Piper Cherokee 140 Owner's Handbook Manual
The Piper Cherokee 140 is a four-seater aircraft known for its reliability and ease of handling. Its Lycoming O-320 engine delivers 140 horsepower, with a cruise speed of 100 mph. The aircraft has a standard 36-gallon fuel capacity, providing a range of 515 miles. Featuring a sturdy aluminum alloy construction, the Cherokee 140 is equipped with a full-time power electrical system and a heating and ventilating system. It is designed for various flight operations, including personal transportation and flight training.
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O!av Kieserud CHEROKEE I 40 OWNER'S HANDBOOK 753-584 Olav K jesecud CHEROKEE 140 PA.28.l 40 Owner's Hondbook Piper Aircraft Cotporotion, Vero Beoch, FlorUo u.5. A. NOTICI] TIIIS IIANDI}OOK IS NO't DESIGNIiD, NOR CAN ANY H^NDDOOK SERVE, A SUBSTTTUTE FOR ADEQU^TE ^S coMpETENT FLIGHT INSTRUCTION, OR KNOWLEDGE OF ^ND THE CURRENT AIRWORTHINES§ DIRECTIVES, THE APPLICABLE FEDERAL AIR REGULATIONS, AND ADVISORY CTRCULARS. IT IS NOT INTENDED TO IIE A GUIDI' OF ITASIC }'LIGHT INSTRUCTION, NOR A TRAINING MANUAI,. 'l'ilrt il^NDD(x)K ls Drist(.;Ntil): I. TO IIELID YOU OI'IiRA'I'E YOUR CHIIROKIiI' WITII SA I.'ETY AND CONIIIDENCE. 2, TO MORE FULLY yOU WITH THE BASIC ^CQU^rNT PERFORMANCE AND HANDLING CHARACTERISTICS OFTHE AIRPLANE. 3. TO MORE FULLY EXPLAIN YOUR CHEROKEE'S OPERÅTION THAN IS PERMISSIBLE TO SET FORTH IN THE AIRPLANE FLIGHT MANUAL. IF THERE IS ANY INCONSISTENCY BETIVEEN THIS HANDBOOK AND THE AIRPLANE FLIGHT MANUAL APPROVED BY THE F.A,A., THE AIRPLANE FLIGHT MANUAL SHALL GOVERN. Revised text and illustrations shall be indicated by a black vertical line in the margin opposite the change, A line opposite the page number will indicate that materi al was relocated. Additional copies of this manual, Part No. 753 584, may be obtained from your Piper Dealcr. Published by PUB UCATIONS DEPARTMENT Piper Aircraft Corporation 753 5U Issu«l: Febnrary 1964 Revised: March l. l99l SECT|ON I SPECIFICATION FEATURES Performance . Weights Power Planc. FueI and Oil Baggage Dimens ions. Landing Gear . THE PIPER CHEROKEE SECTION sEcfloN I SPECIFICATION FEATURES PERFORMANCE The gross $reighr o, l95O Pq.rnds ln the following perlårmance chÅrts appll,es ,o S{rUf Nos, 28-2OOOO to 28-20939, uleas the airpleqe has been modilled t Nos, 28-20940 snd llp hsvc bcen llcenircd from the fa Perforrutrcq flgues ere for strnderd alrplanes Ievel or ståld flhltudc. Any dcvistldl from Sta GRO§S WEIGHTS Telc-off Ru (It,) (flaps 14) Tetc-off Di.Btaræ Over 50 ft. Obsracle (fr.) (fl8ps up) Best Rate of CUmb Spæd (hph) Rrte of CUmD (ft. per mln.) I Scrvtce Cetllug (ft.) Absolute Ceiltng Top $ced (mph) ClutslnB Sp€ed (75% power, sea level) (mph) Optlmum Crulstng Speed pSS potuer, 7000 It., mph) lsm 85 820 15, O0O f7, OOO r r4t (r44.) 'l r20 (f23.) f30 (f33.) wer, sea level) 100 (102+) I I i r?00 Ss 660 r4,3OO ,U. U* i t39 (r42.) ' I f30 (f33.) I 570 (790.r) tZt 1tU.1 .l r00 (r02r) 7.e 8.4 i s.3 s.o I ) 5r5, { hEs. (r20, 6 hr8...) +fO, n frru[ (680, 6 hrs.rr) i 535 (725.+) 560 (780..) ) . Opttmu$ Grulslng Renge (55$ powrr, 10, 0m ft, ) '\iltren Fenders Instålled "With 50 gal. Resene Fæl 730I I 5 600 (840..) SECTION I THE PIPER CHEROKEE SPECIFICATION FEATURES: (cont) PERFORMANCE I : lnetruciloul Pover Crutsltrg Range (50%,pqwer, sea level) Sta[ln-gSpeed (flaps doyn, mFh) Landlng Roll (flaps down, fr.) aRosri r9 50 TErGr{Ts 2r50 I 640,1 6.s hrs. (89s, I t hrs. ti) d50, 6.5 hrs, (910, t hrs. r.) 52 54 48s 53s WEIGHTS Gross U,eight (lbq. ) 1950 ,.180 Empcy Wetght (Standard) (Ibs.) USEFUL LOAD (Standard) (lbs.) Empcy \Yeighr (AutoFlight) (lbs.) UsEFUl, LOAD (Åu.oFligtrr) (lbs.) 2150 l20l 770 949 1220 t24l 730 909 o-320-E2A o-x20-E2A 140 ei 2450 150 at 2700 5, t25 POWER PI.ANT EEgtne - L}æomlng Rated Horsepryer md Speed (rpm) Bore (lo:hes) Stroke (inches) Displaæmetrt (cubic incheE) . CompEesslotr Ratib Dry Weighr (poutrds) Oit Sump Capaqity (qts. ) 5. r25 3.875 319.8 7:\ 3.875 319.8 7i7 272 Propeller (Sensentch) I 8 M74DM M74DM "Wirh 50 gal, Resefle Fuel 650630 1 THE PIPER CHEROKEE SECTION I SPECIFICATION FEAIURES: (conr) GROSS WElerrrs r950 2r50 FUEI. AND OIL (Spccified Octane) 36 50 88 80187 80147 (Altanctc Fuels) See pegc 3O Fuel Capaclty (gal. ) Srandard Fuel Capacity (Sal.) Reserve Oil Capaclty (qts. ) Fuel Aviation Gradc (Minimum Octenc) 36 .50 80187 80.187 BAGGAGE Maximum Baggage (lbs.) 100 ,, Baggaæ Space (cubic ft.) 200.*. ,'» DIMENStONS Wtng Span (ft. ) Wing Area (sq. ft.) trVing LoadinS Qbs. per sq. ft.) Length (ft.) Height (ft.) Power Loading (lbs. per HP) 30 30 r60 12.2 23.3 r60 23.3 t3,4 7.3 7.3 13. 9 r4.3 6.2 6.2 r0.0 IANDING GEAR. Wheel Base (fr.) Wheel Tread (ft. ) Tlre kessure (lbs.) 10.0 Nose Main 24 24 24 24 'rtExcept when family seat and sefety belts are installed 340 lbs. ls permitæd. 770527 SECTIONI THE PIPER CHEROKEE SECTION I DESIGN INFORAAAT]ON Engine and Propeller 5 Stnrctures 6 Landing Gear 6 Conrol System 7 Fuel System 8 Electrlcal system 9 Heating and Ventilating System r0 Cabin Feahrres r2 THE PIPER CHEROKEE SECTION II sEcTtoN il DESIGN INFORMATION ENGINE AND PROPELI.ER The Lycoming o-IZo.EzA enginc inselled in rhe Cherokce PA-28-140 is ratcd ar l4O horsepowcr ar 2450 rpm or 150 horsepower 27OO rpm..,This cngine has a compression ratio of 7 to I end "t requires 8O/87 minimum octanc fucl. Rcfcr to Fuel Rcquiremenrs on page 30 when using alrcrnarc fuels. The engiae is eguipped with a gcared startcr, a 35 ampcre alternator, dual magnctos, vacuum pump drive, a diaphragm-rypc fuel pump and a float carburetor. Exhaust gases are carried through a system constructed of heavy gauge stainless steel which incorporates a heater shroud, to provide cabin