughness ................................. 3-16 Emergency Procedures Check List .................... Engine Fire Dunng Start ........................... Engine Power Loss During Takeoff .................. REPORT: VB-930 3-1 P l P E R AIRCRAFT CORPORATION SECTION 3 PA-28RT-201, A R R O W IV EMERGENCY P R O C E D U R E S SECTION 3 EMERGENCY PROCEDURES 3.1 GENERAL The recommended procedures for coping with various types G emergencies and critical Situations are provided by this section. All of the required ( F A A regulations) emergency procedures and those necessary for the Safe Operation of the airplane as determined by the Operating and design features of the airplane are presented. Emergency procedures associated with those optional Systems and equipment which require handbook Supplements are provided by Section 9 (Supplements). The first Portion of this section consists of an abbreviated emergency check list which supplies a n action sequence for critical Situations with little emphasis on the Operation of Systems. The remainder of the section is devoted to amplified emergency procedures containing additional information to provide the pilot with a more complete understanding of the procedures. These procedures are suggested as the best Course of action for coping with the particular condition described. but are not a Substitute for sound judgment and common sense. Since emergencies rarely happen in modet aircraft. their occurrence is usually unexpected and the best correctiv., ' action rnay not always be obvious. Pilots should familiarize thernselves with the procedures given in this section and be prepared to take appropriate üction should an emergency arise. Most basic emergency procedures. such as power O f f landings. are a normal part olpilot training. Although these emergencies arediscussed here, this information is not intended to replace such training. but only to provide a source of rel'erence and review. and to provide information on procedures which üre not the Same for all aircraft. I t is suggested that the pilot review Standard emcrgency procedures periodically to rernain proficient in them. ISSGED: N O V E M B E R 30. 1978 REPORT: VB-930 3- 1 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA - 28RT - 201, ARROW IV 3.3 EMERGENCY PROCEDURES CHECK LIST ENGINE FIRE DURING START Starter.. ............................................. crank engine Mixture .............................................. idle Cut-Off Throttle ................................................... Open Electric fuel pump .......................................... OFF Fuelselector ............................................... OFF Abandon if fire continues. ENGINE POWER LOSS DURING TAKEOFF lf sufficient runway remains for a normal landing, leave gear down and land straight ahead. If area ahead is rough, or if it is necessary to clear obstructions: Gear selector switch ........................................... UP Emergency gear lever (aircraft equipped with backup gear extender) ...................... .locked in OVERRlDE ENGAGED Position I If sufficient altitude has been gained to attempt a restart: Maintain Safe airspeed. Fuel selector ....................................... switch to tank containing fuel Electric fuel pump ...................................... check ON Mixture ............................................ .check RlCH Alternate air .............................................. OPEN Emergency gear lever ................................... as required If power is not regained. proceed with power O f f landing. 1 ENGINE POWER LOSS IN FLICHT Fuel selector ....................................... switch to tank containing fuel Electric fuel pump ........................................... ON Mixture ..................................................RlCH Alternate air .............................................. OPEN Engine gauges .. ;. ............................. check for indication of cause of power loss' If no fuel pressure is indicated. check tank selector Position to be Sure it is on a tank containing fuel. REPORT: VB - 930 3-2 ISSUED: NOVEMBER 30, 1978 REVISED: JANUARY 31, 1987 YlPEH AIHCHAF'I' CORPORATION SECTION 3 PA-28RT-201, ARROW IV EMERGENCY PROCEDURES When power is restored: Alternate air ........................................... CLOSED Electric fuel pump .......................................... OFF lf power is not restored prepare for power Off landing. Trim for 79 KlAS. ...... POWER OFF LANDING On aircraft equipped with the backup gear extender, lock emergency gear lever in OVERRlDE ENGAGED Position before airspeed drops to 105 KlAS to prevent the landing gear from free falling. ' )nm for 79 KlAS. Locate suitable field. Establish spiral Pattern. 1000 ft. above field at downwind Position for normal landing approach. When field can easily be easily reached slow to 72 KlAS for shortest landing. GEAR DOWN EMERGENCY LANDING Touchdowns should normally be made at lowest possible airspeed with full flaps. When committed to landing: ianding gear selector ..................................... DOWN I Throttle ................................................... close Mixture .............................................. idle cut-Off lgnition ................................................... OFF Master switch .............................................. OFF Fuel selector ............................................... OFF Seat belt and harness.. ....................................... tight TEAR UP EMERGENCY LANDlNG ~ / J In the event a gear up landing is required, proceed as follows: Flaps ................................................. as desired I Throttle ................................................... close Mixture .............................................. idle cut-Off Master switch .............................................. OFF Fuel selector ............................................... OFF Seat belt and harness.. ....................................... tight Contact surface at mini.mum possible airspeed. . . . lgnition switches.. .......................................... OFF ISSUED: NOVEMBER 30,1978 REVISED: JANUARY 31,1987 REPORT: 930 3 - 3 SECTION 3 PIPER AIRCRAFT CORPORATION EMERCENCY PROCEDURES PA - 28RT - 201, ARROW IV FIRE IN FLICHT Source of fire ............................................... check Electrical fire (smoke in cabin): Master switch .............................................. OFF Vents ....................................................... Open Cabin heat ................................................. OFF Land as soon as practicable. I ... i: Engine fire: Fuel selector ............................................... OFF Throttle ............................................... CLOSEL Mixture .............................................. idle C u t - O f f Electric fuel pump .................................... .check OFF Heater and defroster ........................................ OFF Proceed with power O f f landing procedure. LOSS OF OIL PRESSURE Land as soon as possible and investigate cause. Prepare for power O f f landing. LOSS OF FUEL PRESSURE Electric fuel pump ........................................... ON Fuel selector ................................... .check on full tank REPORT: VB - 930 3-4 ISSUED: NOVEMBER 30. 