Airplane Flight Manual for Piper PA-28 Cherokee 140

when the carburetor heat is OFF. 790330 6 SECTION II CHEROKEE 140 "B" CHEROKEE 140 "B" SECTION II 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 lacquer. The wings are attached to each side of the fuselage by in- serting the butt ends 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 the rear spar and at an auxiliary front spar. The wing airfoil section is a laminar flow type, NACA652-415 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 provided with brake drums and Cleveland single disc hydraulic brake assemblies. The nose wheel and the main gear both use 6.00 x 6 four ply tires. All the tires have tubes. The nose gear is steerable through a .44° 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 incorporates 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 (empty weight of airplane plus full fuel and oil) load. The brakes are actuated by a hand lever and a master cyl- inder which is located below and near the center of the instrument panel. The toe brakes and the hand lever have their own brake cylinders but they both use a common reservoir. The parking brake is incorporated in the lever brake and is operated by pulling back on the lever and depressing the knob attached to the top of the handle. To release the parking brake, pull back on the brake lever to disengage the catch mechanism; then allow the handle to swing forward. CONTROL SYSTEM Dual controls are provided as standard equipment with a cable system used between the controls and the surfaces. The horizontal tail is of the all movable slab type, with an anti-servo tab acting as a longitudinal trim tab. It is actuated by a control on the cabin ceiling. The stabilator provides extra stability and control with less size, drag, and weight than conventional tail surfaces. The differential action of the ailerons tends to elimi- nate adverse yaw in turning maneuvers and reduces the amount of coordination required in normal turns. The flaps are manually operated, balanced for light operating forces and spring loaded to turn 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. 7 08 680915 680915 8 SECTION II CHEROKEE 140 "B" 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 to allow easy removal for service or inspection. The standard quantity of fuel is 36 gallons for the Cher- okee 140 "B". To obtain the standard quantity of fuel, fill the tanks to the bottom of the filler neck indicator. Fuel Strainer An auxiliary electric fuel pump is provided for use 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 fuel strainer is equipped with a quick drain and is located on the front lower left corner of the firewall. This strainer should be drained regularly to check for water or sediment ac- cumulation. To drain the lines from the tanks, the tank selector valve must be switched to each tank in turn, with the electric pump on, and the gascolator drain valve opened. Each tank has an individual quick drain located at the bottom, inboard, rear corner. Fuel quantity and pressure are indicated on gauges located in the engine gauge cluster on the left side of the instrument panel. ELECTRICAL SYSTEM The electrical system includes a 12 volt 60 ampere alter- nator, battery, voltage regulator, overvoltage relay, and master CHEROKEE 140 "B" switch relay. The battery and master switch relay are located beneath the baggage compart- ment floor. Access for service or inspection is obtained by raising the hinged floor panel. The regulator and overvoltage relay are located on the for- ward left side of the fuselage behind the instrument panel. Electrical switches are located on the right center in- strument panel, and the circuit breakers are located on the LOOK ON SECTION II Circuit Breaker Panel lower right instrument panel. A rheostat switch on the right side of the switch panel controls the navigation lights and the intensity of the instrument panel light. Standard electrical accessories include starter, electric fuel pump, stall warning indicator, cigar lighter, and ammeter. Navi- gation lights, anti-collision light, landing light and instrument panel lighting are offered as optional accessories. Circuit provisions are made to handle a complete complement of communications and navigational equipment. The alternator system offers many advantages over the gen- erator system. The main advantage is full electrical power output at much lower engine RPM and results in improved radio and electrical equipment operation. Since the alternator output is available all the time, the battery will be charging almost con- tinuously. This will make cold weather starting easier. In generator systems, the ammeter indicates battery dis- charge. In the Cherokee electrical system the ammeter displays in amperes the load placed on the alternator. With all electrical equipment except the master switch in the OFF position, the ammeter will indicate the amount of charging current demanded by the battery. As each item of electrical 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 680915 680915 10 11 SECTION II flight with radios on is about 30 amperes. This 30 ampere value plus approximately 2 amperes for a fully charged