heat and carburetor deicing. The propeller used on the PA-28- I40 is a Sensenich M74DM fixed-pitch aluminum alloy unit. Its diameter is 74 inches with a standard pitch of 60* inches, All performance figures are based on the srandard 60* inch pitch propeller. Cowling on the Cherokee ts designed to cool the engine in all normal flight conditions, including protracted climb, without the use of cowl flaps or cooling ftanges. The throttle is of the push-pull type and is located ir the lower center of the instrument panel. A knurled friction lock ls provlded toprevent creepingof the throttle from any desired position. The mixture control, located in the lower right hand side of the instrument panel, is a push-pull control llke the throttle. The full rich posirion is obrained when the control is full forward, whil.e the full aft position provides an idle cur-off *58 lnch plrch propellers when gross weight is 2I50. +*When gross weight is 2150 770527 SECTION II THE PIPER CHEROKEE for stopping the engine. Intermediate posltlons are used for leåning the mlxture at ahitudes above sea-level, The carburetor heat control, located to the left of the thronle, provides maximum carburetor heat when pul.led to its full aft position. With carburetor heat off, all eugine air passes througtt a highefficiency dry-type filter. Therefore, prolonged ground operatlon with carburetorheat"ON" should be avoided, particularly on unlmproved ftelds as the alr is not flltercd. STRUCTURES All structures are of alumlnum alloy conatnrctlon and are deslgned to ultlmate loed factors weU in excess of normal requirement§. All exterior surfaces are prtmed with etchlng prlmer and painted wlth acrylic enarnel. The wlngs are attached to each elde of the fuselage by Inserting the butt ends of the respective main spars into a spar box carry through which is an integral part of the fuselage sfructure, provlding. ln effect, a contlnuoua main spar urith spllces at each slde of the fuselage. There are also fore and aft attachments at the rear spar and at an auxlliary frmt epar. The wing airfoil section is a l,aminar flow type, NACA 652-4fS wlth the maximum thicknessabout 40% aft of the treading edge. This permlts the main spar carrythrough structure to be located under the rear seat providlng unobstructed cabln floor space ahead of the rear seat. TANDING GEAR The thtee landing gears use a Clevelaod 6O0 x 6 wheel' tbe main wheels belng provtded with brake drums and Cleveland single disc hydraul.ic brake assemblies. The nose wheel and the 67m3r !.- -. - r.' THE PIPER CHEROKEE I SECTION II main gear both use 600 x 6 four ply tires. All the tires have tubes. The nose gear is steerable through a 30 degree arc each side of neutral by use of the rr.rdder pedals. A spring device is lncoraorated in the rudderpedal torque tube assembly to aid in nrdder centering and to provide rudder trim. The nose gear steering mechanism also lncorporates a hydraulic shimmy dampener. The oleo struts are of the air -oil type with normal extension being 3.25 inches for the nose gear and 4.50 inches for the main gear under normal static (emptyweigfu of airplane plus full fueI and oil) Ioad. The brakes are actuated by a hand leverand master cylinder, which is located belowand behind the left centerof the instrument sub-panel. The brake fluid reservoir is installed on the.top Ieft front face of the firavall. The parking brake is incorporated in the master cylinder and is actuated by pulting back on the brake lever, depressirg theknob attached to the left side of the handle and then releasing the brake lever. To release theparking brake, puII backon the brakelever to dlsengage the catch mechanism and allow the handle to swing fonrard. CONTROT sYsTEM Dual controls are provided as standard equipment with a cable system used beEween the controls and the surfaces. The horizontal tail is of the all movable slab type, with an anti -servo tab which also acts as a longitudinal trim tab, actuated by a control on the cabin ceiltng" The stå-bilator provides extra sta-bility and ss slze, drag, and weiglt than conventi allerons areprovlded with a dlfferential eliminate adverse yaw in ilrning mane the amount of coordlnation 67 103 r SECTION II THE PIPER CHEROKEE requtred in normal turns. The flaps are manually operated, balanced for light operating forces and spriog loaded to turn to the up position- A past-center lock incorporated in the actuating linkageholds the flap when it is in the up position so that it may be used as a step on the rlght side. The flap will not support a step load except when in the full up position, so it must be completely retracted when useda§ a step, The flaps have threeextended po- sitions, 10, 25 and 40 degrees. FUEL SYSIEM Fuel is stored in two twenty-five gallon tanks whlch are secured to the leading edge structure of each wing by screws and nut plates. This allows easy removal for service or inspection. The standard quantity of fuel is 36 gallons for the Cherokee 140. Toobtain the standard quantity of fuel, fill the tanks tothe bottom of the filler neck indicator. An auxiliary electric fuel pump lsprovided for use in case of failure of the engine driven pump. The electric pump should be on for all take-offs and landings. The fuel strainer, which is equipped with a quick drain, is located on the front Iower left corner of the firewall. This strainer should be dralned regularly to check for rvater or sediment accumulation. To drain the lines from the tanks, 650630 THE PIPER CHEROKEE SECTION II the tank selector valve must be switched to each tank in turn, with the electric pump on, and the gascolatordrainvalve opened. Each tank has an individual qulck drain located at the bottom, inboard, rear