manual - Mr. Webman
Contents
1. 49 753 806 740118 SECTION SPECIFICATIONS Performance Weights Power Plant Fuel and Oil Baggage Dimensions Landing Gear 691015 CHEROKEE E SECTION SECTION 1 SPECIFICATIONS PERFORMANCE Published figures are for standard airplanes flown at gross weight under standard conditions at sea level unless otherwise stated Performance for a specific airplane may vay from published figures depending upon the equipment installed the condition of engine airplane and equipment atmospheric conditions and piloting technique Each performance figure below is subject to the same conditions as on the corresponding performance chart from which it is taken in the Performance Charts Section Take off Run maximum effort 25 flap ft 720 Take off over 50 ft barrier maximum effort 25 flap ft 1625 Best Rate of Climb Speed mph 85 Rate of Climb ft per min 725 Service Ceiling ft 13 000 Absolute Ceiling ft 15 000 Top Speed mph 152 Optimum Cruising Speed 7596 power optimum altitude mph 143 Cruising Range 75 power optimum altitude mi 725 Optimum Cruising Range 5596 power optimum altitude mi 845 Stalling Speed flaps down mph 57 Stalling Speed flaps up mph 67 Landing Roll flaps down ft 600 Landing Roll over 50 ft barrier ft 1150 753 806 1 740118 SECTION SPECIFICATIONS cont WEIGHTS Gross Weight Ibs Empty Weight Standard Ibs USEFUL LOA2. 22 e er br DE 48 Leveling and 48 Serial Number Plate ERR EE 49 753 806 740118 CHEROKEE E SECTION VI SECTION VI GENERAL MAINTENANCE This section of the Cherokee Handbook contains infor mation which pertains to minor maintenance of the airplane For further maintenance assistance refer to the Service Manual for this airplane Any complex repairs or modification should be accomplished by a Piper Certified Service Center or equivalent LANDING GEAR SERVICE The main wheels are Cleveland Aircraft Products Model 40 86 with Cleveland single disk hydraulic brake assemblies Model 30 55 The nose wheel is a Cleveland Aircraft Products Model 38501 All wheels use a 6 00 x 6 four ply rating type tire with tube Main wheels are easily removed by taking off the hub cap axle nut and the two bolts holding the brake segment in place after which the wheel slips easily from the axle Tires are demounted from the wheels by deflating the tire removing the three through bolts and separating the wheel halves Landing gear oleo struts should be checked for proper strut exposures and fluid leaks The required extensions for the strut when under normal static load empty weight of airplane plus full fuel and oil is 3 25 inches for the nose gear and 4 50 inches for the main gear Should the strut exposure be below that required
3. 40 Landing Distance vs Density Altitude 41 Power Setting Table poania raeno 42 753 806 740118 CHEROKEE SECTION III The take off technique is conventional for the Cherokee The tab should be set slightly aft of neutral with the exact setting determined by the loading of the aircraft Allow the air plane to accelerate to 50 to 60 MPH then ease back on the wheel enough to let the airplane fly itself off the ground Pre mature 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 speed by lowering the nose slightly Take offs are normally made with flaps up However for short field take offs and for take offs under difficult conditions such as deep grass or on a soft surface distances can be re duced appreciably by lowering flaps to 25 CLIMB The best rate of climb at gross weight will be obtained at 85 MPH The best angle of climb may be obtained at 74 MPH At lighter than gross weight these speeds are reduced somewhat For climbing en route a speed of 100 MPH is recommended This will produce better forward speed and increased visibility over the nose during the climb STALLS All controls are effective at speeds down through the stalling speed and stalls are gentle and easily controlled Stall speed chart on following page is at gross weight Stall speeds at lower weigh
4. PIPER CHEROKEE 180 E OWNER S HANDBOOK WARNING The rudder pedals are suspended from a torque tube which extends across the fuselage The pilot should become familiar with the proper positioning of his feet on the rudder pedals so as to avoid interference with the torque tube when moving the rudder pedals or operating the toe brakes 757 436 CHEROKEE 180 E PA 28 180 This handbook for airplanes with serial nos 28 5601 through 28 5859 Owner s Handbook i PIPER Piper Aircraft Corporation Vero Beach Florida U S A NOTICE THIS HANDBOOK IS NOT DESIGNED NOR CAN ANY HANDBOOK SERVE AS A SUBSTITUTE FOR ADEQUATE AND COMPETENT FLIGHT INSTRUCTION OR KNOWLEDGE OF THE CURRENT AIRWORTHINESS DIRECTIVES THE APPLICABLE FEDERAL AIR REGULATIONS AND ADVISORY CIRCULARS IT IS NOT INTENDED TO BE A GUIDE OF BASIC FLIGHT INSTRUCTION NOR A TRAINING MANUAL THE HANDBOOK IS DESIGNED 1 TO HELP YOU OPERATE YOUR CHEROKEE WITH SAFETY AND CONFIDENCE 2 TO MORE FULLY ACQUAINT YOU WITH THE BASIC PERFORMANCE AND HANDLING CHARACTERISTICS OF THE AIRPLANE 3 TO MORE FULLY EXPLAIN YOUR 5 OPERATION THAN IS PERMISSIBLE TO SET FORTH IN THE AIRPLANE FLIGHT MANUAL IF THERE IS ANY INCONSISTENCY BETWEEN THIS HANDBOOK AND THE AIRPLANE FLIGHT MANUAL APPROVED BY THE THE AIRPLANE FLIGHT MANUAL SHALL GOVERN Revised text and illustrations shall be indicated by a black vertical line in the margin opposite the change
5. SECTION Il Cherokee HEATING AND VENTILATING SYSTEM CHEROKEE gt Fresh Air D Cabia Heat 1 Fresh Air Control 4 Defroster Air Outlet 2 Defroster Control 5 Fresh Air Inlet 3 Heater Control 6 Cabin Exhaust Outlet 691212 CHEROKEE E SECTION relay If ammeter continues to indicate no output maintain mini mum electrical load and terminate flight as soon as practical Maintenance on the alternator should prove to be a minor factor Should service be required contact the local Piper Dealer HEATING AND VENTILATING SYSTEM Heat for the cabin interior and the defroster system is pro vided by a heater muff attached to the exhaust system The amount of heat desired can be regulated with the controls located on the far right side of the instrument panel Fresh air inlets are located in the leading edge of the wing at the intersection of the tapered and straight sections A large adjustable outlet is located on the side of the cabin near the floor at each seat location Cabin air is exhausted through an outlet located below the rear seat CABIN FEATURES The instrument panel of the Cherokee is designed to ac commodate the customary advanced flight instruments and the normally required power plant instruments The Artifical Horizon and Directional Gyro are vacuum operated through use of a vacuum pump installed on the engine while the Turn and Bank instrument is electrically operated Above the Attitude Gyro