1978 PA-28RT-201, A K K O W IV EMEKCENCY PROCEDURES HIGH 011, TEMPERATURE Land at nearcst airport and investigatc thc problcm. Y r c p a r c for powcr ofC landing. ALTERNATOR FAILURE Vcrify failure. Reduce elecirical load as niuch as possiblc. Altcmator circuit breakers ........................................................................... check Alt switch .............................................................................. OFF (for I second), thcn on 11 no'output: Alt switch ....................................................................................................... OFF / --- Rcducc electrical load and land as soon as practical. II' battery is fully discharged, thc gear will have to be lowcred using the etncrgency gear extension procedure. Position lights will not illuminate. -! wi'ROPELLER OVEHSPEED Tiirottle ........................................................................................................ rc tard Oil prcssure .................................................................................................. check Prop control ....................................................................... full DECKEASE rpm, then set if any control available Airspced ...................................................................................................... rcduce Throttle ................................................................................ as requircd to rcrnain bclow 2700 rpm i i ISSUED:NOVEMIIER 30,1978 REPORT VB -930 3-5 i I I I ! 1 ,j SECTION 3 PlPER @CKAFT CORYORATION EMERGENCY PROCEDURES PA-28RT-201, ARROW 1V EMERGENCY LANDING CEAH EXTENSION Prior io emergency exicnsion procedure: Masicr swiich ........................................................................................ chcck OP Circui i breakcrs ............................................................................................ check Panel lights ................................................................................ OFF (in daytimc) Gear indicator bulbs ..................................................................................... c h c c ~ i I f landing gcar docs not chcck down and lock: Airspccd............................................................................ r~ducebelow 87 KIAS Landing gear selector swiich .............................................. gear DOWN Position If ge’ar has failed 10 lock down on aircraft equipped with thc backup geai extender. raise emergency gear lever to “Override Engaged” posiiion. I f gear has siill failed to lock down, move and hold the emergency lever down to the EMERGENCY DOWN Position. If gear has still4ailed 10 lock down, yaw ihe airplanc abruptiy from side 10 side with ihe ruddcr. ’’ . I I f the nose gear will not lock down using the above proccdure, slow the aircraft 10 thc lowesi Safe Speed attainable using ihe lowcst power Setting Emergency gear lever (On aircraft equipped with Landing gear selecior switch .............................................. gear DOWN Position If landing gear does not check down, rccycle gear ihrough up position, and ihen select gear DOWN. SPIN RECOVERY required for safc Operation and accomplish the following: . . . )ihe backup gear cxtender) ...................................... “OVERRIDE ENGAGED”‘-’ Rudder ........................................................................................... full oppositc to direciion of roiation Control whccl ........................................................................... full forward whilc \ neuiraiizing ai~crons ’ Throiile. ........................................................................................................... idlc Ruddcr ..................................................................... ncutral (wheri roiation siops) Conlrol whecl .................................................................. as required 10 smooihly rcgain levcl flight aitiiude OPEN DOOR I f boih upper and sidc latchcs are opcn, ihe door will trail slightly opcn an and airspceds will bc reduced slighily. KEPORT: VB-930 ISSUED: NOVEMBER 30,1978 3 -6 REVISED: SEPTEMBER 06,1996 PIPER AIRCRAFT CORPORATION SECTION 3 PA-28RT-201, ARROW IV EMERGENCY PROCEDURES To close the door in flight: Slow airplane to 87 KIAS. Cabin vents ........................................... ;. ... close Storm window.. ............................................ Open If upper latch is Open.. ...................................... iatch If side latch is Open ........................... pul1 on armrcst whiie moving latch handle to latched Position . . .. If both latches are Open.. ........................... latch side latch then top latch .,/ ', ISSUED: NOVEMBER 30,1978 REPORT VB-930 3-7 EMERCENCY PROCEDURES PA - 28RT - 201, ARROW IV !i ..'... ' I THIS PAGE INTENTIONALLY LEFT BLANK i i I , REPORT: VB-930 !/ 3-8 3 I ISSUED: NOVEMBER 30,1978 3.5 AMPLIFIED EMERGENCY P R O C E D U R E S (GENERAL) T h e following paragraphs a r e presented to supply additional ,' information f o r t h e purpose of providing the pilot wiih a more complete understanding of the recommended Course of action and probable cause of , a n emergency Situation. c3.7 ENGINE .FIRE D U R I N C S T A R T Engine fires during start a r e usually t h e result of overpriming. T h e first ttempt t o extinguish the fire is to try to start the engine and d r a w theexcess t'uel back into the induction.system. ... , If a fire is present before t h e engine has started. move t h e mixture control to idle Cut-off. Open the throttle a n d crank the engine. T h i s is a n attempt to d r a w the fire back into t h e engine. If the engine hasstarted. continue Operating to try to pul1 t h e fire into t h e engine. In either case (above). if fire continues m o r e t h a n a few seconds, t h e fire should be extinguished by the best available external means. T h e fuel selector valves should be OFF a n d the mixture a t idle Cut-Off if a n external fire extinguishing method is to be used. 3.9 ENGlNE POWER LOSS DURING TAKEOFF T h e proper action to be taken if loss of power occurs during takeoff will depend o n t h e circumstances of the particular Situation. If sufficient runway rernains to complete a n o r m a l landing. leave t h e ' landing g e a r d o w n and land straight a h e a d . If t h e a r e a ahead is rough. o r if it is necessary to clear obstructions. move the g e a r selector switch to the UP Position. O n aircraft equipped with t h e backup g e a r extender. lock the emergency g e a r lever in the O V E R R I D E IA. E N G A G E D Position. L ISSUED: NOVEMBER 30, 1978 REVISED: J A N U A R Y 31, 1987 REPORT: VB - 930 3 - 9 SECTION 3 PlPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28RT-201, ARROW IV I f sufficient altitude has been gained to attempt a restart. maintain a Safe airspeed and switch the fuel selector to another tank containing fuel. Place the electric fuel pump to ON. Check that the mixture is RICH. Thealtemate air should be OPEN. O n aircraft equipped with the backup gear extender. the landing gear will extend automatically when engine power fails at speeds below approximately 95 K IAS. The glide distance with the landing gear extended is roughly halved. If the Situation dictates. the landing gear can be retained in the retracted Position by locking the emergency gear lever in the OVERRIDE ENGAGED Position. I f 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 procedure (refer to the emergency check list and'paragraph 3.13). 