corner. Fuel quantity and pressure are indicated ongauges located in the engine gauge cluster on the right side of the instrument panel, ELECTRICAT SYSTEM The Cherokeeisequippedwith thepiper F.T.p. (Full Time Power) Electrical System, ICs 12 volt alternatorprovides electrical power at all engine speeds and results in improved performance for radlo and electrical equipment and longerbattery life. In additionto thealternator, the electrical system includes a 25 ampere-hour baEery, a voltage regulator and a master switch relay. The battery and relay are mounted beneath the baggage compartment floor. Access for service or inspection is obtained by raising the hinged baggage compartment floor panel. The battery box is designed to accommodate a Larger capacity battery for extreme cold weather operation. Electrical switches, fuses and fuse spares are located on the lower left side of the in- strument panel. Standard electrical acce s sories, in additiontothose already Iisted, include a starter, stall warning indicator, cigar lighter and ammeter. Mvigation lights, anti-collision light, landing Iight, instrumenr lighting and a cabin dome light are offered as optional acces- 6s0630 SECTION tr THE PIPER CHEROKEE sorles. Circult provlslons are made to handle optlonal communlcatlons and navlgational equipment. In conventlonal generator systems, the ammeter indicates battery discharge. In the Piper FullTime Powerelectrlcal system, the ammeter displays the load in amperes placed on the system at any given time. Wtth all electricalequlpment except the master switch in the "OFF" positionr the ammeter will indicate the amount ofcharging current demandedby the battery. This amount will vary and depends on the percentage of full clørge on the battery at tåe time. When the banery becomes charged, the current dlsplaeed on the ammeter will reduce to a mlnimum value of about two amperes. As each unit of elec- trical equlpment ls swltched on the amount of current ir draws will be shown on the ammeter. The maximum cqltlnuous load for nlght flight with all equipment on is approximately thirty amperes, Thts thlrty ampere s plus approximately two amperes for the futly charged batterywill appear conriouously under these flight condittoos. Because of the mechanical simpliclty of the alternator, matnteoance should prove to be a minor factor as compared to prevlous systems. Should service be requlred, contact your local Piper dealer. HEATING AND VENTII.ATING SYSTEM Heat for the cabln lnterlor and the defroster system is pro- vided by a heater muff attached to the exbaust system. Controls fof these systems are locatedon the lower right hand side of the instrument panel. A third confrol in this area regulates a large fresh air vent located on the left hand stde of the cabin near the pllot's feet. In addition, two side vents are provided one at each seat location. Th"y may be tndependentlyregulated as desired by the seat occupant. IO 6s0630 glev Kleserud THE PIPER CHEROKEE L Frcrh Alr ConEol L D.Iro.rrt codlrcl !. lbrtlr @lsirrl SECTION II a. ILlro.alr AJt Omet l. Frc.b Alr lnler 6 tG.llr [rEt 11 THE PIPER CHEROKEE SECTION II CABIN FEATURES The instrument Panel of the Cherokee is deslgned to accommodate the customary advanced fllght instruments ard all the normally requlred power plant in§truments. Ttrc Artificlal Horlzorl Directiooal Gyro and ttre Turn and Bank instruments are vacuum operated through use of a vacuum pump installed on the englne. A natural separation of the flight group and rhe power group ls provlded by placing the communicattons and radio navigational equipment tn the center of the panel. The front seats are adiustable fore and aft for pllot comfort and ease of enrry and exlt. A famlly seat installation ls avallabl,e whlch provldes two additional seats. Each family seat ls capable of carrylng a full size adult which glves the Ctrerokee 140, 4-place capabilttY. FAMILY SEATS 1. Compass 2. Airspeed lndicator 3. Directional Gyro Indicator 4. Gyro Horizon Indicator 5. Radio ADF 6. Radio VHF 7. Tachometer t2 8, Vacuum Gauge 9. Instrument Cluster 10. Turn and Bank Indicator 11. Clock 12. Stall Warning Light 13. Altimeter 14. Rate of Climb Indicator 6s0630 THE PIPER CHEROKEE SECTION II a?- 650630 L2a SECTION ttl OPERATING INSTRUCTTONS Prcflight ... Starting .....14 . W:um-up ..I5 ' GroundCheck .. 13 .. 16 Takc-off ... t6 Climb. .....r7 Stalls . 18 Cnrfuing , ; 18 Marreuvcrr Approechandlanding ,,,f9 . . . - . . . tg Mooring WeightandBalancc 730tt5 19a .. .l9t THE PIPER CHEROKEE SECTION TII sEcTloN il OPERATING INSTRUCTIONS PREFLIGHT The airplane should be given a thorough visual inspection prior to each flight. Particular attention should be given to *re followirg items in the illustration belov: I. a. Master switch "ON. " b. Check fuel quantlty indlcators (two tanks) ' c. Master switch and ignition "OFF. " 2. a. Check for o<ternal damage, operational lnterference 66t20t 13 SECTION III THE PIPER CHEROKEE of control surfaces or hiqges. b. Insure that wings and conrrol surfaces are free of snow, ice or frost, 3. a. Visually check fuel supply, secure caps. b. Drain fuel tank sumps. c. Check that fuel system vents are open. 4. a. Check landing gear shock struts for proper inflation. b. Check tires for cuts, wear and proper inflatlon. c. Drain fuel rystem sump (left side of eircraft) 5. a. [nspect windshteld for cleanliness. b. Check the propeller and spinnet for defects or nicks. c, Check for obvious fuel or oil leaks. d. Check oil level, 8 quarts maximum. (Insure dipstick is properly seated.) e, Inspect cowling and inspection covers for security f. Check nose wheel tire for inflatlon, wear, g. Check nose wheel shock strut for proper inflation. 