6. 740118 SECTION V PERFORMANCE CHARTS Altitude Conversion Chart 36 Takeoff Distance vs Density Altitude 37 Rate of Climb vs Density Altitude 38 Range vs Density Altitude 39 True Airspeed and RPM vs Density Altitude 40 Landing Distance vs Density Altitude 0 41 Power Setting Table cueca 28 42 753 806 740118 CHEROKEE E SECTION V PA 28 180 PIPER CHEROKEE 1 ALTITUDE CONVERSION CHART THIS CHART SHOULD BE USED TO DETERMINE DENSITY ALTITUDE FROM EXISTING TEMPERATURE AND PRESSURE ALTITUDE CONDITIONS FOR USE WITH PERFORMANCE CHARTS 24000 TI TITI 20000 2 10 pass Un y E ROS i u 10000 ca E 5 12000 pom q 5 s N qa 8000 Nie a A a d ES Na gt 40 20 0 20 40 60 80 100 TEMPERATURE F 753 806 36 740118 SECTION V 28 180 PIPER TAKE OFF DISTANCE Vs DENSITY ALTITUDE MAXIMUM EFFORT 25 FLAPS PAVED LEVEL DRY RUNWAY 7000 1000 5000 4000 3000 BENSITY ALTITUDE FT 2000 1000 0 50
7. A line opposite the page number will indicate that material was relocated Additional copies of this manual Part No 753 806 may be obtained fromyour Piper Dealer Published by PUBLICATIONS DEPARTMENT Piper Aircraft Corporation 753 806 Issued October 1969 Revised January 1974 INDEX SECTION Page Specifications Sow Performance 1 Weights 2 Power Plant 2 Fuel and Oil 2 Baggage 2 Dimensions 3 Landing Gear 3 SECTION Il Design Information 5 Engine and Propeller 5 Structures 5 Landing Gear 6 Control Systems 7 Fuel System 7 Electrical System 9 Heating Ventilating System 13 Cabin Features 13 SECTION Ill Operating Instructions 16 Preflight LO Starting Engine rt a Warm Up and Ground Check Se Eos 19 Take Off 2 25 ooo 519 Climb ca 222 0222 m Uk ww Roc o 220 Stalls 2 2 4 ouod S decim 0 20 Cruising fas put Qs oe ell Approach and Landing o xr 222 Stopping Engine 23 691015 INDEX cont SECTION II cont Page Engine Power Loss 23 MOOFID 22525 pipe 24 Weight and Balance 24 Operating Tips a 23m bun bo Rd ue ARS 24 SECTION IV Emergency 27 Introduction ek 27 Engine Power Loss During Takeoff 27 Engi
8. the ammeter will indicate 0 output from the alternator relay may be reset by switching the ALT switch to OFF for approximately one second and then returning the ALT switch to ON 7 The vacuum gauge is provided to monitor the pressure available to assure the correct operating speed of the vacuum driven gyroscopic flight instruments It also monitors the condition of the common air filter by measuring the flow of air thru the filter If the vacuum gauge does not register 5 1 Hg at 2000 RPM the following items should be checked before flight a Common air filter could be dirty or restricted b Vacuum lines could be collapsed or broken c Vacuum pump worn d Vacuum regulator not adjusted correctly The pressure even though set correctly can read lower under two conditions 1 Very high altitude above 12000 feet 2 Low engine RPM usually on approach or during training maneuvers This is normal and should not be considered a malfunction 25 753 806 740118 CHEROKEE E SECTION Ill 8 The shape of the wing fuel tanks is such that in certain maneuvers the fuel may move away from the tank outlet If the outlet is uncovered the fuel flow may be interrupted and a temporary loss of power may result Pilots can prevent inadvertent uncovering of the outlet by avoiding maneuvers which could result in uncovering the outlet Running turning takeoffs should be avoided as fuel flow interruption may occur if tank in
9. amount of charging current demanded by the battery As each item of elec trical equipment is turned on the current will increase to a total appearing on the ammeter This total includes the battery The maximum continuous load for night flight with radios on is about 30 amperes This 30 ampere value plus approximately two am peres for a fully charged battery will appear continuously under these flight conditions The amount of current shown on the ammeter will tell immediately if the alternator system is operating normally as the amount of current shown should equal the total amperage drawn by the equipment which is operating If no output is indicated on the ammeter during flight reduce the electrical load by turning off all unnecessary electrical equip ment Check both 5 ampere field breaker and 60 ampere output breaker and reset if open If neither circuit breaker is open turn off the ALT switch for 1 second to reset the overvoltage 10 753 806 740118 CHEROKEE E LIFT DETECTOR dz STARTER FUEL GAUGES SOLENOID STARTER P STARTER SWITCH FUEL TANK SENDERS ALTERMATER OUTPUT y CIRCUIT PROTECTOR MASTER SOLEROW BATTERY SLE O ALTERNATOR CIRCUIT PROTECTOR VOLTAGE OVERVOLTAGE REGULATOR PROTECTOR BEE mel Jun ay L ALTERMATOR 6 9 RADIO INTERFERENCE CAPACITOR 691015 SECTION Il ALTERNATOR SOURCE POWER RELAY ENERGIZING CIRCUIT ELECTRICAL SYSTEM 11
10. height In jacking the Cherokee for landing gear or other service a jack kit available through Piper Dealers or Distributors should be used This kit consists of two hydraulic jacks and a tail stand At least 250 pounds of ballast should be placed on the base of the tail stand before the airplane is jacked up The hydraulic jacks should be placed under the jack points on the bottom of the wing and the airplane jacked up until the tail skid is at the right height to attach the tail stand After attaching the tail stand and adding the ballast the jacking may be continued until the aircraft is at the height desired The steering arms from the rudder pedals to the nose wheel are adjusted at the rudder pedals or at the nose wheel by turning in or out the threaded rod end bearings Adjustment is normally accomplished at the forward end of the rods and should be done in such a way that the nose wheel is in line with the fore and aft axis of the plane when the rudder pedals and rudder are centered 44 753 806 740118 CHEROKEE E SECTION VI Alignment of the wheel can be checked by pushing the plane back and forth with the rudder centered to determine that the plane follows a perfectly straight line The turning arc of the nose wheel is 22 degrees in either direction and factory ad justed at stops on the bottom of the forging The turning radius of the nose wheel is 17 feet The steering arm stops should be carefully adjusted
11. it should be determined whether air or oil is required by first raising the airplane on jacks Depress the valve core to allow 753 806 43 740118 SECTION VI CHEROKEE air to escape from the strut housing chamber Remove the filler plug and slowly raise the strut to full compression If the strut has sufficient fluid it will be visible up to the bottom of the filler plug hole and will then only require proper inflation Should fluid be below the bottom of the filler plug hole oil should be added Replace the plug with valve core removed attach a clear plastic hose to the valve strut of the filler plug and sub merge the other end in a container of hydraulic fluid MIL H 5606 Fully compress and extend the strut several times thus drawing fluid from the container and expelling air from the strut chamber To allow the fluid to enter the bottom chamber of the main gear strut housing the torque link assembly must be disconnected to let the strut be extended a minimum of 10 inches The nose gear torque links need not be disconnected Do not allow the strut to extend more than 12 inches When air bubbles cease to flow through the hose compress the strut fully and again check fluid level Reinstall the valve core and filler plug and the main gear torque links if disconnected With fluid in the strut housing at the correct level attach a strut pump to the air valve and with the airplane on the ground inflate the oleo strut to the correct