3.11 ENGINE POWER LOSS IN FLICHT 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 emergencylanding (refer to Paragraph 3.13). An airspeed of at least 79 KlAS should be maintained. if aititude 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. I f no fuel pressure is indicated, check the tank selector Position to be Sure it is on a tank containing fuel. When power is restored move the alternate air to the " CLOSED " Position and turn OFF the electric fuel pump. I f the preceding steps d o not restore power. prepare for a n emergency land ing. I ;i _. REPORT: VB - 930 3 - 10 ISSUED: NOVEMBER 30, 1978 REVISED: JANUARY 31, 1987 B>ll'tI{ ,i[!?re,;F-. T ' > O - _ t'r'uq'i'lop SECTION 3 PA - 28RT - 201, ARROW I V EMERGENCY PROCEDURES I f time permits. t u r n t h e ignition switch to"l."then to "R"then back 10 " HOTH. " Move t h e throttle a n d mixture control levers to different Settings. This m a y restore power i f t h e Problem is too rich o r too lean a mixture o r if ,Jthere is a partial fuel system restriction. T r y the other fucl t a n k . W a t e r i n t h e fuel could take s o m e time to be used up. and allowing theengine to windmill m a y restore power. I f p o w e r loss is d u e to water. fuel pressure indications will be normal. l f cngine failurc w a s caused by fucl cxhaustion power will not b e restored after switching fuel tanks until the c m p t y fucl lines a r e filled. This m a y require u p to ten seconds. I 1 power is not rcgained. procecd with the Power Off 1.anding procedure ( d e r to emergency check list a n d Paragraph 3. I3), 3.13 POWER OFF LANDING I f loss of poLver occurs iit altitude. lock emergency g e a r lever i n " O V E R R I ' D E E N G A G E D " position beforc iiirspeed d r o p s to 105 K I A S 10. prc\.cnt thc landing g c a r f r o m inadvcrtcntl!, free f'alling on aircraft equipped Lvith t h c backup gear cxtcndcr. T r i m thc iiircriift for best gliding angle (79 KIAS. Air C o n d . off) a n d look for a suitablc field. I f measures taken to rcstore power a r c not cf'fecti\.e. a n d if time permits. check y o u r Charts f o r airports in thc immediate \.icinity: i t mny bc possible to land at o n e if ~ O U Iiaw siil'l'icicnt altitudc. At bcst gliding angle. with the engine windmilling. iind the propcllcr control in f i i I I D E C R E A S F . rpm. the aircraft will travel iippro'tirnatcly 1.6 milcs I'orcnch thoiisiind fcct ofaltitude. I f possible. n0tify thc F A A b!. radio ot' !xiiir difticiilt!, iind intcntions. If a n o t h e r Pilot o r pnsscngcr is iibonrd. 1r.t hin1 hclp. .. h 2 ..... iYhcn !uii h e \ v locatcd ;I siiitoblc ticld.cstablish ii spiral p a t t e m a r o u n d this l'icld. '1.r). 1 0 bc 111 1000 f'cct abo\.c thc licld a t the dotvnwind position. 10 ni:ikc ii norniiil Innding iippioiich. \Vhcn thc ticld c;in ciisil! be reachcd.slow to 7 7 K IAS \vith Ilnps do\vii for thc shortcst landinp. Escess altitude rnay be l o h t b!. \\.idciiiiig !.oiir pnttcrii. iihing llnps o r slipping. o r ;I c o m b i n a t i o n of I Ile\r.. ,) li'licthcr .to iiticiiipt ;I Iiinding \ v i t l i p i i r u p o r dinvn d e p e n d s on man! I'iictors. 1.1' tlic t'icld choscn is cib\.ioiisl!. sniooth iind lirm. a n d l o n p e n o u g h to briiig tlic plaiic to ;I stop. ilic gciir hhoiild bc do\vn. I f thcrc ;Ire s t u m p s o r r o c k 5 o r other Iiirgc obstnclcs in thc ticld. ihr. gcar in t h c d o w n position will bcttcr proicct tlic occiipnnt\ oftlir. aircrait. 11. ho\\.cvr.r. t h c iield is suspected 10 bc csccssiwl!. s o t t o r s1ioi.r. o r \vhcn Inndiiig in \\';itcr of an! depth. a \\-hccls-iip Iiiiidirig will iioriii;ill!~ hc siit'cr iiiid d o lcss diimngcto theairplane. 1,. '.: .._..I' ISSI'ED: IVOVEMBER 30. 1978 REi'ISED: J A N l ' A R Y 31. 1987 REPORT: VB - 930 3-1 1 LIVICKCICNL Y P K U L C U U K E S PA-28RT-201, A R R O W I V O n aircraft equipped with the backup gcar cxtcndcr. thc landing gcar Iwill free fall at airspeeds below approximately 95 KIAS. and will takc h i x 10 eight seconds to be down and locked. Ifa gear up landing is dcsircd. i t will bc necessary to lock theoverrideleverin t h c O V E R R I D E ENCiAGEDposition before the airspeed drops to 105 K l A S to prcvcnt thc Innding gcar I'rorn inadvertently free falling. Touchdown should normally bc madc ;I[ thc lowcst possiblc iiirspccd. (a) Gear Down Emergency I-anding When committed to a gear down emcrgcncy landing. closc thc throttle control and shut OFF the mastcr and ignition. switchcs. Flaps may be used as desired. Turn thc fucl sclcctor vuI\.c to'OFF and move the mixture to idlc cut-of'l'. Thc scat bclts and shouldcr harness (if installed) should be tightened. Touchdown should bc , normally made at the lowcst possiblc airspced. Always remember that the automatic gcar mcchanism will extend the gear below approximately 95 K l A S with power oll. He prepared to lock the emergency gear lever in thc O V E R R I D E ~ E N G A G E D Position before the airspeed drops to 105 K l A S tu prevent the landing gear from inadvertently f'rec f'alling. unlcss gear extension is desired. NOTE I f the master switch is OFF. thc gear cannot bc retracted. (b) Gear Up Emergency Iianding O n aircraft equipped with thc backup gcar extcnder. lock thc emergency gear lever in O V E R R I D E E K G A G E D Position bcforc theairspeed drops 10 105 K l A S to prevcnt the landinggcarlrom in- advertently free falling. Wing flaps should bc cxtcndcd 11sdcsircd. When committed to a gcar up landing. CI.OSE thc throttle and shut OFF the master and ignition switches. Turn OFF the _ , . fuel selector valve. ~ ,; I Touchdowns should normally bc miidc at thc lowcst possiblc airspeed with full flaps. REPORT: VB-930 3- 12 ISS1:ED: N O V E M B E R 30, 1978 REVISED: JAN1:ARY 31. 1987 , I'PlPER AIRCRAFT CORPORATION SECTION 3 PA-28RT-201, ARRO W IV EMER GEN CY PRO CEDURES t I - 3.15 FIRE IN FLIGHT ,:[.. 1:. The presence of fire is noted through smoke, smell and heat in the cabin. It is essential that the source of the fire be promptly identified through instrument readings, character of the smoke, or other indications since the action to be taken differs somewhat in each case. - -L- E L ----L Check for the source of the fire first. c- ----------- If an electrical fire is indicated (smoke in the cabin), the master switch should be turned OFF.The cabin vents should be opened and the cabin heat tumed 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 throttie. Thc mixture should be at idle cut-Off. Turn the electric fuel pump nication is not required select master switch OFF. If the terrain permits, a landing should be made immediately. I OFF.In all cases, the heater and defroster should be OFF.If radio commu- i I i NOTE . I- iThe possibility of an engine fire in fiight is I extremely remote. The procedure given is i gencrai and pilot judgmcnt should be the deter- mining factor for action in such an emergency. ? I 3.17 LOSS OF OIL PRESSURE Loss of oil pressure may be either partial or complete. A partial loss of oil pressure usuaily indicates a malfunction in the oil pressure regulating ) System, and a landing should be made as soon as possible to investigate the , c. , cause and prevent engine damage. A complete loss of oil pressure indication may signify oil exhaustion o r may be the result of a faulty gauge. In either case, proceed toward the nearest airpori, and be prepared for a forced landing. If the Problem is not a 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: NOVEMBER 30,1978 REPORT: VB-930 2-13 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28RT-201, ARROW IV Depending on the circumstances, it may be advisable to make an Off airport landing while power is still available, particularly if other indications of actual oil pressure loss, such as sudden increases in temperatures, or oil smoke, are apparent, and an airport is not close. ! If engine stappage occurs, proceed with Power Off Landing. 