Cessna 152 Pilot's Operating Handbook

Continue to use until a total of 50 hours has accumulated or oil consumption has stabilized. NOTE The airplane was delivered from the factory with a corro- sion preventive aircraft engine oil. This oil should be drained after the first 25 hours of operation. MIL-L-22851 Ashless Dispersant Oil: This oil must be used after first 50 hours or oil consumption has stabilized. Recommended Viscosity for Temperature Range: MIL-L-6082 Aviation Grade Straight Mineral Oil: SAE 50 above 16°C (60°F). SAE 40 between -1°C (30°F) and 32°C (90°F). SAE 30 between -18°C (0°F) and 21°C (70°F). SAE 20 below -12°C (10°F). MIL-L-22851 Ashless Dispersant Oil: SAE 40 or SAE 50 above 16°C (60°F). SAE 40 between -1°C (30°F) and 32°C (90°F). SAE 30 or SAE 40 between -18°C (0°F) and 21°C (70°F). SAE 30 below -12°C (10°F). Oil Capacity: Sump: 6 Quarts. Total: 7 Quarts (if oil filter installed). 1-4 1 July 1978 Revision 1 31 March 1983 CESSNA MODEL 152 SECTION 1 GENERAL MAXIMUM CERTIFICATED WEIGHTS Ramp: 1675 lbs. Takeoff: 1670 lbs. Landing: 1870 lbs. Weight in Baggage Compartment: Baggage Area 1 (or passenger on child's seat) - Station 50 to 76: 120 lbs. See note below. Baggage Area 2 - Station 76 to 94: 40 lbs. See note below. NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 120 lbs. STANDARD AIRPLANE WEIGHTS Standard Empty Weight, 152: 1101 lbs. 152 II: 1133 lbs. Maximum Useful Load, 152: 574 lbs. 152 II: 542 lbs. CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6. BAGGAGE SPACE DIMENSIONS Baggage area dimensions are illustrated in detail in Section 6. SPECIFIC LOADINGS Wing Loading: 10.5 lbs./sq. ft. Power Loading: 15.2 lbs./hp. SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS Knots Calibrated Airspeed is indicated airspeed corrected for position and instrument error and expressed in knots. Knots calibrated airspeed is equal to KTAS in standard atmosphere at sea level. 1 July 1978 1-5 SECTION 1 GENERAL CESSNA MODEL 152 KIAS KTAS A FE VNO VNE 4G Go vx Vy Knots Indicated Airspeed is the speed shown on the airspeed indicator and expressed in knots. Knots True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature. Manuevering Speed is the maximum speed at which you may use abrupt control travel. Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air, then only with caution. Never Exceed Speed is the speed limit that may not be exceeded at any time. Stalling Speed or the minimum steady flight speed at which the airplane is controllable. Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configu- ration at the most forward center of gravity. Best Angle-of-Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance. Best Rate-of-Climb Speed is the speed which results in the greatest gain in altitude in a given time. METEOROLOGICAL TERMINOLOGY OAT Standard Tempera- ture Pressure Altitude Outside Air Temperature is the free air static temperature. It is expressed in either degrees Celsius or degrees Fah- renheit. Standard Temperature is 15°C at sea level pressure alti- tude and decreases by 2°C for each 1000 feet of altitude. Pressure Altitude is the altitude read from an altimeter when the altimeter's barometric scale has been set to 29.92 inches of mercury (1013 mb). 1-6 1 July 1978 CESSNA MODEL 152 ENGINE POWER TERMINOLOGY BHP RPM Static RPM SECTION 1 GENERAL Brake Horsepower is the power developed by the engine. Revolutions Per Minute is engine speed. Static RPM is engine speed attained during a full-throttle engine runup when the airplane is on the ground and stationary. AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon- strated Crosswind Velocity Usable Fuel Unusable Fuel GPH NMPG 20 g Demonstrated Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demon- strated during certification tests. The value shown is not considered to be limiting. Usable Fuel is the fuel available for flight planning. Unusable Fuel is the quantity of fuel that can not be safely used in flight. Gallons Per Hour is the amount of fuel (in gallons) consumed per hour. Nautical Miles Per Gallon is the distance (in nautical miles) which can be expected per gallon of fuel consumed at a specific engine power setting and/or flight configura- tion. g is acceleration due to gravity. WEIGHT AND BALANCE TERMINOLOGY Reference Datum Station Arm Moment 1. July 1978 Reference Datum is an imaginary vertical plane from which all horizontal distances are measured for balance purposes. Station is a location along the airplane fuselage given in terms of the distance from the reference datum. Arm is the horizontal distance from the reference datum to the center of gravity (C.G.) of an item. Moment is the product of the weight of an item multiplied 1-7 SECTION 1 GENERAL CESSNA MODEL 152 Center of Gravity (C.G.) C.G. Arm C.G. Limits Standard Empty Weight Basic Empty Weight Useful Load Maximum Ramp Weight Maximum Takeoff Weight Maximum Landing Weight Tare by its arm. (Moment divided by the constant 1000 is used in this handbook to simplify balance calculations by reduc- ing the number of digits.) Center of Gravity is the point at which an airplane, or equipment, would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. Center of Gravity Arm is the arm obtained by adding the airplane's individual moments and dividing the sum by the total weight. Center of Gravity Limits are the extreme center of gravity locations within which the airplane must be operated at a given weight. Standard Empty Weight is the weight of a standard air- plane, including unusable fuel, full operating fluids and full engine oil. Basic Empty Weight is the standard empty weight plus the weight of optional equipment. Useful Load is the difference between ramp weight and the basic empty weight. Maximum Ramp Weight is the maximum weight approved for ground maneuver. (It includes the weight of start, taxi and runup fuel.) Maximum Takeoff Weight is the maximum weight ap- proved for the start of the takeoff run. Maximum Landing Weight is the maximum weight ap- proved for the landing touchdown. Tare is the weight of chocks, blocks, stands, etc. used when weighing an airplane, and is included in the scale read- ings. Tare is deducted from the scale reading to obtain the actual (net) airplane weight. 1-8 1 July 1978 CESSNA MODEL 152 SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS THIS DATA APPLICABLE ONLY TO AIRPLANES WITH LYCOMING 0-235-12C ENGINE. FOR AIRPLANES WITH ENGINE MODIFIED TO O-235-N2C, REFER TO DATA IN SECTION 9 SUPPLEMENT. TABLE OF CONTENTS Introduction Airspeed Limitations Airspeed Indicator Markings Power Plant Limitations Power Plant Instrument Markings Weight Limits Center Of Gravity Limits Maneuver Limits Flight Load Factor Limits Kinds Of Operation Limits Fuel Limitations Other Limitations Flap Limitations Placards Page 2-3 2-3 2-4 2-4 2-5 2-5 2.5 2-6 2-6 2-6 2-7 2-7 2-7 2-8 1 July 1978 Revision 1 - 31 March 1983 2-1/(2-2 blank)