12. of the owner and pilot to determine that the airplane remains within the allowable weight vs center of gravity envelope while in flight For weight and balance data see the Airplane Flight Manual and Weight and Balance form supplied with each airplane OPERATING TIPS The following Operating Tips are of particular value in the operation of the Cherokee 1 Learn to trim for take off so that only a very light back pressure on the wheel is required to lift the airplane off the 691015 24 SECTION Ill CHEROKEE E ground 2 The best speed for take off is about 60 MPH under normal conditions Trying to pull the airplane off the ground at too low an airspeed decreases the controllability of the airplane in event of engine failure 3 Flaps may be lowered at airspeeds up to 115 MPH To reduce flap operating loads it is desirable to have the airplane at a slower speed before extending the flaps 4 Before attempting to reset any circuit breaker allow a two to five minute cooling off period 5 Before starting the engine check that all radio switches lisht switches and the pitot heat switch are in the off position so as not to create an overloaded condition when the starter is engaged 6 The overvoltage relay is provided to protect the elec tronics equipment from a momentary overvoltage condition ap proximately 16 5 volts and up or a catastrophic regulator failure In the event of a momentary condition the relay will open and
13. so that the nose wheel reaches its full travel just after the rudder hits its stops This guarantees that the rudder will be allowed to move through its full travel BRAKE SERVICE The brake system is filled with MIL H 5606 Petroleum base hydraulic brake fluid This should be checked at every 50 hour inspection and replenished when necessary by filling the brake reservoir on the upper left front side of the firewall to the indi cated level If the system as a whole has to be refilled with fluid it should be done from the brake end of the system by filling with fluid under pressure This will eliminate air from the system as it is being filled No adjustment of brake clearances is necessary on the Cherokee brakes If after extended service the brake blocks be come worn excessively they are easily replaced with new segments TIRE INFLATION For maximum service from the tires on the Cherokee keep the tires inflated to the proper pressure of 24 pounds for all three wheels Interchange the tires on the main wheels if necessary to produce even wear All wheels and tires are balanced before original installation and the relationship of the tire tube and 753 806 45 740118 SECTION VI CHEROKEE wheel should be maintained if at all possible Unbalanced wheels can cause extreme vibration on take off In the installation of new components it may be necessary to rebalance the wheel with the tire mounted CARE OF WINDSHIELD AND WIND
14. switch ON 3 Turn the electric fuel pump ON 4 Put mixture control in IDLE CUT OFF 5 Engage the starter by rotating magneto switch clockwise and pressing in When the engine fires advance the mixture control and move the throttle to desired setting Starting Engine When Flooded 1 Open the throttle full 2 Turn the master switch ON 3 Turn the electric fuel pump OFF 4 Put mixture control in IDLE CUT OFF 5 Engage the starter by rotating magneto switch clockwise and pressing in When the engine fires advance the mixture control and retard the throttle When the engine is firing evenly advance the throttle to 800 RPM If oil pressure is not indicated within thirty seconds stop the engine and determine the trouble In cold weather it will take a few seconds longer to get an oil pressure indication If the engine has failed to start refer to the Lycoming Operating Handbook Engine Troubles and Their Remedies Starter manufacturers recommend 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 691015 18 SECTION V PERFORMANCE CHARTS Altitude Conversion Chart 22 22 0 36 Takeoff Distance vs Density Altitude 37 Rate of Climb vs Density Altitude 38 Range vs Density Altitude 39 True Airspeed and RPM vs Density Altitude
15. switch is located in the switch panel above the throttle quadrant Each tank has an individual quick drain located at the bottom inboard rear corner and should be drained to check for 691015 7 SECTION Il CHEROKEE E FUEL PRESSURE GAUGE FUEL QUANTITY GAUGES m VENT M ENGINE FUEL PUMP S ELECTRIC FUEL PUMP DRAIN GASCOLATOR LEFT TANK RIGHT TANK FUEL SYSTEM SCHEMATIC 8 691015 CHEROKEE E SECTION water before each flight The fuel strainer which is also equipped with a quick drain is located on the front lower left corner of the firewall This strainer should be drained regularly to check for water or sediment accumulation Fuel quantity and pressure are indicated on gauges located in a cluster on the left side of the instrument panel ELECTRICAL SYSTEM The electrical system includes 14 volt 60 amp alternator battery voltage regulator overvoltage relay and master switch relay The battery is mounted in a stainless steel box imme diately aft of the baggage compartment The regulator and over voltage relay are located on the forward left side of the fuselage behind the instrument panel Electrical switches are located on the right center instru ment panel and the circuit breakers are located on the lower right instrument panel A rheostat switch on the left side of the switch panel controls the navigation lights and the dome instru ment light It also dims the dome light The similar switch
16. use is not full Prolonged slips or skids in any pitch attitude or other unusual maneuvers which could cause uncovering of the fuel outlet must be avoided when tank being used is not full 9 The rudder pedals are suspended from a torque tube which extends across the fuselage The pilot should become familiar with the proper positioning of his feet on the rudder pedals so as to avoid interference with the torque tube when moving the rudder pedals or operating the toe brakes 10 lights should not be operating when flying through overcast and clouds since reflected light can produce spacial disorientation Do not operate strobe lights when taxiing in the vicinity of other aircraft 753 806 26 740118 SECTION IV EMERGENCY PROCEDURES Introduction 22 222 22 44 2 QU 27 Engine Power Loss During Takeoff 27 Engine Power Loss In Flight 28 Power Off Landing 29 30 Loss of Oil Pressure 31 Loss of Fuel Pressure 32 High Oil Temperature 32 Alternator Failure 33 Engine Roughness 33 SPINS Scie Ae een cube da et ud 34 Open 2171 a Ge 4 cn eine a 35 753 806 740118 SECTION IV SECTION IV EMERGENCY PROCEDURES INTRODUCTI