3.19 LOSS OF - FUEL PRESSURE The most probable cause of loss of fuel pressure iS either fuel depletion in the fuel tank selected, or failure of the engine driven fuel pump. If loss of fuel pressure occurs, check that the fuei selector is on a tank containing fuel and turn ON the electric fuel pump. ',.' ' If the problern is not an empty tank, land as soon as practicai and have the engine driven fuel pump and fuel. System checked. 3.21 HIGH' ,OIL TEMPERATURE An abnorrnaiiy high oil temperature indication may be caused by a low (I oil level, an obstruction in the oil cooler, damaged or improper baffie scals, a defective gauge, or other causes. Land as soon as practical at an 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 problern. Watch the oil pressure gauge for an accompanying loss of pressure. . I 3.23 ALTERNATOR FAILURE Loss of alternator Output is detected through zero rtading on the ammeter. Before executing the following procedure, h u r e that the reading is Zero and not merely low by actuating an electrically powered device, such as the landing light. If no increase in the ammeter reading is noted, altemator failure can be assumed. REPORT: VB-930 3-14 ISSUED: NOVEMBER 30,1978 1'1 I'EH AI HCR A E T CORI'OH AT1ON SECTION 3 PA-28RT-201, ARROW IV EMERCENCY PROCEDURES The elcctrical load should be rcduced as much as possible. Check the silicrnator circuit breakcrs for a poppcd circuit breaker. I ....I ' The ncxt step is to aitcmpt to reset the overvoltage relay. This is accom- plished by moving thc AL?' switch to OFF for one second and then 10 ON. If thc trouble was causcd by a rnomentary overvoltage condition (16.5 Volts and up) ihis proccdurc should rcturn the ammeter lo a normal rcading. If ihc ammetcr continucs to indicatc 0 Output. or if the altcrnator will not rcmain resct, turn O f f ihc ALT switch, rnaintain minimum electrical load and land as soon as practical. All electrical load is h i n g supplied by ihe battery and ciin bc dcplctcd rapidly. 3.25 PROPELLER OVERSPEED Propcllcr ovcrspccd is caused by a malfunction in the propcllcr govcrnor or low oil pressurc which allows the propeller blades to rotate to full low pitch. If propeller overspeed should occur, retard the throttle and check the oil ''". cssure. The propeller control should be moved to full "DECREASE rpm" d thcn set if any control is available. Airspeed should be reduced and h k r o t t l c used to maintain 27oO RPM. 3.27 EMERGENCY LANDINC GEAR EXTENSION Prior to initiaiing thc emergency extension procedure check to insure that the rnastcr switch is ON and [hat the circuit breakers have not opencd. If i t is daytime thc panel lights should bc turned OFF. Check the landing gear indicaiors for faulty bulbs. 1 NOTE Refcr 10 Paragraph 4.39 for differences when emcrgcncy cxtension procedure is performcd for training purposcs. 11' itic Innding gcar docs not chcck down and locked, rcduce the airspeed below 87 KIAS. Movc tlie landing gear selector switch to thc DOWN "yosition. 11' ihe gear has 1'ailcd to lock down on aircraft equipped with the mkup gear cxtcndcr, raise ihe emcrgency gear levcr to the OVERRlDE --'ENGAC;ED position. I f gcar has still failcd to lock down, move and hold thc emcrgcncy lever down to ihe EMERGENCY DOWN position. I REPORT: VB - 930 . . - ISSUED: NOVEMBER 30,1978 If the gcar has still failcd to lock down, yaw ihc airplanc abruptly liorii If the nose gcar will not lock down using tlic abovc proccdurc. slow tlic airplane to the lowcst Safe specd attainable using thc lvwest powcr scttinl required for Safe Operation and raisc the emcrgcncy gear lcver to the OVERRIDE ENGAGED position on aircraft cquippcd with tlie backiip gear extnder. Move the landing gcar selector switch to ihc gear DOWN position. If the landing gear does not check down, recycle the gcar through the UP Position and then select the "DOWN" Position. I side to side with the rudder. I 3.29 SPIN RECOVERY Intentional Spins are prohibited in this airplanc. If a Spin is inndvertently entered, immediately apply full rudder opposite to the direction of rotation. Move the control wheel full forward while neutralizing the ailcrons. Move the throttle to IDLE.When the rotation stops. ncutralize the rudder and easc back on the control wheel as required to smoothly regain a lcvel fiiglii attitude. 3.31 OPEN DOOR ," "he cabin door is double latched, so the chances of its springing Open i i ; flight at both the top and bottom are remote. Howcver, should you forget thL upper latch, or not fully engage the side latch, thc door may spring partially open. This will usually happen at takeoff or soon afterward. A partially opcn door will not affect nomial flight characteristics, .and a normal landing ciin be made with the door open. If both upper and side latches are open, the door will trail slightly opcn, and airspeed will be reduced slightly. To close the door in fiight. slow the airplane 10 87 KIAS, closc ihc cahin vents and open the storm window. If the top latch is opcn. latch ii. If the sidc latch is open, pul1 on the arm rest while moving tlic latch handle to the latchcd Position. If both latches are open, close ihe side latch then thc iop latch. 3.33 ENGINE ROUGHNESS Engine roughness may be caused by dirt i n thc injector nozzlcs., - induction system icing, or ignition Problems. First adjust ihe mixture for maximum smoothncss. The engine will r u n rough if the mixture is too rich or too lean. REPORT: VB-930 3 -16 ISSUED: NOVEMBER 30,1978 REVISED: JANUARY 31,1987 PiPLW AIRCRAFT CORPORATION SECTlON 3 PA-28RT-201, ARROW IV EMERGENCY PROCEDURES Move the alternate air to OPEN and then turn "ON" the electric fuel pump. Switch the fuel seiector to another tank to See if fuei contamination is the problern. Check the engine gauges for abnormal readings. If any gauge readings are abnormal proceed accordingly. i h c magneto switch should then be moved to "L" then "R," then back to 'BOTH." if operation is satisfactory on tither magneto, proceed on that magncto at reduced power with full RICH rnixture to a landing at the first available airport. If roughness persists, prepare for a precautionary landing at Pilot's discretion. REPORT: VB-930 Z17 ISSUED: NOVEMBER 30, 1978 -. L., * Paragraph No. 4.1 4.3 4.5 4.7 4.9 4.1 1 c- 4.13 '- 4.15 4.17 4.19 4.2 1 4.23 4.25 4.27 4.29 4.3 I oba .33 d '4.35 4.37 4.39 4.4 1 TABLEOFCONTENTS SECTION 4 NORMAL PROCEDURES Page No. General .......................................... 4-1 Airspeeds for Safe Operations . .... . ... . .'... . . . . . . . . . 4-I Normal Procedures Check List ..... ... . .. . . . .. . . . . .. 