6. a, Stow tow bar and control locks, if used, b. Check baggage for proper storage and security. c. Close and secure the baggage compartment door. 7 . a . Upon entering aircraft ascertain that all primary flight controls operate properly, b. Close and secure the cabin door. c. Check that required papers are in order and in the aircraft. d, Fastcn seat belts and shouldcr harncss. STARTING ENGINE After completlon of the preflight inspection: I . Lock the wheel brakes. 2. Set the carburetor heat control in the full "COLD" position. 3. Select the desired tank with the fuel valve. 4. Move the mixture to the full "RICH" positton. 5. Open the throttle I/8 to t/4 inch. 6. Turn the electric fuel pump "ON. " 14 7t01t5 THE PIPER CHEROKEE SECTION III In cold weather (below 40 degrees F.) prime rhe engine with onetothree full strokes of the priming pump. If extremely cold, stårting will be aided by pulling the propeller through by hand (switch "OFF') four ro five revolutions. If rhe temperature is above 40 degrees the engine may be primed by rhree or four short quick strokes of the throttle. After priming, turn the electric master sv/itch on, engage the starter and allow the engine to turn approximately one full revolution, then turn the ignition swltch to the "Left" magneto position. When the engine is firing evenly, turn the magneto switch to the "Both" position and advance rhe thrortle ro 800 RpM, Check the oil pressure gauge for a pressure indication. If oil pressure is not indicated within thirty seconds, stop the engine and determine the trouble. If the engine fails to start at the first attempt, another attempt should be made wirhout priming. If this fails, ir is possible thar the engine is overprimed, Turn the magneto switch off, open the throttle slowly, and rorate the engine approximately ten revolutions with the starrer. Reprime the engine with one half the amounr used in the inirial artempt, turn the magneto switch to "Left, " and repear the starting procedure. If the engine again fails to start, refer to the "Lycoming OperatingHandbook, Section VII, Engine Troubles. " WARM.UP As soon as the engine starts, the oil pressure should be checked. If no pressure is indicated within rhirry seconds, stop the engine and determlne the trouble, In cold weather it will take a few seconds Ionger to get an oil pressure indication. Warm-up the engine ar 800 ro I200 RPM. Take-off may be made as soon as ground check is completed, providing that the rhrottle may be opened fully wirhout back firing or skipping, and wirhout reduction in engine oil pres§ure, l5 SECTION III THE PIPER CHEROKEE GROUND CHECK Check the magnetos at 2o0o RPM by switching from Both to Right then back to Both before switching to Left. Differential drop should not exceed 50 RPM while the total drop on either magneto should not exceed 175 RPM. Check vacuum gauge, indicator should read 5" Hg t.1" Hg at 2oo0 RPM. Check both the oil temperature and pr6sure. Thc temperature may be low for some time if the engine isbeingrun forthefirst timeof the day, but as long as the pressure is within limits the engine is ready for take-off. Carburctor heat should also be checked prior to take'off to be sure that the control is operating properly and to clcar any icc which may have formed during taxiing. Avoid prolonged ground operation with carburetor heat ON as the air is unfiltered. Mixture should be set full rich, except a minimum amornt of leaning is permitted for smooth enginc operation when taking off at high elevation. TAKE.OFF Just before take-off the following items should be checkcd: 7. Elecuic fuel pump "ON" l. Controls free 8. Engine gauges normal Flaps 2. "UP" 3. Tab set 9. Dcor latched 4. Mixture "RICH" 5. Carburetor heat "OFF" 6. Fucl on proper tank lo. Altimeter set 11. Fasten belts/harness The take-off technique is conventional for the Cherokee. The tab should be set slighdy aft of neutrd, with the exect setting determined by the loading of the aircraft. Allow the airplane to accelerate to 50 to 60 miles per hour, then ease back on the wheel enough to let the airplane fly itself off the ground. Premature raising of the nose, or raising it to an excessive angle, will result in a delayed take-off, After take-off let the aircraft accelerate to the desired climb specd by lowering the nose slightly. 16 770527 THE PIPER CHEROKEE SECTION III Shon Field, Obstacle Clearance : Lower the flaps to 25 " (second notch), accelerere to 55-60 miles per hour and ease back on the control wheel to roate. After breaking ground, accelerate to the best angle of climb specd, 74 miles per hour. Slowly retrect the flaps when the obstacle has been cleared and continue climb at 85 miles per hour, Shon Field, No Obstacles: Lower the flaps to 25 " (second notch) accelerate to 55{0 miles per hour. Ease back on the control wheel to rotate and accelerate to best rate of clirnb speed, 85 miJes per hour. Slowly rctract the fleps while climbing out. Soft Field, No Obstacle; Lower the flaps to 25 o (second notch), accelerate aircraft and pull nose gear from the ground assoon as possible, lift offat lowest possible airspccd. Accclcrate just above the ground to best race of climb speed, 85 miles per hour. Climb out white slowly retracting the flaps. Soft Field, Obstacle Clearance: Lowcr flaps to 25 o (second notch), accelerate aircraft, pull nose gcar off as soon as possbile and lift off at lowest possiblc airspced. Accclerate jusr above the ground to best angle of climb speed, 74 miles per hour to climb past obstaclc clearance height, continue climb whilc accelcrating to best rate of climb spced, 85 miles per hour and slowly retract the flaps, CLIMB The best rate of cli.mb at gross weight will be obtained at 85 miles per hour. The best angle of climb may be obtained at 74 miles per hour. At lighter rhan gross weight these speeds are reduced somewhar. For climbing enroute a speed of l0O miles per hour ls recommended. This wlll producebetter forward speed and lncreased vlslbtlity over the nose durtng the climb. 