17. 0 1000 1500 2000 2500 3000 3500 TAKE Of F DISTANCE FT 37 753 806 740118 CHEROKEE E SECTION V PA 28 180 PIPER CHEROKEE RATE OF CLIMB Vs DENSITY ALTITUDE 2400 LBS GROSS WT 16000 TI er 14000 12000 tE 10000 5 8000 lt 5 6000 4000 2000 o bs 0 200 400 600 800 1000 RATE CLIMB FT MIN 753 806 38 740118 SECTION V CHEROKEE PA 28 180 PIPER CHEROKEE T 1 bud RANGE Ys DENSITY ALTITUDE ez 2400 LBS GROSS WT 50 GAL FUEL FULL TANKS LEAN MIXTURE 10000 5 EZ 8000 3 S E x 6000 5 C3 4000 2000 0 RANGE STATUTE MILES 39 753 806 740118 SECTION V CHEROKEE E PA 28 180 PIPER CHEROKEE HAN 033097 1 9 INIOd 033450 1 OL NMOG ATIVOILH3A 8 3 0340 3001111 IWYS LV 8 H3MOd 40 0 53 19 SIHL V 6 8 183 0887 0522 0062 OL ATIVLNOZIHOH 7 H31N3 IM 8085 81 0070 Wad XUN OL 0111111 SUQLXIN SA Wee ONY 02245 INUL 6 00001 00021 DENSITY ALTITUDE FT 40 806 753 740118 SECTION V CHEROKEE PA 28 180 PIPER CHEROKEE LANDING DISTANCE Vs DENSITY ALTITUDE 2400 LBS G
18. D Standard Ibs POWER PLANT Engine Lycoming Rated Horsepower Rated Speed rpm Bore in Stroke in Displacement cu in Compression Ratio Dry Weight 165 Propeller FUEL AND OIL Fuel Capacity U S gal Oil Capacity 416 Fuel Aviation Grade min octane BAGGAGE Maximum Baggage Ibs Baggage Space cu ft Baggage Door Size in CHEROKEE 2400 1310 1090 O 360 A4A 180 2700 5 125 4 375 361 0 8 5 1 285 M76EMMS60 50 91 96 200 24 20 x 22 691212 CHEROKEE E SECTION SPECIFICATIONS cont DIMENSIONS Wing Span ft 30 Wing Area sq ft 160 Wing Loading lbs per sq ft 15 0 Length ft 23 5 Height fO 7 3 Power Loading lbs per hp 13 3 LANDING GEAR Wheel Base ft 6 2 Wheel Tread ft 10 Tire Pressure psi Nose 24 Main 24 Tire Size Nose 4 ply rating 6 00 x 6 Main 4 ply rating 6 00 x 6 691015 3 SECTION 4 691015 SECTION Il DESIGN INFORMATION Engine and Propeller Structures Landing Gear Control Systems Fuel System Electrical System Heating and Ventilating System Cabin Features 691015 13 13 CHEROKEE E SECTION SECTION Il DESIGN INFORMATION ENGINE AND PROPELLER The Cherokee E is powered by a Lycoming O 360 A4A four cylinder direct drive horizontally opposed engine rated at 180 HP at 2700 RPM It is furnished with a starter 60 ampere 12 volt alternator shielded ign
19. ON This section contains procedures that are recommended if an emergency condition should occur during ground operation takeoff or in flight These procedures are suggested as the best course of action for coping with the particular condition described but are not a substitute for sound judgement and common sense Since emergencies rarely happen in modern aircraft their occurrence is usually unexpected and the best corrective action may not always be obvious Pilots should familiarize themselves with the procedures given in this section and be prepared to take appropriate action should an emergency arise Most basic emergency procedures such as power off landings are a normal part of pilot training Although these emergencies are discussed herein this information is not intended to replace such training but only to provide a source of reference and review and to provide information on procedures which are not the same for all aircraft It is suggested that the pilots review standard emergency procedures periodically to remain proficient in them ENGINE POWER LOSS DURING TAKEOFF The proper action to be taken if loss of power occurs during takeoff will depend on circumstances 1 If sufficient runway remains for a normal landing land straight ahead 2 If insufficient runway remains maintain a safe airspeed and make only a shallow turn if necessary to avoid obstructions Use of flaps depends on circumstances Normally flaps should b
20. OUT WITH COMPRESSED ON USE OWL REPLACE TER W PUMCTURED Om DAMAGED BUSHMMGI CLEAN EXTERIOR WITH ORT TYPE MBL AMD CLEAN WITH DIY TYPE BEARING ROLLER AMD DO MOT PACK GREASE i WHEEL HOUSING OLEO STRUTS AMD BRAKE RESERVO FILL PER UMET OR CONT AMER OR REFER TO SERVICE DISASSE Y O Rims PORTS WIPE ALL LUBRICATION POINTS CLE AM OF OLD GREASE Om DIRT BEFORE LUBRICAT ASSEMBLE INTERY ALS BETWEEN CHANGES CAM IMCHEASED AUCH AS 120 ENGINES EQUIPPED WITH FULL FLOW TRIDGE TYPE OL FILTERS THE ELEMENT n RE PLACED EACH 50 HOURS OF OPERATION SECTION VI CAWTIONS MOT FLUID WTN A CASTOR GA ester DO MOT UCA TE COCKPIT CONTROLS DO MOT APPLY TO RUBBER PARTS 51 52
21. OWS A certain amount of care is needed to keep the plexiglas windows clean and unmarred The following procedure is recom mended 1 Flush with clean water and dislodge excess dirt mud etc with your hand 2 Wash with mild soap and water or Piper Plastic Cleaner Use a soft cloth or sponge Do not rub 3 Remove oil grease or sealing compounds with a soft cloth and kerosene 4 After 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 jew eler s rouge to rub out the scratch smoothing and then applying wax BATTERY SERVICE Access for service or inspection of the battery is obtained through the removal of the panel at the right rear side of the baggage compartment The stainless steel box has a plastic drain tube which is normally closed off with a clamp and which should be opened occasionally to drain off any accumulation of liquid The battery should be checked for proper fluid level but must not be filled above the baffle plates Use only water no acid A hydrometer check should be performed to determine the percent of charge present in the battery 46 753 806 740118 CHEROKEE SECTION VI If the battery is not up to charge recharge starting at a 4 ampere rate and finishing with a 2 ampere rate Quick charges are not recommended FUEL AND OIL REQUIREMENTS Aviation Grade 91 96 Octane minimum fuel must be used in the engin
22. ROSS WT 6000 5000 E pS 3 4000 E E D 3000 c 2000 1000 0 0 200 400 600 800 1000 1200 1400 LANDING DISTANCE FT 41 753 806 740118 SECTION V CHEROKEE E 00021 0857 9 00021 000 1 1 3 0653 0192 6 000 000 01 0292 c 0000 000 6 029 0992 0 72 22 0006 0008 0092 0292 Le 000 8 000 Z 079 0857 0192 oerz ve 0007 000 9 0293 0953 0672 OLvC 86 0009 0005 0092 Oraz 0Zvc 0688 Lv 000 G 000 0853 0253 0 22 000 000 0953 0093 oerz OSE 87 000 000 0953 0872 0 0883 eg 0002 000 1 0253 0977 06 c 0188 99 0001 15 0066 Ortz OLE 0622 6S 15 UV UV 55914 J9N0d 0 19 04 0 19 4 9 J NOd 9509 due 550 dH dH 921 dH dH 801 PIS M 0 3 081 52195 096 0 904 Dunes 19 42 753 806 740118 SECTION VI GENERAL MAINTENANCE Landing Gear 5 43 Brake Secheee Du eei 45 Tire Inflation ass res BOR l E tae ed ee E 45 Care of Windshield and 4 46 Battery 5 46 Fuel and Oil 47 Fuel System 52 Ester ey pU 47 Air Filte
23. XHAUST GAS TEMPERATURE SAUSE Y PALCO IMDICATOS 16 C AR LIGHTER 25 MAGNETO STARTER SWITCH 34 SWITCH PAMEL 6 ei t0 g co 17 SUCTION GAUSE 26 FUEL SYSTEM CLUSTER 35 CIRCUIT BREAKER PANEL 18 CAT DEFROST 27 CHECK LIST 691212 14 CHEROKEE E SECTION NOTES 691015 15 SECTION Ill OPERATING INSTRUCTIONS Preflight Starting Engine Warm Up and Ground Check Take Off Climb Stalls Cruising Approach and Landing Stopping Engine Engine Power Loss Mooring Weight and Balance Operating Tips 691015 16 17 19 19 20 20 21 22 23 23 24 24 24 CHEROKEE E SECTION Ill SECTION Ill OPERATING INSTRUCTIONS PREFLIGHT 1 Master switch and ignition OFF 2 a Check for external damage and operational interfer ence of control surfaces or hinges b Insure that wings and control surfaces are free of snow ice or frost 3 a Visually check fuel supply and secure caps 691015 16 SECTION CHEROKEE b Drain fuel tank sumps two c Drain fuel system sump left side of aircraft d Check that fuel system vents are open e Check main landing gear shock struts for proper in flation approximately 4 50 inches showing f Check tires for cuts wear and proper inflation 4 a Check windshield for cleanliness b Check propeller and spinner for defects or nicks c Check for obvious fuel or oil leaks d Check
