Performance Data for Cessna 172M Skyhawk

SAE 30 below -12°C (10°F). Oil Capacity: Sump: 6 Quarts. Total: 7 Quarts (if oil filter installed). 1-4 1 July 1978 V CESSNA MODEL 172N MAXIMUM CERTIFICATED WEIGHTS Ramp, Normal Category: 2307 lbs. SECTION 1 GENERAL Utility Category: 2007 lbs. Takeoff, Normal Category: 2300 lbs. Utility Category: 2000 lbs. Landing, Normal Category: 2300 lbs. Utility Category: 2000 lbs. Weight in Baggage Compartment, Normal Category: Baggage Area 1 (or passenger on child's seat) - Station 82 to 108: 120 lbs. See note below. Baggage Area 2 - Station 108 to 142: 50 lbs. See note below. NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 120 lbs. Weight in Baggage Compartment, Utility Category: In this category, the baggage compartment and rear seat must not be occupied. STANDARD AIRPLANE WEIGHTS Standard Empty Weight, Skyhawk: 1397 lbs. Skyhawk II: 1424 lbs. Maximum Useful Load: Normal Category Utility Category Skyhawk: 910 lbs. 610 lbs. Skyhawk II: 883 lbs. 583 lbs. CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6. BAGGAGE SPACE AND ENTRY DIMENSIONS Dimensions of the baggage area and baggage door opening are illustrated in detail in Section 6. SPECIFIC LOADINGS Wing Loading: 13.2 lbs./sq. ft. Power Loading: 14.4 lbs./hp. 1 July 1978 1-5 SECTION 1 GENERAL CESSNA MODEL 172N SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS KIAS KTAS VA VFE VNO VNE √So vx Vy 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. 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 1-6 Outside Air Temperature is the free air static temperature. 1 July 1978 CESSNA MODEL 172N Standard Tempera- ture Pressure Altitude SECTION 1 GENERAL 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). ENGINE POWER TERMINOLOGY BHP RPM Static RPM 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 g 1 July 1978 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. 1-7 SECTION 1 GENERAL WEIGHT AND BALANCE TERMINOLOGY Reference Datum Station Arm Moment 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 CESSNA MODEL 172N 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 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. 1-8 1 July 1978 CESSNA MODEL 172N Maximum Landing Weight Tare SECTION 1 GENERAL 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 July 1978 1-9/(1-10 blank) CESSNA MODEL 172N SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS TABLE OF CONTENTS Introduction. Airspeed Limitations Airspeed Indicator Markings Power Plant Limitations Power Plant Instrument Markings Weight Limits. Normal Category Utility Category Center Of Gravity Limits Normal Category Utility Category Maneuver Limits Normal Category Utility Category Flight Load Factor Limits Normal Category Utility Category Kinds Of Operation Limits Fuel Limitations . . Other Limitations Flap Limitations Placards Page 2-3 2-4 2-5 2-5 2-6 2-6 2-6 2-7 2-7 2-7 2-7 2-7 2-7 2-7 2-8 2-8 2-8 2-9 2-9 " 2-9 2-9 2-10 1 July 1978 2-1/(2-2 blank)