7 30ll 5 t7 SECTION III THE PIPER CHEROKEE STALTS stalt characteristics of tfie cherokee are conventional. Visual stall warning is provided by a red light located on the left side of the instruÅnt panel which is turned on automatically betwcen 5- and 1O miles per hour above stall spced. Gross weight stalling speed with.power off and full flaps is 52 miles pcr hour at 1950 pounds and 54 miles per hour at 215o pounds. With flaps up this sPeed is increased 9 miles per hour. lntentional sPins are prohibited in the normal category airplane' For approved maneuver§ and entry speeds refer to the Flight Manual' CRUISING The cnrising speed of thå Chetokee is determincd by many factos including powei setdng, altitude, temPcraturg loading, and equipment installed on the airPlane. The normal cruising power is 75% of the rated horsepower-of the engine. Tnre airspeedr, wi,ict may be obtained at *eriors altitudes and polwer rettings, can be determined from the chans in "Section IV" of this handbook. Usc of the mixture control in cmising flight reduces fuel consumption significantly, especially at higher dtiodes, and rcduces fuels are used. The mixture should be lead deiosits wfren thc "it"-it. leaned whcn 75o/o power or less is being used, If any doubt exists-T-t9 the amount of power being used, the mixture should be in the FULL RICH position for all opirations. Æways enrich the mixture before increasing powcr settings -continuous ,se of carburetor heat during cruising flight The decreases engine efficiency. unles icing conditions in the carburetor are severe, do not cruisc with thc heat on. Apply full carbuetor heat slowly and only for a few seconds at intervals determined by icing seventy, In- order to keep the airplane in best lateral trim during cruising flight, the fuel should be used elternately from each main tank' It is rJommended that one main tank be used for one hour after take.off; the other main tank used until nearly exhausted, then return to the first main tank. r8 770527 tl.l:.v Kiesersd THE PIPER CHEROKEE sEcTroN llr MANEUVERS The alrpl,ane ls approved for certain aerobatic måneuvers up to a gross welght of 1950 lbs., provided it is loaded within theapprovedweight and center of gravity limits. (See Airplane Fli.ght Manual) The maneuvers are spins, steep turns, lazy elghts and chandelles. APPROACH AND TANDING The airplane should be trlmmed to an approach speed of about 85 mlles per hour with flaps up. The flaps can be lowered at speeds up to ll5 miles per hour, if deslred, and lf approach speed is reduced 3 miles per hour for each additlonal notch of flap. Carburetor heat should not be applled unless there ls an indicatlonof carburetor iclng slnce the use of carburetor heat causes a reduction ln power which may be critical in case of a go-around. Full throttle operationwlth heaton is likelytocause detonation. The amount of flap used during landings and the speed of the aircraft at contact with the runway should be varied according to the landlng surface and existing condltions, both windwise and loadwise. It is generally good practlce tocontact the grotrnd at the minimum possible safe speed consistent with existing conditlons. Norrnalln the best technlque for short and slow landings is to use full flap andenough powertomaintain thedesired airspeedand approach fltght path. Mixture should befullrich, fuel on the fullest tank, carburetor heat off, and electric fuel pump on. Reduce the speed during the flareoutand contact the ground close to the stalling speed (55to65 MPIfl. After gtound contact hold the nose wheel off as long as possible. As the airplane slols down, drop tlre nose and apply the brakes. There wlll be less chance of skidding the tires lf the flaps are retracted before 7301 I s r9 SECTION UI THE PIPER CHEROKEE applying the brakes. Braking ls mosteffectivewhen back pressure isapplted tothe control wheel, pufttngmost of the atrcraft wetght on the maln wheels. In high wlnd condttlons, ParticuIarly ln strong cross-winds, lt may be desirable to approach the ground at htgher than normal speeds with partial or no flaps. To stop the engine after landing, pull the mixure control full back to idlc crt-off. trYhen dternatc fuels arc used, the engine should be run up to 12OO RPM for one minute prior to shutdown to clesn out any unburned fuel. Æter the engine stops turn magneto and mætcr switches off. MOORING The Cherokee should be moved on ttre ground with the aid of the nose wheel tourhar providedwith each plane and secured tn the baggage compartment. Tie downs may be secutedto rings provided under each wing, and to lhe tall skid, The aileron and stabtlator controls should be secured by looping the safety belt through the control wheel and pulling lt tight. The rudder is held in positlon by lts connections to the nose wheel steering, and normally does not have to be secured. The flaps are locked when in the full up positlon, and should be left retracted. WEIGHT AND BAIANCE It is the responsibility of the owner and pilot to determine that the airplane remains within theallowable weight v§ certer of gravity envelopewhllein flight. For weight and balance data see the Airplane Flight Manual and Weiglrt and Balance Form supplied with each alrplane. L9a 770527 sEcTroN lv PERFORMANCE CHARTS Takeoff DistancevsDensityAltinrde Rate of Climb vs Dcnsity 1 Altitude . .. ... , 20 . . . . 2l TrucAirspccdvsDensityAltitude(l9Solbsgrosswt) , . . ,. . . 