24. are two lights which indicate high or low vacuum A natural separa tion of the flight group and the power group is provided by placing the flight group in the upper instrument panel and the power group in the center and lower instrument panels The cabin interior includes a pilot storm window two sun visors ash trays two map pockets and pockets on the backs of each front seat The front seats are adjustable fore and aft for pilot passenger comfort and ease of entry and exit Arm rests are also provided for the front seats The 24 cubic foot baggage area may be reached from the cabin or through a large 20 x 22 inch outside door 691212 13 15 16 17 18 SIMA 19 20 2122 2324 25 26 27 28 23 x 31 32 3 4 35 6 LIGHT 10 maeaea BEACOH RECEIVER CONTROL 19 CHECK LIST 28 TACHOMETER a SLIDE SLOPE INDICATORS 20 AUTOCOMTROL 111 AUTOPILOT 29 ENGINE PRIMER B ven 492 pana 12 SELECTOR SWITCH 21 ENGINE INSTRUMENT CLUSTER 30 THROTTLE QUADRANT 4 110699147 1 COMMUNICATIONS AND NAVIGATION TRANSCEIVERS 22 Gent COUPLER 31 THROTTLE QUADRANT FRICTION KNOG rene AUZLIVER AMD INDICATOR 23 AUTOPILOT TRANSMITTER SWITCH 32 CARBURETOR MEAT CONTROL artirura 6720 13 CONTROL AMD INDICATOR 24 CONTROL LOCK 33 E
25. be lost by widening your pattern using flaps or slipping or a combination of these Touchdown should normally be made at the lowest possible airspeed with full flaps When committed to landing 1 Ignition Off 2 Master Switch Off 3 Fuel Selector Off 4 Mixture Idle Cut Off 5 Seat belt Tight FIRE 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 Source of fire Check 1 Electrical Fire smoke in cabin a Master Switch Off b Vents Open c Cabin Heat Off d Land as soon as possible 30 753 806 740118 CHEROKEE SECTION IV 2 Engine Fire In Flight Fuel Selector Off Throttle Closed Mixture Idle cut off Heater Off In all cases of fire Defroster Off In all cases of fire If terrain permits land immediately The possibility of an engine fire in flight is extremely remote The procedure given above is general and pilot judgment should be the deciding factor for action in such an emergency 3 Engine Fire During Start a If engine has not started 1 Mixture Idle cut off 2 Throttle Open 3 Turn engine with starter This is an attempt to pull the fire into the engine If engine has already started and is running conti
26. buretor heat causes a reduction in power which may be critical in case of a go around Full throttle op eration with heat on is likely to cause 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 landing surface and conditions of wind and airplane loading 753 806 22 740118 SECTION Ill CHEROKEE E It is generally good practice to contact the ground at minimum possible safe speed consistent with existing conditions Normally the best technique for short and slow landings is to use full flap and enough power to maintain the desired airspeed and approach flight path Reduce the airspeed during out and contact the ground close to stalling speed After ground contact hold the nose wheel off as long as possible As the air plane slows down drop the nose and apply the brakes There will be less chance of skidding the tires if the flaps are retracted before applying the brakes Braking is most effective when back pressure is applied to the control wheel putting most of the airplane weight on the main wheels In high wind conditions particularly in strong crosswinds it may be desirable to approach the ground at higher than normal speeds with partial or no flaps STOPPING ENGINE At the pilot s discretion the flaps should be raised and the electric fuel pump turned off After parking the radios should be turned off and the engine stopped b
27. e Because the use of lower grades can cause serious damage in a very short period of time the engine war ranty is invalidated by such use The oil capacity of the Lycoming O 360 A4A is 8 quarts and the minimum safe quantity is 2 quarts It is recommended that the oil and oil filter be changed every 50 hours or sooner under unfavorable conditions The following grades are recom mended for the specific temperatures Temperatures above 60 F S A E 50 Temperatures between 30 and 90 F S A E 40 Temperatures between 0 and 70 F S A E 30 Temperatures below 10 F S A E 20 FUEL SYSTEM The fuel screen in the strainer will require cleaning every 50 hour inspection The strainer located ahead of the firewall is accessible for cleaning by removal of the lower cowl When the strainer is reassembled after cleaning a small amount of grease applied to the gasket will facilitate assembly 753 806 47 740118 SECTION VI CHEROKEE CARE OF AIR FILTER The carburetor air filter must be cleaned at least once every fifty hours Under extremely adverse conditions of operation it may be necessary to clean the filter daily Extra filters are in expensive and a spare should be kept on hand and used as a rapid replacement The filter manufacturer recommends that the filter be tapped gently to remove dirt particles Do not blow out with compressed air LEVELING AND RIGGING Leveling the Cherokee E for purposes of weighing or riggin
28. e fully extended for touchdown 753 806 27 740118 SECTION IV CHEROKEE E 3 If you have gained sufficient altitude to attempt a restart proceed as follows a MAINTAIN SAFE AIRSPEED b FUEL SELECTOR SWITCH TO ANOTHER TANK CONTAINING FUEL c ELECTRIC FUEL PUMP CHECK ON MIXTURE CHECK RICH e CARBURETOR HEAT ON P NOTE If engine failure was caused by fuel exhaustion power will not be regained after tanks are switched until empty fuel lines are filled which may require up to ten seconds If power is not regained proceed with the POWER OFF LANDING procedure ENGINE POWER LOSS IN FLIGHT 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 low altitude the first step is to prepare for an emergency landing See POWER OFF LANDING Maintain an airspeed of at least 82 MPH IAS and if altitude permits proceed as follows 1 Fuel Selector Switch to another tank containing fuel 2 Electric Fuel Pump On 3 Mixture Rich 4 Carburetor Heat On 5 Engine Gauges Check for an indication of the cause of power loss 6 Primer Check Locked 7 If no fuel pressure is indicated check tank selector position to be sure it is on a tank containing fuel 28 753 806 740118 CHEROKEE E SECTION IV When power is restored 8 Carburetor Heat Off 9 Electric Fuel Pump Off If the above steps d
