Pilot's Operating Handbook

Cowling on the Cherokee is designed to cool the engine in all normal flight conditions, including protracted climb, with- out the use of cowl flaps or cooling flanges. The throttle is of the push-pull type and is located in the lower center of the instrument panel. A knurled friction lock is provided to prevent creeping of 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 like the throttle. The full rich position is obtained when the control is full forward, while the full aft position provides an idle cut-off *58 inch pitch propellers when gross weight is 2150. **When gross weight is 2150 770527 5 SECTION II THE PIPER CHEROKEE. THE PIPER CHEROKEE SECTION II 1 for stopping the engine. Intermediate positions are used for leaning the mixture at altitudes above sea-level. The carbu- retor heat control, located to the left of the throttle, provides maximum carburetor heat when pulled to its full aft position. With carburetor heat off, all engine air passes through a high- efficiency dry-type filter. Therefore, prolonged ground oper- ation with carburetor heat "ON" should be avoided, particularly on unimproved fields as the air is not filtered. 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 butt ends of the respective main spars into a spar box carry through which is an integral part of the fuselage struc- ture, providing, in effect, a continuous main spar with splices at each side of the fuselage. There are also fore and aft at- tachments at the rear spar and at an auxiliary front spar. The wing airfoil section is a laminar flow type, NACA 652-415 with the maximum thickness about 40% aft of the lead- ing 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 600 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 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 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 master cylin- der, which is located below and behind the left center of the in- strument sub-panel. The brake fluid reservoir is installed on the top left front face of the firewall. The parking brake is in- corporated in the master cylinder and is actuated by pulling back on the brake lever, depressing the knob attached to the left side of the handle and then releasing the brake lever. To release the parking brake, pull back on the brake lever to disengage the catch mechanism and 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 which also acts as a longitudinal trim tab, actuated by a control on the cabin ceiling. 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 eliminate adverse yaw in turning maneuvers and also reduces the amount of coordination 6 671031 671031 7 1 I SECTION II THE PIPER CHEROKEE THE PIPER CHEROKEE SECTION II required in normal turns. The flaps are manually operated, balanced for light oper- ating 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 ex- cept when in the full up position, so it must be completely re- tracted when used as a step. The flaps have three extended po- sitions, 10, 25 and 40 degrees. the tank selector valve must be switched to each tank in turn, with the electric pump on, and the gascolator drain valve open- ed. Each tank has an individual quick drain located at the bot- tom, inboard, rear corner. Fuel quantity and pressure are indicated on gauges located in the engine gauge cluster on the right side of the instrument panel. FUEL SYSTEM ELECTRICAL SYSTEM 1 1 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 in- spection. The standard quantity of fuel is 36 gallons for the Cherokee 140. To obtain the standard quantity of fuel, fill the tanks to the bottom of the filler neck indicator. 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. The fuel strainer, which is equipped with a quick drain, is located on the front lower left corner of the firewall. This strainer should be drain- ed regularly to check for water or sediment accumulation. To drain the lines from the tanks, The Cherokee is equipped with the Piper F.T.P. (Full Time Power) Electrical System. Its 12 volt alternator provides elec- trical power at all engine speeds and results in improved per- formance for radio and electrical equipment and longer battery life. In addition to the alternator, the electrical system includes a 25 ampere-hour battery, 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 acces- sories, in addition to those al- ready listed, include a starter, stall warning indicator, cigar lighter and ammeter. Navi- gation lights, anti-collision light, landing light, instrument lighting and a cabin dome light are offered as optional acces- 000000000 8 650630 650630 9 SECTION II THE PIPER CHEROKEE THE PIPER CHEROKEE SECTION II sories. Circuit provisions are made to handle optional commun- ications and navigational equipment. In conventional generator systems, the ammeter indicates battery discharge. In the Piper Full Time Power electrical sys- tem, the ammeter displays the load in amperes placed on the system at any given time. With all electrical equipment except the master switch in the "OFF" position, the ammeter will in- dicate the amount of charging current demanded by the battery. This amount will vary and depends on the percentage of full charge on the battery at the time. When the battery becomes charged, the current displaced on the ammeter will reduce to a minimum value of about two amperes. As each unit of elec- trical equipment is switched on the amount of current it draws will be shown on the ammeter. The maximum continuous load for night flight with all equipment on is approximately thirty amperes. This thirty amperes plus approximately two amperes for the fully charged battery will appear continuously under these flight conditions. Because of the mechanical simplicity of the alternator, maintenance should prove to be a minor factor as compared to previous systems. Should service be required, contact your local Piper dealer. HEATING AND VENTILATING SYSTEM www. Heat for the cabin interior and the defroster system is pro- vided by a heater muff attached to the exhaust system. Con- trols for these systems are located on the lower right hand side of the instrument panel. A third control in this area regulates a large fresh air vent located on the left hand side of the cabin near the pilot's feet. In addition, two side vents are provided, one at each seat location. They may be independently regulated as desired by the seat occupant. 1. Fresh Air Control 2. Defroster Control 3. Heater Control 10 650630 fresh air cabin heat 4. Defroster Air Outlet 5. Fresh Air Inlet 6. Heater Duct 11 SECTION II THE PIPER CHEROKEE THE PIPER CHEROKEE SECTION II CABIN FEATURES The instrument panel of the Cherokee is designed to ac- commodate the customary advanced flight instruments and all the normally required power plant instruments. The Artificial Horizon, Directional Gyro and the Turn and Bank instruments are vacuum operated through use of a vacuum pump installed on the engine. A natural separation of the flight group and the power group is provided by placing the communications and radio navigational equipment in the center of the panel. The front seats are adjustable fore and aft for pilot com- fort 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, 4-place capability. 1. Compass 2. Airspeed Indicator FAMILY SEATS 3. Directional Gyro Indicator 4. Gyro Horizon Indicator 5. Radio ADF 6. Radio VHF 7. Tachometer 8. Vacuum Gauge 9. Instrument Cluster 10. Turn and Bank Indicator 11. Clock 12. Stall Warning Light 13. Altimeter 14. Rate of Climb Indicator 12 . 650630 650630 8 $ 7 IL ZI 13 12a 1 SECTION III OPERATING INSTRUCTIONS Preflight 13 Starting 14 Warm-up 15 Ground Check 16 Take-off 16 17 Climb Stalls Cruising 18 18 Maneuvers 19 Approach and Landing 19 Mooring Weight and Balance 19a 19a 1 1 661201 THE PIPER CHEROKEE SECTION III OPERATING INSTRUCTIONS SECTION III PREFLIGHT The airplane should be given a thorough visual inspection prior to each flight. Particular attention should be given to the following items in the illustration below: 1. a. Master switch "ON." b. Check fuel quantity indicators (two tanks). c. Master switch and ignition "OFF." 2. a. Check for external damage, operational interference 13 13