4-3 Amplified Normal Procedures (General) ... .. . . .... ... 4-12 Prefiight Check.. .... .. .. . .... . .. . ...... . . .... . . . .. 4-12 Before Starting Engine .............. . . ... . . ... . .... 4- 15 . .'1 Staning Engine ....... . . . . . . . . . . ....... , . . . .. . . . . .. 4- I5 I . Warm-Up ......... , . . . . . . ........... . . . . . , . . . .... 4-17 Taxiing ..... , ........ . . . . . ... . , .. . ... . . . . . .... . .. . 4-I7 ! Ground Check 4-18 Before Takeoff ... . ........... . .. . . . .. . .. . , . . . . . . . . 4- I8 ! Takeoff ... ... . . . . . . .. , ..... . . . . ... . ....... . ..... . 4-19 1 j Climb .. . ....... . ... . ........ . . . . . ..... .. . . ... . .. . 4-20 Cruising . .. .. . . . . . . ............. , . .. . . . . . . . . . . . . . . 4-2 1 Approach and Landing . . . . . . . . , ..... . . . . . . ... . , . . . . 4-22 Stopping Engine.. ... . . . . . . ... . . . . . . . . . . . . ... . . . . . . 4-23 Parking .......................................... 4-23 Stalls . . . . . . . . ...... . . . . . . . . . . , . . . . . . . . . . . . . . . .... 4-24 4-24 Landing Gear . . .. . . . . , . . .. . .. . . . , . . . . . . . .. . . , . . . . . 4-25 Weight and Balance.. . . . . . . . .. . . . . . . . . . . . . . . . . . . , . . 4-26 1 1 1 ! ..... ... . .. . ... . ..... . .. . .. . . . . . . . . . . . , j Turbulent Air Operation.. . . . . . . .. . . . . . . . . . . . . . . . . . . :; 1 ;REPORT: VB-930 ; . I PIPER AIRCRAFT CORPORATION SECTION 4 PA-28RT-201, ARROW IV NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES 4.1 GENERAL This section clearly descnbes the recommended procedures for the conduct of normal Operations for the Arrow IV. All of the required (FAA regulations) procedures and those necessary for the safe Operation of the airplane as determined by the Operating and design features of the airplane are presented. Normal procedures associated with those optional systems and equip- ment which require handbook Supplements are provided by Section 9 (Supplements). These procedures are provided to present a source of reference and review and to supply information O n procedures which are not the Same for all aircraft. Pilots should familiarizt themselves with the procedures given in this section in Order to become proficient in the normal operations of the i I ! airplane. ! The first Portion of this section consists of a short form check list which supplies an action sequence for normal Operations with little emphasis on the Operation of the systems. The remainder of the section is devoted to amplified normal procedures 1 and how to periorm them. This Portion of the section is not intended for use as an in-flight reference due to the lengthly explanations. The short form check list should be used for this purpose. I ! I ,.vhich provide detailed information and explanations of the procedures ! 4 3 AIRSPEEDS FOR SAFE OPERATIONS The following airspeeds are those which are significant to the safc Operation of the airplane. These figures are for Standard airplanes flown at gross weight under Standard conditions at sea level. . - 1i \ t. ISSUED: NOVEMBER 30,1978 REPORT: VB-930 A-. . . .: SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28RT-201, ARR.0W IV Performance for a specific airpiane 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 gear up, flaps up gear down, flaps up 87 KIAS 76 KIAS (b) Best Angle of Climb Speed 77 KIAS 70 KIAS (c) Turbulent Air Operating Speed (See Subsection 2.3) 121 KIAS (d) Maximum R a p Speed 108 KIAS (e) Landing Final Approach Speed (Flaps 40') 74 KIAS ( f ) Maximum Demonstrated Crosswind Velocity 17 KTS REPORT: VB-930 A . 9 ISSUED: NOVEMBER 30,1978 d T Y : i . 0 ; 4 3 NORMAL PROCEDURES CHECK LIST PREFLIGHT CHECK COCKPIT Control wheel .................................... release restraints r - 7 XFarking brake ..................... .:......................... set - .. 'Aliswitchcs ................................................ OFF Mixture idle Cut-Off Master switch ON Fuel gauges ......................................... check quantity Annunciator panel .......................................... check Master switch OFF Primary fiight controls. ............................ proper Operation Trim neutral Pitot and static Systems.. .................................... drain Windows .......... ;................................. .check clean .............................................. ............................................... ............................................... . . Raps.. .......................................... proper Operation .................................................... ISSUED: NOVEMBER 30, 1978 REPORT: VB-930 1 . ) SECTION 4 PIPER AIRCRAFT CORPORATlON ~ O R M A LPROCEDURES PA-28RT-201, ARROW IV . Rcquired Papers ................................... check on board Tow bar and baggage.. ............................. stow properly - Baggage door.. ................................... close and secure i securc , . . RIGHT WING Surface condition ........................... clear of ice, frost, Snow R a p and hinges.. .......................................... .check Ailer,on and hinges .......................................... .check Wing tip and lights.. ....................................... .check Fuel tank check supply ,d visuaily - secure cap Fuel tank vent.. .;.......................................... clear Fuel tank surnp.. ........................................... drain Tie down and chock.. ..................................... remove Main gear strut.. ..................................... .:...proper infiation (2.5 2 2 5 in.) Tire ...................................................... .check Brake block and disc ...................................... ..check Fresh air inlet clear NOSE SECTION .. i ........................................... .............................................. ,I . General condition ......................................... ..check ! . Cowling .................................................. securc Windshield ................................................. clean Propeiler and spinner.. ..................................... .check AU inlets .................................................. clear Alternator belt ........................................ check tcnsion Chock.. ................................................. rcmove ) Nose gear strut ........................................... .proper inflation (2.75 f .25 in.) Nose wheel tire ............................................ .check .: Engine baffle seals ......................................... .check j Oil ................................................ check qiumtity Dipstick .......................................... properly seated . . . . ., , .i Fucl strainer ............................................... drain -! LEFTWING < Surface condition ........................... clcar of ice, frost, Snow Fresh air inlct .............................................. clear $ !. REPORT: VB-930 ISSUED: NOVEMBER 30,1978 4-4 YlYhH AIKCHAFT COKVUKAIION SECTiON 4 PA-28RT-201, ARROW IV NORMAL PROCEDURES Chock ................................................... remove Main gear strut .............................. .;. ...........p roper inflation (2.5 +. .25 in.) Tire .......................................................... check Brake block and disc ........................................ .check Fuel tank ........................................... check supply visually - secure cap Fuel tank vent.. ............................................ clear Fuel tank sump.. ........................................... drain Tie down ................................................ remove Pitotlstatic head .................................... remove Cover - holes clear Wing tip and lights.. ....................................... .check Aileron and hinges .......................................... .check Flap and hinges.. .......................................... .check FUSELAGE Antennas .................................................... check Empennage ................................ clear of ice, frost;snow Fresh air inlet ........................................... .:.. clear Stabilator and tnm tab ....................................... check Tie down ................................................ rcmove Master switch ............................................... ON Cockpit iighting ............................................ check Nav and strobe lights.. .................................... ..check Stall warning .............................................. .check Pitot heat ................................................. .check All switches ................................................ OFF Passengers ................................................ board Cabin door.. ..................................... close and secure Seat belts and hamess ............................... .fasten .check k. inertia reel ) /.i , BEFORE STARTING ENGINE Brakes ............................................ 1.......... set Propeller.. ................................... full INCREASE rpm Fuel selector ......................................... desired tank . Alternate air ............................................... .OFF ) ISSUED: NOVEMBER 30,1978 REPORT: VB-930 ‘4-5 I SECTiON 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28RT-201, ARRO W IV STARTMC ENGINE WHEN COLD Throttie ................................................ 112" open . Master switch ................................................ ON Electnc fuel pump ........................................... ON Mixture ......................................... prime .then idle Starter. .................................................... engage Mixture .............................................. .full RICH Throttle .................................................. adjust Oil prtssure ............................................... .check cut-Off ' , . STARTING ENGINE WHEN HOT Throttle ............................................... 1/ 2" Open Master sWitch ............................................... ON Electnc fuel pump ........................................... ON Mixture .............................................. idlc cut-Off Starter. ................................................... engage Mixture advance . . Throttle .................................................. adjust Oii pressure ................................................. check ................................................. (' '. STARTINC ENGINE WHEN FLOODED Throttle ..;. ............................................ Open full Master switch ............................................... ON .EleCtnc fuel pump .......................................... OFF Mixture .............................................. idle cut-off Starter. .................................................... engage .... Mixture ................................................ .advance Throttle .......................... ?...................... retard Oil pressure ................................................ .check REPORT VB-930 . I ISSUED: NOVEMBER 30,1978 PIPER AIRCRAFT CORPORATIUN SECTION 4 PA-ZSRT-201, ARRO W IV NORMAL PROCEDURES STARTING WITH EXTERNAL POWER SOURCE Master switch .............................................. OFF AU electncai equipment ...................................... OFF Terminals ................................................ connect Extcmal power plug ............................... insert in fuselage Proceed with normal Start Throttle ..................................... lowest possible RPM Extemal power plug ........................ disconnect from fuselage Master switch ................................ ON - check ammeter Oil ptessure ............................................... .check (- WARM-UP Throttie ....................................... 1400 to 1500 R P M TAXIING Chocks ................................................ removed Taxi area ...................................................clear Throttle ............................................. apply slowly Prop ................................................. high RPM Brakes.. .................................................. .check Steenng .................................................... check GROUND CHECK Propeller. ........................................ full INCREASE Throttle ............................................... 2000 RPM max. diff. 50 RPM Vacuum ...................................... 4.8" Hg.to 5.1 " Hg. Oil temperature ............................................ .check Oil pressure ............................................... .check Magnetos ....................................max. drop 175 RPM . ! ISSUED: NOVEMBER 30,1978 REPORT: VB -930 4-7 3 L L I l U I l 4 YiYLK AlKLKAr 1 LUKYWKATlUN NORMAL PROCEDURES PA-28RT-201, ARROW IV Air conditioner ............................................. 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 falterning. Electric fuel pump .......................................... OFF Fuel pressure ............................................. ..check Throttle ...... ........................................... retard , . BEFORE TAKEOFF Master switch ............................................... ON Fiight instniments ........................................... check Fuel selector ......................................... proper tank Altemate air ........................................... CLOSED Seat backs ................................................. erect Mixture ...................................................... set , . ... Electric fucl pump ............................................ ON . Enginc gauges ............................................. .check . Prop ......................................................... Set . Belts/ harness ............................................ fastcned . Empty seats .............................. .seat belts snugly fastend Flaps.. ...................................................... set 1 Trim tab.. .................................................... set Controls .................................................... f m . Doors ................................................... iatched .. Air conditioner ............................................. OFF . . TAKEOFF NORMAL Flaps. ....................................................... set Tab ................................................. .:......Set Accelerate to 65 to 75 KIAS. 