29. g is accomplished as follows 1 Partially withdraw two machine screws located imme diately below the left front side window These screws are leveling points and the airplane is longitudinally level when a level placed on the heads of these screws indicates level 2 To put the airplane in a longitudinally level position on scales first block the main gear oleos in the fully extended position then deflate the nose wheel tire until the proper attitude is obtained For rigging only the airplane may be placed on jacks for leveling 3 To level the airplane laterally place a level across the baggage compartment floor along the rear bulkhead Rigging Although the fixed flight surfaces on the Cherokee cannot be adjusted for rigging purposes it may be necessary upon occasion to check the position of these surfaces The movable surfaces all have adjustable stops as well as adjust able turnbuckles on the cables or push pull tubes so that their range of travel can be altered The positions and angular travels of the various surfaces are as follows 1 Wings 7 dihedral 2 washout 2 Stabilator Travel 18 up 2 down tolerance 1 48 753 806 740118 SECTION VI Fin should be vertical and in line with center of fuselage Aileron Travel 30 up 15 down tolerance 2 Flap Travel 10 25 40 tolerance 2 Rudder Travel 27 right and left tolerance 2 Stabilator Tab Travel 3 up 12 do
30. ition vacuum pump drive fuel pump and a dry automotive type carburetor air filter The exhaust system is of the cross over type to reduce back pressure and improve performance It is made entirely from stain less steel and is equipped with dual mufflers A heater shroud around the mufflers is provided to supply heat for the cabin and windshield defrosting The Sensenich M76EMMS60 fixed pitch propeller is made from a one piece alloy forging STRUCTURES All structures are of aluminum alloy construction and are designed to ultimate load factors well in excess of normal re quirements All exterior surfaces are primed with etching primer and painted with acrylic enamel The wings are attached to each side of the fuselage by in serting the buttends of the respective main spars into a spar box carry through which is an integral part of the fuselage structure providing in effect a continuous main spar with splices at each side of the fuselage There are also fore and aft attachments at 691015 5 SECTION CHEROKEE the rear spar and at an auxiliary front spar The wing airfoil section is a laminar flow type NACA659 415 with the maximum thickness about 40 aft of the leading edge This permits the main spar carry through structure to be located under the rear seat providing unobstructed cabin floor space ahead of the rear seat LANDING GEAR The three landing gears use a Cleveland 6 00 x 6 wheel the main wheels being pr
31. ne Power Loss In Flight 28 Power Off Landing 29 Aa e n tgp S 30 Loss of Oil Pressure 31 Loss of Fuel Pressure 2 2222 32 High Oil Temperature 32 Alternator Failure 33 Engine 33 OPUS Got eho dee di 34 Open CTS ber eo hos 35 SECTION V Performance 36 Altitude Conversion Chart 36 Takeoff Distance vs Density Altitude 37 Rate of Climb vs Density Altitude 38 Range vs Density Altitude 39 True Airspeed RPM vs Density Altitude 40 Landing Distance vs Density Altitude 41 Power Setting Table 42 753 806 740118 INDEX cont SECTION VI Page General Maintenance 43 Landing Gear Service 45 Brake Service 45 Tire Inflation 45 Care of Windshield and Windows 2 46 Battery Service E ee d 46 Fuel and Oil Requirements 47 Fuel System 2 4 47 Care of Air Filter 2 eu a ae ae d 48 Leveling and Rigging 48 Serial Number Plate
32. nted on the trailing edge of the stabilator to reduce the control system forces This tab is actuated by a control wheel on the floor between the front seats The stabilator provides extra stability and controllability with less size drag and weight than conventional tail surfaces The ailerons are provided with a differential action which tends to reduce adverse yaw in turning maneuvers and which also reduces the amount of coordination required in normal turns A rudder trim adjustment is mounted on the right side of the pedestal below the throttle quadrant and permits directional trim as needed in flight The flaps are manually operated balanced for light operating forces and spring loaded to return to the up position A past center lock incorporated in the actuating linkage holds the flap when it is in the up position so that it may be used as a step on the right side The flap will not support a step load except when in the full up position so it must be completely retracted when used as a step The flaps have three extended positions 10 25 and 40 degrees FUEL SYSTEM Fuel is stored in two twenty five gallon tanks which are secured to the leading edge structure of each wing by screws and nut plates This allows easy removal for service or inspection An auxiliary electric fuel pump is provided in case of failure of the engine driven pump The electric pump should be on for all take offs and landings and when switching tanks The pump
33. nue operating to try pulling the fire into the engine In either case stated a and b if the fire continues longer than a few seconds the fire should be extinguished by the best available external means If external fire extinguishing is to be applied 1 Fuel Selector Off 2 Mixture Idle cut off Engine fires during start are usually the result of over priming The procedure above is designed to draw the excess fuel back into the induction system LOSS OF OIL PRESSURE Loss of oil pressure may be either partial or complete A partial loss of oil pressure usually indicates a malfunction in the oil pressure regulating system and a landing should be made as soon as possible to investigate the cause and prevent engine damage 753 806 740118 31 SECTION IV CHEROKEE E A complete loss of oil pressure indication may signify oil exhaustion or may be the result of a faulty gauge In either case proceed toward the nearest airport and be prepared for a forced landing If the problem is 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 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 o
34. o not restore power prepare for an emergency landing If time permits 1 Ignition Switch L then R then back to BOTH 2 Throttle and Mixture Different settings This may restore power if problem is too rich or too lean a mixture or a partial fuel system restriction 3 Try another fuel tank Water in the fuel could take some time to be used up and allowing the engine to windmill may restore power If power loss is due to water fuel pressure indications will be normal NOTE If engine failure was caused by fuel exhaustion power will not be regained after tanks are switched until empty fuel lines are filled which may require up to ten seconds If power is not restored proceed with POWER OFF LANDING procedures POWER OFF LANDING If loss of power occurs at altitude trim the aircraft for best gliding angle 82 MPH IAS and look for a suitable field If measures taken to restore power are not effective and if time permits check your charts for airports in the immediate vicinity it may be possible to land at one 1f you have sufficient altitude If possible notify the FAA by radio of your difficulty and intentions If another pilot or passenger is aboard let them help 753 806 29 740118 SECTION IV CHEROKEE When you have located a suitable field establish a spiral pattern around this field Try to be at 1000 feet above the field at the downwind position to make a normal approach Excess altitude may
