172M POH - WINGS Flight School

Fuel Capacity: Standard Tanks: Total Capacity: 42 gallons. Total Capacity Each Tank: 21 gallons. Total Usable: 38 gallons. Long Range Tanks: Total Capacity: 52 gallons. Total Capacity Each Tank: 26 gallons. Total Usable: 48 gallons. NOTE CESSNA MODEL 172M OIL To ensure maximum fuel capacity when refueling, place the fuel selector valve in either LEFT or RIGHT posi- tion to prevent cross-feeding. Oil Grade (Specification); MIL-L-6082 Aviation Grade Straight Mineral Oil: Use to replenish supply during first 25 hours and at the first 25-hour oil change. 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: SAE 50 above 16°C (60°F). SAE 10W30 or SAE 30 between -18°C (0°F) and 21°C (70°F). SAE 10W30 or SAE 20 below -12°C(10°F). NOTE Multi-viscosity oil with a range of SAE 10W30 is recom- mended for improved starting in cold weather. Oil Capacity: Sump: & Quarts. Total: 9 Quarts. 1-4 CESSNA MODEL 172M SECTION 1 GENERAL MAXIMUM CERTIFICATED WEIGHTS 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: 1387 lbs. Skyhawk II: 1412 lbs. Maximum Useful Load: Normal Category Utility Category Skyhawk: Skyhawk II: 913 lbs. 613 lbs. 888 lbs. 588 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 illus- trated in detail in Section 6. SPECIFIC LOADINGS Wing Loading: 13.2 lbs./sq. ft. Power Loading: 15.3 lbs./hp. 1-5 SECTION 1 GENERAL CESSNA MODEL 172M SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS KIAS KTAS V A VFE VNO V. NE V6 √50 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 at- mosphere 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 rel- ative to undisturbed air which is KCAS corrected for altitude and temperature. Maneuvering Speed is the maximum speed at which you may use abrupt control travel. Maximum Flap Extended Speed is the highest speed permis- sible 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 ex- ceeded 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 configuration 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 Outside Air Temperature is the free air static temperature. It is expressed in either degrees Celsius (formerly Centi- grade) or degrees Fahrenheit. 1-6 CESSNA MODEL 172M SECTION 1 GENERAL Standard Tempera- ture Pressure Altitude Standard Temperature is 15°C at sea level pressure altitude and decreases by 2°C for each 1000 feet of altitude. Pressure Altitude is the altitude read from an altimeter when the barometric subscale 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 en- gine runup when the airplane is on the ground and stationary. AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon- strated Crosswind Velocity Demonstrated Crosswind Velocity is the velocity of the cross- wind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests. The value shown in not considered to be limiting. Usable Fuel Usable Fuel is the fuel available for flight planning. Unusable Fuel GPH NMPG g 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 spe- cific engine power setting and/or flight configuration. g is acceleration due to gravity, WEIGHT AND BALANCE TERMINOLOGY Reference Datum Station 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. 107 SECTION 1 GENERAL CESSNA MODEL 172M Arm Moment Center of Gravity (C. G.) C. G. Arm C. G. Limits Standard Empty Weight 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 reducing the number of digits.) Center of Gravity is the point at which an airplane, or equip- ment, 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 airplane, including unusable fuel, full operating fluids and full engine oil. Basic Empty Basic Empty Weight is the standard empty weight plus the Weight weight of optional equipment. Useful Useful Load is the difference between takeoff weight and the basic empty weight. Load Gross Gross (Loaded) Weight is the loaded weight of the airplane. (Loaded) Weight Maximum Takeoff Maximum Takeoff Weight is the maximum weight approved for the start of the takeoff run. Weight Maximum Landing Weight Tare 1-8 Maximum Landing Weight is the maximum weight approved 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. CESSNA MODEL 172M 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 Placards 4 = ་ ° 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 2-10 2-1/(2-2 blank) CESSNA MODEL 172M INTRODUCTION SECTION 2 LIMITATIONS Section 2 includes operating limitations, instrument markings, and basic placards necessary for the safe operation of the airplane, its engine, standard systems and standard equipment. The limitations included in this section have been approved by the Federal Aviation Administration. When applicable, limitations associated with optional systems or equip- ment are included in Section 9. NOTE The airspeeds listed in the Airspeed Limitations chart (figure 2-1) and the Airspeed Indicator Markings chart (figure 2-2) are based on Airspeed Calibration data shown in Section 5 with the normal static source. If the alter- nate static source is being used, ample margins should be observed to allow for the airspeed calibration varia- tions between the normal and alternate static sources as shown in Section 5. Your Cessna is certificated under FAA Type Certificate No. 3A12 as Cessna Model No. 172M. 2-3 SECTION 2 LIMITATIONS AIRSPEED LIMITATIONS CESSNA MODEL 172M Airspeed limitations and their operational significance are shown in figure 2-1. SPEED KCAS KIAS REMARKS VNE Never Exceed Speed 158 160 Do not exceed this speed in any operation. VNO Maximum Structural 126 128 Cruising Speed Do not exceed this speed except in smooth air, and then only with caution. VA Maneuvering Speed: 2300 Pounds 96 97 1950 Pounds ୫୫ 1600 Pounds 80 80 Do not make full or abrupt control movements above this speed. VFE Maximum Flap Extended 86 85 Do not exceed this speed Speed with flaps down. Maximum Window Open Speed 158 160 Do not exceed this speed with windows open. 2-4 Figure 2-1. Airspeed Limitations