'Control wheel .................................... back pressure to rotate to climb attitude ' I REPORT: VB-930 4-8 ISSUED: NOVEMBER 30,1978 PIPER AIRCRAFT CORPORATION SECTION 4 PA-28RT-201, ARROW IV NORMAL PROCEDURES S H O R T FIELD. OBSTACLE CLEARANCE '?I F l a p s . . ........................................ 25" (second notch) ..-d' Accelerate to 50 to 60 KlAS depending on aircraft weight. Control wheel .................................... back pressure to rotate to climb attitude After breaking ground. accelerate to 55 to 65 KlAS depending on aircraft weight. Gear (OVERRIDE ENGAGED on aircraft equipped with backup gear Accelerate to best flaps up angle of climb speed - 77 KIAS, slowlyretract the flaps and climb past the obstacle. Accelerate to best flaps up rate of climb speed - 87 KIAS. S O F T FIELD .................................................... extender) UP I F l a p s . . ........................................25 " (second notch) Accelerate to 50 to 60 KlAS depending on aircraft weight. Control wheel .................................... back pressure to rotate to climb attitude After breaking ground, accelerate to 55 to 65 KlAS depending on aircraft weight. Gear (OVERRIDE ENGAGED on aircraft equipped with backup gear extender) .................................................... UP Accelerate to best flaps up rate of climb speed 87 KIAS. F l a p s . . ............................................. retract slowly . I CLIMB Best rate (2750 Ib.) (gear up) . -1 Best rate (2750 Ib.) (gear down) , (flaps up) ............................................ . 8 7 KlAS (flaps up) . 7 6 KlAS Best angle (2750 Ib.) (gear up) (flaps up) ............................................ . 7 7 KlAS Best angle (2750 Ib.) (gear down) (flaps up). ...............70 KlAS En route ............................................... 104 KlAS Electric fuel pump ................................. O F F at desired altitude / ............................................ .......; ! '1 ..4J ISSUED: NOVEMBER 30, 1978 REVISED: JANUARY 31, 1987 REPORT: VB-930 4-9 SECTXON 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28RT-201, ARROW IV 1 CRUISING Reference Performance Charts, Avco - Lycoming Operator's Manual an-' power Setting table. Normal rnax power .......................................... 75% Power ......................................... set per power fable Mixture .................................................. adjust j APPROACH A N D LANDINC Fuel selector ......................................... proper tank Seat backs ................................................. erect Beltsl harness .............................................. fasten Electric fuel pump ........................................... ON Mixture ..................................................... Set Propeller.. ................................................... set Gear ...................................... .down - 130 KlAS max Flaps ......................................... set - 108 KlAS max Air conditioner ............................................. O F F Trirn to 75 K l A S STOPPING ENGINE Flaps.. ................................................... retract Electric fuel pump .......................................... O F F Air'conditioner ............................................. OFF Radios .................................................... O F F Propeller.. ....................................... full INCREASE Throttle .................................................. f u l l af. Mixture .............................................. idle Cut-01, Magnetos. ................................................. OFF Master switch ............................................... O F F PARKINC ................................................ Parking brake set.,.-~ Control wheel ................................... secured with belt- Flaps.. ................................................... full u t ..... Wheel chocks.. ........................................... in place Tie downs.. ............................................... secure . . i REPORT: VB - 930 4-10 ISSUED: NOVEMBER 30, 1978 (I. PIPER AiRCRAFT CORPORATION SECTION4 j PA-28RT-201, ARRO W IV NORMAL PROCEDURES /: 1 E r c THIS PAGE INTENTIONALLY LEFT BLANK c ISSUED: NOVEMBER 30,1978 .J REPORT: VB-930 : Li1 ---*--*. -. rufin AIKLKAF'~'COKPORATION NORMAL PROCEDURES PA-28RT-201, ARROW IV 4.7 AMPLIFIED NORMAL PROCEDURES (GENERAL) The following paragraphs are provided to supply detailed information and explanations of the normal procedures necessary for the Safe Operation of the airplane. 4.9 PREFLIGHT CHECK The airplane should be given a thorough prefiight and walk-around atus, computation of weight and C.G. limits, takeoff and landing riistances, and in-flight Performance. A weather briefmg shouid be obtained for the intended flight path, and any other factors relating to a Safe flight should be checked before takeoff. check. The preflight should include a check of the airplane's operational 1 , I CA UTION The flap Position should be noted befon boarding the airplane. The flaps must be placed in the UP Position' before they will lock and support weight on the step. c COCKPIT Upon entering the Cockpit, relcase the seat belts secunng the control wheel and Set the parking brake. Insure that all clectrical switches and the :: magneto switch arc OFF and the mixture is in idle cutsff. Turn ON the master switch, check the fuel quantity gauges for adequate supply and check .. that the annunciator panel illuminatts. Turn OFF the master switch. Check the pnmary fight controls and fiaps for proper Operation and Set the trim to neutral. Open the pitot and static drains to remove any moisture that has >mulatcd in the lines. Check the windows for cleanliness and that the rcquired Papers are on board. Properly stow the tow bar and baggage and secure. Closc and secure the baggage door. RIGHT WING I , Begin the walk -around at the trailing edge of the nght wing by checking that the wing surface and control surfaccs are clear of ict, frost, Snow or other extraneous substances. Check the flap, aileron and hinges for damage and operational interference. Static wich should bc firmly attached and in good condition. Check the wing tip and lights for damage. q REPORT: VB-930 4-12 ISSUED: NOVEMBER 30,1978 ......' PIPER AIRCRAFT CORPORATION PA-ZSRT-201, ARRO W IV . SECTION 4 NORMAL PROCEDURES Open the fuel cap and visually check the fuel color and the quantity should match the indication that was on the fuel quantity gauge, replacccap securely. The fuel tank vent should be clear of obstructions. Drain the fuel tank through the quick drain located at the lower inboard rear Corner of the tank, making Sure that enough fuel has.been drained to insure that aii water and Sediment is removed. The fuel system should be drained daily pnor to the first fight and after each refueling. .. CAUTION When draining any amount of fuel, care should be taken to insure that no f r e hazard exists before starting engine. Remove the tie down and chock. Next, a complete check of the landing gear. Check the gear strut for proper infiation, there should be 2.5 f .25 inches of strut exposure under a normal static load. Check the tire for Cuts, wear, and proper infiation. Make a visual check of the brake block and disc. Check that the fresh air inlet is clear of foreign matter. NOSE SECTION : Check the generai condition of the nose section, look for oil or fluid