35. oil level insure dipstick is properly seated e Check cowling and inspection covers for security f Check nose wheel tire for inflation and wear g Check nose gear shock strut for proper inflation approximately 3 25 inches showing h Check for foreign matter in air inlet 5 a Stow tow bar and control locks if used b Check baggage for storage and security c Close and secure the baggage compartment door 6 a Uponentering airplane remove and stow control column lock pin in side pocket Check that all primary flight controls operate properly b Close and secure cabin door c Check that required papers are in order and in the airplane d Fasten safety belts STARTING ENGINE 1 Set parking brake ON 2 Set the carburetor heat control in the full COLD position 3 Select the desired tank with fuel selector valve Starting Engine When Cold 1 Open throttle approximately 1 4 inch 2 Turn the master switch ON 3 Turn the electric fuel pump ON 4 Move the mixture control to FULL RICH 17 753 806 740118 CHEROKEE SECTION 5 Engage the starter by rotating magneto switch clockwise and pressing in 6 When the engine fires advance throttle to desired setting If the engine does not fire within five to ten seconds disengage starter and prime with one to three strokes of the priming pump Repeat the starting procedure Starting Engine When Hot 1 Open the throttle approximately 1 2 inch 2 Turn the master
36. on the right side controls and dims the panel lights aroa X AUTO Tu Hy tant y our Pur FELO W Por BANK ANONG mav COM BEACON 0 080 0 0 08 00 Circuit Breaker Panel 753 806 740118 SECTION CHEROKEE E Standard accessories include a starter electric fuel pump stall warning indicator cigar lighter fuel gauge and ammeter The navigation lights anti collision light landing light instrument lighting and cabin dome light are optional Circuits will handle an entire complement of communications and navigational equip ment The alternator system offers many advantages over the gen erator system both in operation and maintenance The main ad vantage is full electrical power output at lower engine RPM This is a great improvement for radio and electrical equipment operation Since the alternator output is available at all times the battery will be charging for a greater percentage of use This will make cold morning starting easier The words master switch used hereafter in this manual indicate both sides of the switch battery side BAT and alter nator side ALT are to be depressed simultaneously to Off or On as directed Unlike previous generator systems the ammeter does not indicate battery discharge rather it displays in amperes the load placed on the alternator With all electrical equipment off except master switch the ammeter will be indicating the
37. ovided with Cleveland single disc hydraulic brake assemblies No 30 55 All wheels use 6 00 x 6 four ply tires with tubes The nose gear is steerable through a 44 degree arc by use of the rudder pedals A spring device is incorporated in the rudder pedal torque tube assembly to aid in rudder centering and to provide rudder trim The nose gear steering mechanism also in corporates a hydraulic shimmy dampener The three struts are of the air oil type with the normal extension being 3 25 inches for the nose gear and 4 50 inches for the main gear The standard brake system for the Cherokee consists of a hand lever and master cylinder which is located below and behind the left center of the instrument sub panel The brake fluid reservoir is installed on the top left front face of the firewall The parking brake is incorporated in the master cylinder and is actuated by pulling back on the brake lever depressing the knob attached to the handle and releasing the brake lever To release the parking brake pull back on the lever to disengage the catch mechanism and allow the handle to swing forward Optional toe brakes are available to supplement the standard hand lever and parking brake system 6 691015 SECTION Il CONTROL SYSTEMS Dual controls are provided as standard equipment with a cable system used between the controls and the surfaces The horizontal tail is of the Flying Tail type stabilator with a trim tab mou
38. r oil smoke are apparent and an airport is not close If engine stoppage occurs proceed to POWER OFF LANDING LOSS OF FUEL PRESSURE 1 Electric Boost Pump On 2 Fuel Selector Check on Full Tank If problem is not an empty fuel tank land as soon as practical and have engine driven fuel pump checked HIGH OIL TEMPERATURE An abnormally high oil temperature indication may be caused by a low oil level an obstruction of the oil cooler damaged or improper baffle seals 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 problem Watch the oil pressure gauge for an accompanying loss of pressure 32 753 806 740118 CHEROKEE SECTION IV ALTERNATOR FAILURE Loss of alternator output is detected through a zero reading on the ammeter Before executing the following procedure insure 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 alternator failure can be assumed 1 Reduce Electrical Load 2 Alternator Circuit Breakers Check 3 Alt Switch Off for 1 second Then On If the ammeter continues to indicate no output or alternator will not stay reset turn off Alt switch maintain minimum electrical load and land a
39. s soon as practical All electrical load is being supplied by the battery ENGINE ROUGHNESS Engine roughness is usually due to carburetor icing which is indicated by a drop in RPM and may be accompanied by a slight loss of airspeed or altitude If too much ice is allowed to accumulate restoration of full power may not be possible therefore prompt action is required Carburetor Heat On See Note RPM will decrease slightly and roughness will increase Wait for a decrease in engine roughness or an increase in RPM indicating ice removal If no change in approximately one minute return carburetor heat to COLD If the engine is still rough try steps below 1 Mixture Adjust for maximum smoothness Engine will run rough if too rich or too lean 2 Electric Fuel Purrp On 3 Fuel Selector Change tanks to see if fuel contamination is the problem 4 Engine Gauges Check for abnormal readings If any gauge readings are abnormal proceed accordingly 753 806 33 740118 SECTION IV CHEROKEE 5 Magneto Switch L then R then back to BOTH If operation is satisfactory on either magneto proceed on that magneto at reduced power with mixture full rich to a landing at the first available airport If roughness persists prepare for a precautionary landing at pilot s discretion NOTE Partial carburetor heat may be worse than no heat at all since it may partially melt the ice which will refreeze in the intake sys