22 TrueAirspeedvsDcnsityAltitudc(2150lbsgrosswt), . . . . . . 2, Rangc vs Density Altitude (1950lb,s gross wt) . . 23a- Range vs Density Altitude (2f 50 lbs gross wt) . . 23b PowervsAltinrde(l950 lbsgrosswt) ,,.....24 lbsgroswt) ...,.,.25 PowervsAltitude(2l5O Landing Distance vs Density Glide Distancc vs Altitude Altitudc AltitudeConversionChart. 7rotts . , 25a , . . 2Jb .,..,..26 THE PIPER CHEROKEE SECTIONIV PIPER CHEROKEE PA-29-140 [AME.@FF DOSIIANGE vs"llt I ALIIITUDE_] ,[ I,*lrrL"'] ns. §r0ss mf,rf trtrttr rlllr 0f clmr It t ,000 I ri0uE ,000 II. ls ivl lo I I lll I ,l 8000 I - I tmo I E § t Eiltl e ,l < > > -§7 ttll F I I § §1 3C00 § ø a e 2000 t, : t000 I ^-0 500 I 00t 1500 2000 1500 3000 tlol TllE - 730r15 lt0l oft l[§nrct ttET 20 THE PIPER CHEROKEE SECTION IV PIPER CHEROKEE PA-28-140 tttttr 16000 RATE OF CLIMI VS DENSITY ALTITI DE \ I --14000 ttll H rzooo ,.t I l95O LBS. GROSS W] 2150 LBS GROSS W' ttl \\ \ \ \ ct f E roooo tr fz. sooo UJ ct 6000 \ \ 4000 2000 o \ loo 200 too.loo 500 6()0 700 800 90() looo RATE OF CLIMB-FEET PER MINUTE 2l 730rr5 THE PIPER CHEROKEE SECTION IV PIPER CHEROKEE PA-29-140 TRUE AIRSPEED VS DENSITY ALTITUDE FULL THROTTLE r2000 toooo 80()0 6000 4000 200() o 730llt 22 THE PIPER CHEROKEE SECTION IV PIPER CHEROKEE PA-28-t40 tltttll TRUE AIRSPEED VS DENSITY ALT]TUDE --- 2I5O LB§ GROS§ w1 t4000 rlltt 12000 }( F trJ H pooo I o "; l E Eooo \ IG !z eooo L:q el tl.t a ie/ 4000 2000 o I I I loo I ilo I I 120 130 t40 150 t60 rRUE AIRSPEEO, M.PH. 23 65(b30 THE PIPER CHEROKEE SECTIONTV PIPER CHEROKEE PA-28-140 tttttrt L- RANGE T F I t4000 VS OENSITY ALTITUDE 1950 L8S. GROSS rlrt 36 GAL.FUEL (slondod) ---' - 50 GAL.FUEL (rith reserve)_ 'åe 12000 F l! lr, L )g - roooo - II aQo ilt ål lrJ o F b eooo F f; 6 eooo lt i ti ;o D tl t I I ilt I Ht I I I I tt/l-/ I I I 4000 VI I I 2000 I I I I I I il !O I I I t I ) 500 600 700 eoo 900 looo llo0 RANGE. MILES 7rott5 23a SECTION IV T'HE PIPER CHEROKEE PIPER CHEROKEE PA-29-140 36 GAL. FUEL(shndordl ----lrrr t4000 50 GAL. FUEL (wilh rcscrvel ;€ a åe o t2000 I , I F |o lrJ @ H roooo I ut o f 5 iS I to sooo -A I I I ,l I F o 4000 t: I I I I I I I I o I , I I I I _t I 2000 I I Iut 6000 I I I I I 500 600 700 800 900 rooo iloo RA^IGE, MILES 730115 THE PIPER CHEROKEE SECTION IV PIPER CHEROKEE PA-28-140 . POWER -VS - ALTITUDE t950 LBS. GROSS WT. t4000 F lrj lrJ L -o t2000 I I l.V *'/l* I t l- TOOOO f F F d Booo F U) fr o 6000 | 'e (, ø _<r _)_ * rsl ,l # 2000 o E)_ q. (, § a. (r' Q / s*. -å 4000 lo- o 10 ,A ^§r,r^s7 I *-lrl_l I - *'/[ I-) 2000 2lo0 2200 2300 2400 2500 2600 2700 ENGINE SPEED - R,PM ENGINE SPEEO - R.P.M. 730115 24 SECTIONIV THE PIPER CHEROKEE PIPER CHEROKEE PA-28-140 rtt POWER VS AUT|TUDE ttr r50 .8S. GRO ss li r4000 F tzooo / UJ trl 5 roooo F 5 < II / .r1 "+ ls/ * a u +' 8000 Q'r lJ/ F al, a' z B eooo 4000 2000 e^r§rcft lo o I N 2000 2loo 22c0 2300 ?4c,0 2500 2600 27c/c ENGINE SPEED-RPM. 2S 730115 THE PIPER CHEROKEE SECTION IV PIPER CHEROKEE PA-28-140 # + LANDING DISTANCE t tr tr -i DEN'ITYXLT.'UDE I -l FL, APs 4oo POTI'ER OFF PAVED LEVEL DRY RL INTIOAY 'No WND I IIAXIMUM BRAK]NG SHOBT FIE] DE FFORT' 7000 F trJ lrl L tl 6000 E 5 < 5000 F t95o LBS. GRosS - -T-r2rsoLBs. offl*'j J -it -: I -o+EI 3r, z H 4ooo -oL zl P l-l 3000 wr. I 'rfi I JI ol -<f J- l 6t Fl_ iH :hr *F 2000 I I roo0 I o 200 400 600 800 looo 1200 1400 LANOING OISTANCE, FEET 730115 25a sEcrIoN lv THE PTPER CHEROKEE PA-2E-140 PIPER CHEROKEE llllll GLOEE EDSTANCE vs AUTOIIUDE rrrlll talll E- uto, --- ! ruu a :l E rnr IIII fl$m a |l lr.r, 3l|0 trortr[r ilr -Ms lllt 0. a0[0 tl0t ! alllltlt2lt8 atrt urc[ ruI§ 2sb 7ror,5 THE PIPER CHEROKEE SECTIONIV PIPER CHEROKEE PA-28-140 lllllllllll AL]IIIIUDE GQ)INVEIiI§||a)IN gIfiJ4\IB]I fit§ GIrm $u,[0 lE uso n oEttilltt ot§n [TluDr rnof, EI§IltS IHmrIUnt rID Pntssu[E rllluffi GffiDlIlo§ r0r ust ilTlrErmilrlff Gilm§. 1{000 20000 r§l tr ,d»r ;18000 c U» $9 t > 12000 \1t - ir! l/ A t00t +- G ia T \[E» -i \ b!. .!il-- L .t0 .10 0 20 13 ITTPMIIURT . 'F 7 3011 5 iL 80 l! 100 sEcfloN v I GENERAT MAINTENANCE Tire lnflation 27 Battery.Scwice 27 Scrvicc 27 Scrvice Fuel Requiremens 28 Brakc Landing Gear Carc of Air Filtcr CarcofWindshiddandWindour ....., . Lcvcling end Rigging Scriel Nunbcr Plrtc 770527 30 t2 32 ,, )3 , TTIE PIPER CH EIIOKI-.]IJ SIjCT'I()N V sEcfloN v GENERAT MATNTENANCE TIRE INFTATION F'or rtraxinrurl service fronr the tires ()n thc Chcrokcc, kt.cp the tlres inflatetl t() the proper pressurc of 24 pr»untls for thc nrain gear an<l 24 pountls for thc. nose whccl. lnterchlngc thc tires on the nrain wheels, if necessary, to pr«rtluce, even \t,cilr. AII wheels an<l tires are balancccl bcfore original lrrstullation, and the relationship of thc tire, tube and whccl shoukl bc ur:rin- tained, if at all poo-sible. Out of balancc wheels con causc (,xtrenle vibration on take-off. In the installation o[ new cotup(rnents, it nray be necessary to rebalance thc' whce,lwith thc tire s nrounted. BATTERY SERVICE The l2 volt hattery is locate'd in a stain.lcrss stcel containe,r under the baggage conrFlrtment floor. Thc containersllould l)e d rained occasional I y by opening t he nrbber ca p on t lrc d rain I ul)c. Check the batte ry fo r propcr tluid levc'l (bek»v tlrc baf flc platcs ). Use a hydrometer to determine thedensity of the battcry fluid. If the battery is discharged, clrarge lt llcfore takc-off as tlrrce volts areneeded toexcitcthe alternator. Rcchurgcstarting at a 4 anrp rate and finishing witlt a 2 amp rate. Quick charges are not recommended. BRAKE SERVICE Tlre brake system is filled with MIL-ll-5606 (petrolcunr 6ri0s0 t 27 SECTION V THE PIPER CHEROKEE base) hydraulic brake fluid. This should be checked at evertI00 hour inspection and replenished