leakage and that the cowling is secure. Check the windshield and clean if necessary. The propeller and spinner should be checked for dctnmcntai nicks, Cracks, or other defects. The air inlets should be cleai of obshctions and check the alternator belt for proper tension. T h e landing Iight should be clean and intact. ' d' Remove the chock and check the nose gear strut for proper hfiation; there should be 2.75 f .25 inches of strut exposure under a normal static load. Check thc tire for Cuts, wear, and proper inflation. Check the cngine baffle seais. Check the oil level, make Sure that the dipstick has been properly seated. . Open the fuel strainer located on the left sidc of the firewali longenough ) to remove any accumulation of water and Sediment. ISSUED:NOVEMBER 30,1978 REPORR.VB-930. ' ' 4-13 - . SEcTION.4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28RT-201, ARROW IV LEFT WING ( i h e wing surface should be clear of ice, frost, Snow, or other extraneous substances. Check that the fresh air inlet is clear of foreign matter and rcmove the chock Check the main gear strut for proper inflation, there should be 2.5 f.25 inches of strut exposure under a normal static load. Check the tirc and the brake block and disc. Open the fuel cap and visually check the fuel color.The quantity should I match the indication that was on the fuel quantity gauge. Replace cap securely. The fuel tank vent should be clear of obstructions. Drain enough fuel to insurc that aU water and Sediment has been removed. Remove tie down and remove the Cover from the pitotlstatic head on the undenide of the wing. Make Sure the holes are Open and clear of obstnictions. Check the wing tip and lights for damage. Check the aileron, flap, and hinges for damage and operational interference and that the static wich art..firm€y attached and in good condition. FUSELAGE Check the condition and secunty of the antennas. The empennage should be clear of ice, frost, Snow, or other extraneous substances and the fresh air inlet at the top of the fin should beclear of foreign matter. Check the stabilator and trim tab for damage and operational interference, the tnm tab should move in the Same direction as stabilator. Remove the tie down. ( Upon returning to the Cockpit, an operational check of the intenor lights, exterior lights, stall warning System, and pitot heat should now be made. Turn the master switch and the appropriate switches ON. Check the panel lighting and the overhead flood light. Visually confirm that exterior lights are operational. Lift the stall detector on the leading edge of the left wing and detcrmine that the waming hom is activated. With the pitot heat switch ON the pitot head will be hot to the touch. After these Checks are complete the master switch and ail electncal switches should be tumed OFF. Board the passengers and close and secure the cabin door. Fasten the seat belts and shoulder harness and check the function of the inertia reel by pulling sharply on the strap. Fasten seat belts on empty seats. REPORT: VB-930 4-14 ISSUED: NOVEMBER 30, 1978 REVISED: FEBRUARY 16,1979 PIPER AIRCRAFT CORPORATION SECTION 4 PA-28RT-201, ARRO W IV NORMAL PROCEDURES 4.11 BEFORE STARTING ENGINE Before starting the engine the brakes should be Set ON and the propeller lever moved to the full INCREASE rpm Position. The fuel selector should then be moved to the desired tank. ( 4.13 STARTINC ENGINE (a) Starting Engine When Cold c~ Open the throttle lever approximateiy 1/ 2 inch. Turn ON the master switch and the electric fuel pump. Move the mixture control to full RICH until an indication is noted on the fuel flow meter. The cngine is now pnmed. Move thc mixture control to idle c u t s f f and engage the Starter by rotating thc magneto switch clockwise. When the engine fires, c release the magneto switch, advance the mixture control to full RICH and move the throttle to the desired Setting. If the engine does not iire within five to ten seconds, disengage the Starter-and repnme. (b) Starting Engine When Hot . Open the throttle approximately 1/ 2 inch. Turn ON the master switch and the electric fuel pump. Move the mixture control lever to idle cutsff and engage the Starter by rotating the magneto switch clockwise. When the engine fires, release the magneto switch, \ advance the mixture and move the throttle to the desired Setting./ L, (c) Starting Engine When Flooded The throttle lever should be full OPEN. Turn ON the master switch and turn O F F the emergency fuel pump. Move the mixture control lever to idle cut-Off and engage the Starter by rotating the magneto switch clockwise. When the engine fires, release the magneto switch, advance the mixture and retard the throttle. ISSUED: NOVEMBER 30,1978 REPORT: VB-930- - - “ r n ~ * . V * . r i r n m AIKLKAP 1 L‘UKYOKATION NORMAL PROCEDURES PA-28RT-201, ARROW IV (d) Starting Engine With External Power Source An optional feature called the Piper External Power (PEP) allows the Operator to use an external battery to crank the engine without having to gain access to the airplane’s battery. I . . . . . . . .. Turn the master switch O F F and turn all electncal equipment OFF. Connect the RED lead of the PEP kit jumper cable to the POSITIVE (+) terminal of an external 12-volt battery and the BLACK lead to the NEGATIVE (-) terminal. Insert the plug of the jumper cable into the socket located on the fuselage. Note that when the plug is inserted, the electrical system is ON. Proceed with the normal starting technique. . After the engine has started, reduce power to the lowest possible RPM, to reduce sparking, and disconnect the jumper cable from the aircraft. Turn the master switch ON and check the alternator ammeter for an indication of Output. DO NOT ATTEMPT FLIGHT IF THERE IS NO INDICATION OF ALTERNATOR OUTPUT. <.- ’ NOTE For all normal Operations using the PEP jumper cables, the master switch should bc OFF,but it is possible to use the ship’s battery in parallel by turning the master switch ON. * This will give longer cranlcing capabilities, but will not incrcase the amperage. CA UTION Care should be exercised because if thc ship’s ‘ 1 battery has becn depleted, the extemal power supply can be reduced to the level of the ship’s battery. This can be tested by turning the master switch ON momentanly while the Starter is engaged. If cranking speed increases, the ship’s battery is at a higher level than the external power supply. ) When the engine is finng evenly, advance the throttlc to 800 RPM.If oil pressure is not indicated within thirty seconds, stop the engine and deterrnine REPORT: VB-930 4-16 ISSUED: NOVEMBER 30,1978 PIPER AIRCRAFT CORPORATION SECTION 4 PA-28RT-201, ARROW I V NORMAL PROCEDURES the trouble. I n cold weather i t will take a few seconds longer to get a n oil pressure indication. I f the engine has failed to Start, refer to the Lycoming Operating Handbook, Engine Troubles and Their Rernedies. , '"'\\ Starter manufactures recomrnend that cranking periods be limited to thirty seconds with a two minute rest between cranking periods. Longer cranking periods will shorten the life of the Starter. ' L J 4.15 WARM - UP Warm-up the engine at 1400 t o 1500 R P M . Avoid prolonged idling at low R P M . as this practice may result in fouled Spark plugs. Takeoff rnay be rnade as soon as the ground