battery will appear continuously under these flight conditions. The master switch is a split switch with the left half oper- ating the master relay and the right half energizing the alternator. The switch is interlocked so that the alternator cannot be oper- ated without the battery. For normal operation, be sure both halves are turned on. If no output is indicated on the ammeter, during flight, reduce the electrical load by turning off all un- necessary electrical equipment. Check both the 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 one second to reset the overvoltage relay. If ammeter continues to indicate no output, turn off the "ALT" switch, maintain minimum 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. Do not take off with a fully discharged battery as 3 volts are needed to excite the alternator. 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. If unusual odors are noticed, the heat should be shut off and the system inspected for leaks. 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 floor panel. CHEROKEE 140 "B" CHEROKEE 140 "B" SECTION II CHEROKEE 140 B Cabin Heat, Defroster, Fresh Air 790330 680915 4. Defroster Air Outlet 6. Cabin Exhaust Outlet 5. Fresh Air Inlet 1. Fresh Air Control 2. Defroster Control 3. Heater Control of bengi 12 <->Fresh Air ▷ Cabin Heat SECTION II CABIN FEATURES CHEROKEE 140 "B" CHEROKEE 140 "B" SECTION II The instrument panel of the Cherokee is designed to ac- comodate the customary advanced flight instruments and all the normally required power plant instruments. The artificial 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. A vacuum gauge is mounted on the far right side of the instrument panel. A natural separation of the flight group and power group is provided by placing the flight group in the upper instrument panel and the power group in the sub-panel center. The radios and circuit breakers located on the right hand instrument panel have extra circuits provided for a complete line of optional radio equipment. The microphone is located the console cover from Serial No. 25801 and up. The front seats are adjustable fore and aft for pilot comfort and ease of entry and exit. A family seat installation is available which provides two additional seats. Each family seat is capable of carrying a full size adult which gives the Cherokee 140 "B", 4-place capability. uo 13 FAMILY SEATS 81 16 17 690220 690220 O WARDO 0000000000000 21 22 23 24 1. STALL WARNING INDICATOR 10. 2. CLOCK 3. TURN INDICATOR 3. AIRSPEED INDICATOR 5. DIRECTIONAL GYRO 6. ATTITUDE GYRO 7. PLACARD PLACARD 25 13. TRANSMITTER SELECTOR SWITCH 12. OMNI AND GLIDE SLOP INDICATORS 11. MARKER BEACON LIGHTS 14. VHF TRANSCEIVERS 15. ADF RECEIVER 16. DME RECEIVER 8. VERTICAL SPEED INDICATOR 17. 9. ALTIMETER 18. CIGAR LIGHTER SUCTION GAUGE 30 31 32 33 28. ENGINE PRIMER 20. AUTOCONTROL 111 AUTOPILOT 19. PHONE JACK 21. OMNI COUPLER 22. PITCH CONTROL 30. THROTT LE QUADRANT FRICTION LOCK 29. THROTTLE QUADRANT 31. CARBURETOR HEAT CONTROL 32. AMMETER 23. MAGNETO SWITCHES & STARTER 32. 24. INSTRUMENT CLUSTER 25. RPM CRUISE CHART 26. CHECK LISTS 27. TACHOMETER 34. CIRCUIT BREAKER PANEL 35. HEAT AND DEFROST CONTROLS 33. SWITCH PANEL 14 CONE BORED SECTION III OPERATING INSTRUCTIONS Preflight. 15 Starting Engine 16 Warm-Up 18 Ground Check 19 Take-Off 19 Climb 21 12 Stalls 21 Cruising 22 Maneuvers 23 Approach and Landing. 23 Stopping Engine. 24 Engine Power Loss. 24 24 Mooring Weight and Balance. Operating Tips 25 25 25 25 25 CHEROKEE 140 "B" PREFLIGHT SECTION III OPERATING INSTRUCTIONS SECTION III The airplane should be given a thorough visual inspection prior to each flight. Particular attention should be given to the following items: 1. a. Master switch ON. b. Check fuel quantity indicators (two tanks). c. Master switch and ignition OFF. 680915 15 SECTION III CHEROKEE 140 "B" CHEROKEE 140 "B" 2. a. Check for external damage, operational interference 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, secure caps. b. Drain fuel tank sumps. 140 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 inflation. 5. a. Inspect windshield for cleanliness. b. Check the propeller and spinner 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 inflation, wear. g. Check nose wheel shock strut for proper inflation. h. Check for foreign matter in air inlets. 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. aircraft. b. Close and secure the cabin door. c. Check that required papers are in order and in the d. inertia reel. Fasten seat belts and shoulder harness. Check function of STARTING ENGINE 16 1. Set the parking brake. 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. SECTION III 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 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. Starting With External Power Source: An optional feature known as Piper External Power (PEP) allows the operator to use an external battery to crank the engine without having to gain access to the aircraft battery. The procedure is as follows: 1. Turn aircraft MASTER SWITCH to OFF. 2. Connect RED lead of PEP kit jumper cable to POSITIVE (+) terminal of external 12 volt battery and BLACK lead to NEGATIVE (-) 17 730116 730116