when necessary by filIurg the brake resenroir on the firewall to the indicated level. If the system as a whole has to be refilled with fluid, this should be done by filling with the fluid under pressure from the brake end of the system. This will elimlnate air from the system as it is being filled. No adjustment of brake clearances is necessary on the Cherokee, If after extended sewice the brake blocks become worn excessively, they are easilyreplaced with new segments. TANDING GEAR SERVICE Main wheels are easlly removed by taking off the hub cap, axle nut, and the two bolts holding the brake segment in place, after wNch the wheel slips easlly from the axle. Tires are removed from the wheels by first deflating the tire, removing thethreethroughbolts, and separating thewheel halves. Landing gearoleo stnlts should be checked for proper srrut exposures and fluid leaks. The required extensions for the strut when under normal static load (ernpty weight of airplane plus tuII tuel and oil) is 3. 25 inches for the nose gear and 4. S0 incbes for the main gear. Should the strut exposure be belor,v that required, it should be determined whether alr or oil is required by first raisirg the alrplane on jacks. Depress the valve core to allowair toescape from thestrut housing chamber, Remove the filler plug and slowly raise the strut to full compression. U the strut has sufficient fluid itwill be visibleupto the bottom of the filler plug hole and will then only require proper inflation. Should fluid be below the borrom of the filler plug hole, oil should be added, Replace the plug with valve core remqved, attach a clear plastic hose to the valve stem of the filler plug and submerge the other end in a container of hydraulic fluid (MIL-H-5606). Fully compress and extend the strut several 2B 670424 THE PIPER CHEROKEE sEcTtoNv FUEL SELECTOR VALVE RIOI{T TAilK LEFT TANX FUEL OUANTITY GAUCES 29 SECTION V THE PIPER CHEROKEE times thus drawlng fluid from the container and expelllngair from the strut chamber. To allow fluid to enter the botrom chamber of the main gear stnrt housing, the torque link assem bly must be disconnected to let the strut be extended a minimum of l0 inches, (The nose gear torque llnks need not be disconnected.) Do not allow the stmt to extend more than l2 inches. When air bubbles cease toflow through the hose, compress the strut fully and againcheck fluid level Reinstall the valve core and filler plug, and the main gear torque links if disconnected. Wit With fluid in thestrut housingat thecorrect level, artach a strut pump to the air valve and with the airplane on the ground, inflate the oleo strut to the correct heiglrt. In jacking the Cherokee for landing gear or other service, jack a kit (available through the PiperAircreft Sewice Depart ment) should be used. This kit conslsts of two hydraulic jacks and a tail stand. At least 350 pounds of ballast should be placed on the base of the tail stand beforejacking up rheairplane. The hydraulic jacks should be placed under the jack points on the bottom of the wing and the airpl,anejacked up until the tail skid is at the right height to attach the tail stand. After attaching the tail stard, and adding the ballast, rhe jacking may be continued until the airplane is at the height desired. FUEI REQUIREMENTS The minimum aviation grade fuel for åe pA-28-f4O is g0/87. Since the use of low€r grades can cause serious engine drmage in a short pcriod of time, rhe engine warranEy is invalidated by the use of lowcr oclanes. Whcnoer 8O/E7 is not av&ilable, rhe low6r lcad 100 grade should be used. (Sec Fuel Grade Comparison Chan, next page.) Refer to the Latest issue of Lycoming Service Insrnrcrion No. 1070 for addirional information, The continuous us€, more than Z1oh of thc opcraring time, of thc higher leadcd fuels can result in increased eogine deposits, both in the combustion chamber and in the engine oil. It may require increased 30 770527 THE PIPER CHEROKEE SECTION V spsrk plug meintcna.nc! and morc frcqucnt oit changcs. The frcquency of sperk plug maintenancc and oil drain pcriods will bc governeC bv thc amount of lead pcr gallon and thc rypc of.opcration. Opcration at full rich mixrure rcquires inorc frcqucnt mainrenance pcriods; thcrcforc, it is important ro use propcr approved mixturc leaning proccdures. 'i Rcfcrcncc the latcst issuc of Lycorning Scrvicc Lcttcr No. Llg5 for carc, opcration,rnd mlintcnanc. of dhc airplanc whcn using tlre highcr lcaded fud. A summary of thc current grades as well as thc previous fuel dcsignatioru arc shown in rhc following chan: FUEL CRADE COMPARISON CTIART Pnviou Commrr<i:l Fucl Grd6 (^ST[LD9lo) Cu..m( Mili(lry Curtnr ('bmmcacial I;ucl Gr:dc! (ASTM-)9lG7r) Fucl Gndcr (^tll--G-JJ72li) ^mandmcnr (lrerlc Cul r Har, TEL ml/U S gzl 8(Vff7 9lle6 rm/tJo Iil/l4l b luc ta(!n purplc i ( r.d( ot 80 z0 'l00LL l.o l([ 4.6 ,Uax TEL (:oldr ml/U,S.8rl. rcd blu< o.5 2.0 8(ccn 't. o (itrdc tolil 100/uo t t5l 1+t No t Mu. Tl:L Co or rad gr«n purpl. ml/U.S. gd 0.5 " J.o 4.6 :..n1#,'?,-Jå:ffi ';"J;:i:i'åt'l:';ifr [1;'I,;:f ::5;l*-#:'iliJili;l?h;*", up ro .a mUU.S. BlUon rrc approvtd Io. ut. in rll engin<, I crdfiarcd for u* wirh Frdc loo/l rO tuel. OIL REQUIREMENTS The capaciry of the 0-320 scries engine is 8 qurrts, and the minimum safc quantity is 2 quarts [t is rccommcndcd that t]re oil be changcd crrcry 50 hours and sooner. under unfavorablc operating -conditions. Interrels bctween oil changcs can be incrcased as much as 100% on cngines cquipped with full flow carridge typc oil filters, prorridcd the elemerrt is rcplaccd cach 50 hours of opcration and the specificd octane fuel is used. Should fucl other than the specified o«ane rating for the powcr plant bc