40. tem When using carburetor heat therefore always use full heat and when ice is removed return the control to the full cold position SPINS Intentional spins are prohibited in this aircraft If a spin is inadvertently entered immediately use the following recovery procedures 1 THROTTLE IDLE 2 RUDDER FULL OPPOSITE TO DIRECTION OF ROTATION 3 CONTROL WHEEL FULL FORWARD 4 RUDDER NEUTRAL WHEN ROTATION STOPS 5 CONTROL WHEEL AS REQUIRED TO SMOOTHLY REGAIN LEVEL FLIGHT ATTITUDE 34 753 806 740118 CHEROKEE E SECTION IV OPEN DOOR The cabin door on the Cherokee is double latched so the chance of its springing open in flight at both the top and bottom is remote However should you forget the upper latch or not fully engage the lower latch the door may spring partially open This will usually happen at takeoff or soon afterward A partially open door will not affect normal flight characteristics and a normal landing can be made with the door open If both upper and lower latches open the door will trail slightly open and airspeed will be reduced slightly To close a door in flight proceed as follows 1 Slow aircraft to 100 MPH IAS 2 Cabin Vents Close 3 Storm Window Open 4 If upper latch is open latch If lower latch is open open top latch push door further open and then close rapidly Latch top latch A slip in the direction of the open door will assist in latching procedure 753 806 35
41. ts will be correspondingly less 691015 20 SECTION Ill CHEROKEE STALL SPEED TABLE Angle of Bank Flaps 40 Flaps Retracted 0 57 MPH 67 MPH 20 59 MPH 69 MPH 40 65 MPH 77 MPH 60 81 MPH 95 MPH Power Off Gross Weight 2400 Ibs CRUISING The cruising speed is determined by many factors including power setting altitude temperature loading and equipment in stalled on the airplane The normal cruising power is 75 of the rated horsepower of the engine True airspeeds which may be obtained at various altitudes and power settings can be determined from the charts in Section of this handbook Use of the mixture control in cruising flight reduces fuel consumption significantly especially at higher altitudes The mixture should be leaned during cruising operation above 5000 feet altitude and at pilot s discretion at lower altitudes when 75 power or less is being used If any doubt exists as to the amount of power being used the mixture should be in the FULL RICH position for all operations under 5000 feet To lean the mixture pull the mixture control until the engine becomes rough indicating that the lean mixture limit has been reached in the leaner cylinders Then enrich the mixture by pushing the control towards the instrument panel until engine operation becomes smooth The fuel flow meter will give a close approximation of the fuel being consumed If the airplane is eq
42. uipped with the optional exhaust gas 21 691015 CHEROKEE SECTION Ill temperature EGT gauge a more accurate means of leaning is available to the pilot For best power mixture lean the mixture until the peak EGT is reached then enrich the mixture until the temperature drops a minimum of 25 F For best economy mixture lean until the peak EGT is reached and continue to lean until the temperature drops a minimum of 25 F Do not lean above 75 power In order to keep the airplane in best lateral trim during cruising flight the fuel should be used alternately from each tank It is recommended that one tank be used for one hour after take off then the other tank be used for two hours then return to the first tank which will have approximately one and one half hours of fuel remaining if the tanks were full at take off The second tank will contain approximately one half hour of fuel Do not run tanks completely dry in flight APPROACH AND LANDING Before landing check list 1 Fuel on proper tank 2 Electric fuel pump ON 3 Mixture set 4 Flaps set 115 MPH MAX 5 Seat belts fastened The airplane should be trimmed to an approach speed of about 85 MPH with flaps up The flaps can be lowered at speeds up to 115 if desired and the approach speed reduced 3 MPH for each additional notch of flaps Carburetor heat should not be applied unless there is an indication of carburetor icing since the use of car
43. wn tolerance 1 Bae mt Cable tensions for the various controls are as follows Rudder 40 5 lbs Stabilator 40 5 Ibs Ailerons 40 5 Ibs Stabilator Trim 10 1 Ib Flaps Approx 10 Ibs For extreme cases of wing heaviness the flap on the wing heavy side may be adjusted down from the zero position as desired The service manual should be consulted for the proper method of adjusting surface travels SERIAL NUMBER PLATE The serial number plate is located near the stabilator on the left side of the airplane Refer to this number for service or warranty matters 753 806 49 740118 SECTION VI CHEROKEE E NOTES 50 753 806 740118 CHEROKEE E EXAMPLE ICA TIO LETTER G 2427 LUBRICATION CHART PA 28 130 753 806 740118 TYPE OF LUBRICANTS SPECIFICATION LUBRICANT LUBRICATING GEMERAL PURPOSE 0 TEMPERATURE LUBRICATING OIL AIRCRAFT RECIPRO CATING ENGINE PISTOM GRADE SPECIFIED SAE 50 ABOVE b F AW TEMP SAE 40 36 TO M F TEMP 9 1 Am TEMP SAE 20 BELOW IOP am TEMP MTD amp AULK FLUID PETROLEUM BASE CREASE AIRCRAFT INSTRUMENT GEAR ACTUATOR SCREW GREASE AIRCRAFT waco TEMPERATURE DUPONT ALL PURPOSE SLIP SPRAY OR EQUIVALENT PARKER Ru 1 SPECIAL INSTEWCTIONS AIR FILTER TO CLE AM FILTER TAP GENTLY TO REMOVE DIRT PARTICLES DO MOT BLOW
44. y pulling the mixture control to idle cut off The throttle should be left full aft to avoid engine vibration while stopping Then the magneto and master switches should be turned off and the parking brake set ENGINE POWER LOSS The most common cause of engine power loss is mismanage ment of the fuel Therefore the first step to take after engine power loss is to move the fuel selector valve to the tank not being used This will often keep the engine running even if there is no apparent reason for the engine to stop on the tank being used 23 691015 CHEROKEE SECTION Ill If changing to another tank does not restore the engine 1 Check fuel pressure and turn on electric fuel pump if off 2 Push mixture control to full RICH 3 Check ignition switch Turn to best operating magneto left right or both MOORING The Cherokee should be moved on the ground with the aid of the nose wheel tow bar provided with each plane and secured in the baggage compartment Tie down ropes may be secured to rings provided under each wing and to the tail skid The aileron and stabilator controls should be secured by utilization of the control column lock pin in the left hand wheel control column The rudder is held in position by its connections to the nose wheel steering and normally does not have to be secured The flaps are locked when in the full up position and should be left retracted WEIGHT AND BALANCE It is the responsibility
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