uscd, rcfcr to the latcst issuc of Lycoming Servicc Letter No. L185 and Lycoming Service Irutruction No. 1014 for additional information and recommcndcd scrvice 770527 3l SECTION V THE PIPER CHEROKEE proccdures. Thc following grades ere recommended for tJrc specificd temPcratures: Tcmpcratwcs above 60oF Tempcratures bctwcen 30oF to 90oF Temperatuies between 0oF to TOoF Temperatures bclow 10oF SAE 5O SAE 40 SAE 30 SAE 20 Either mineral oil or anti-dispcrsånl oil may bc uscd, but the two typcs of oil may never bc mixcd. CARE OF AIR FILTER The ca rbu retor a I r filte r must be cl caned at least once every fifty hours. Under extremelyadverse conditionsof operatiott it may be necessary to clean the filterdaily. Extra filters areinexpensive and a spare should be kept on hand and used a:; a rapid replacement. The filter manu(acturer recommends thar the filterbe tapped gently to remove dirt particles. Do not blow out \ryith compressed air. CARE OF WINDSHIELD AND WTNDOWS A cerrain amount of care is ncedcd to keep the plexiglass win<low.s clcun and untnarrctl. 'l'hc following procctlurc is rccollt rtrc nrlctl: l. Flush witlr clean wate r and tlislodge excess dirt, mud, etc . , with your lund. 2. Wash with mild soap and water. Use a soft cloth or sponge, do not nrb. 32 770527 THE PIPER GHEROKEE SECTION V 3. Remove oil, grease or sealrng compolrnos wrth a sofr cloth and kerosene. 4. Afler cleaning apply a thin coat of hard polishing wax Rub lightly with a soft cloth. 5. A severe scratch or mar may be removed by using jeweler's rouge to rub out the scratch, smoothing, and then applying wax. SERTAL NUMBERPLATE The serial nurnber plate is located near the stabilator on the left side of the airplane . Refer to this number for service or warranty matters. LEVELING AND RIGGING Leveling the Cherokee for puposes of weighing or rigging is accomplished as follows: l. Partially withdraw two machine screws locaM irnmdiately below the left front side window. Thæe screws are leveling points and the airplane is longitudinally level when a lwel placed on the heads of thæe screws indicates level. 2. To put the airplane in a longitudinally level position on scales, first block the main gear ol.eos in the firlly extended position, then deflate the nose wheel tire rrntil the proper attitude is obtained. For rigging only, the airplane ruay be placed on jacks for leveling. 3. To level the airplane laterally, place a lwel across the baggage compartment floor along the rearbulkhead. Rigging: Æthough the fixed flight surfaces on the Cherokee cannot be adjusted for rigging purposæ, it may be necessary upon occasion to check the position of these surfaces. The mo.vable surfaces all have adjustable stops, as well as adjustable turnbuckles on the cables or push-pull tubes, so that their range 770527 9tr e<- gEE 6 H: EO =a f-- I I L" z o ts (J El :i THEPIPERCHEROKEE SECTION V of Lravel can be altered. The positions and angular travels of the various surfaccs are as follows: 1. Wings: 7o dihedral,2" washoul 2. Søbilator Travel: l8': up, 2o down, tolerance * lo. 3 Fin should be vcrtical and in line wih center of fuselage . 4. Ailcron Travcl: 30" up, 15" down, rolcrancc+ 2". 5. Flap 'fravcl: 0", 25', 40o, tolerance + 2"6. Ruddcr Travcl: 27" right and ldft, lolcnrn«r + 2o. 7 - Surbilator Tab Travcl: 3"up, l? &lwn, tolcmncc f -l ". 1 Cablc tensions for thervarious controls arc as follows: Rudden,l0 t5 lbs, Ailerons:4Ot5 lbs. 9 1030 I Stabilars:40 +5 lbs. StabilaorTrim: 14 tl lb. 35 'f ltE PtI'riR cl{liR oKUrl (,r, I',UJ,IlqA:IlOll CiråJ!'J IOrr . . \, Prpunc[.runoruuiz]\-atl.t{ro I I il;----_l rriro l"l*"a I I I olrll lil' o l*" I *ollli Olav Klesercd INDEX I SpecificationFeaturcsr Performance SECTTON Itowcr I'Lutt FuelandOil ... ....,.. ...... Dimensions Landing Gear . Starting Warnrup GroundCheck . Takeoff Climb. Stslls..... Cnrising Mananvers Approachandlanding Mooring Weight and Bdance 770527 z 3 3 Informations Sructures Landing Gear Conuol Systcm FuelSystem ...... ElectricalSystem ........9 HeetingandVcntilatingSystem ..... CabinFeanrres .,... Opcratinglnstrucions: 1 I J SECTION II Design SECTION III Pag. . ...... 5 6 6 7 8 1O 12 13 .,..1+ ..,f5 ,... 16 . .. 16 ....17 .....18 ....18 .......19 ..... 19 ...19a . . l9e INDEX (cont.) SECTION lV Takeoff DistanccvsDcruityAltitude Rate of Climb vs Densiry Altitude True Airspced vs Density Altitude (f95Olbsgrossweight) Pagc . . - . . . 20 . . . 2L .....-.22 True Airspeed vs Dcnsiry Aldtudc (2150 lbs. gross weight) Range vs Density Altitude (1950 lbs, gross wt) Rangc w Density Altirudc (2150 lb6, gross r+r) Power vs Ntitude (1950 lbs. gross weight) Powcr rrs Altitudc (2150Ibs. gross wcight) 23 232 23b 2+ 25 252 Glidc Distance vs Altitude 25b Altitude Convcrsion Chan . 26 SECTION V 'GeneralMaintcnancc , . , Tirelnflation BettcryServicc BrekeServicc LandingGcarService FuclRequircments OilRcquirements.. Wilr«lowc Ssill Nunrbcrtrhtc.. Carc of Windshickl antl ....27 . ....27 ....27 .....27 .. ....28 .:..... !O ,.....31 . . . . 32 .....33 770527 ">

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Key features
- Four-seater aircraft
- Lycoming O-320 engine
- 140 horsepower
- Cruise speed of 100 mph
- 36-gallon fuel capacity
- Range of 515 miles
- Aluminum alloy construction
- Full-time power electrical system
- Heating and ventilating system
Frequently asked questions
The Piper Cherokee 140 is powered by a Lycoming O-320 engine.
The cruise speed of the Piper Cherokee 140 is approximately 100 mph.
The range of the Piper Cherokee 140 is 515 miles with a standard 36-gallon fuel capacity.
The Piper Cherokee 140 is constructed from sturdy aluminum alloy.
Yes, the Piper Cherokee 140 is equipped with a heating and ventilating system.