Cessna_210_C210M_Centurion...

when the altimeter's barometric scale has been set to 29.92 inches of mercury (1013 mb). ENGINE POWER TERMINOLOGY BHP RPM MP 1-6 Brake Horsepower is the power developed by the engine. Percent power values in this handbook are based on the maximum continuous power rating. Revolutions Per Minute is engine speed. Manifold Pressure is a pressure measured in the engine's induction system and is expressed in inches of mercury (Hg). CESSNA MODEL 210M INTRODUCTION SECTION 1 GENERAL This handbook contains 9 sections, and includes the material re- quired to be furnished to the pilot by CAR Part 3. It also contains supple- mental data supplied by Cessna Aircraft Company. Section 1 provides basic data and information of general interest. It also contains definitions or explanations of symbols, abbreviations, and terminology commonly used. DESCRIPTIVE DATA ENGINE Number of Engines: 1. Engine Manufacturer: Teledyne Continental. Engine Model Number: IO-520-L. Engine Type: Normally-aspirated, direct-drive, air-cooled, horizontally- opposed, fuel-injected, six-cylinder engine with 520 cu. in. displacement. Horsepower Rating and Engine Speed: Maximum Power (5 minutes - takeoff): 300 rated BHP at 2850 RPM. Maximum Continuous Power: 285 rated BHP at 2700 RPM. PROPELLER Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: D3A32C88/82NC-2. Number of Blades: 3. Propeller Diameter, Maximum: 80 inches. Minimum: 78.5 inches. Propeller Type: Constant speed and hydraulically actuated, with a low pitch setting of 11. 5° and a high pitch setting of 28.1° (30 inch station). FUEL Approved Fuel Grades (and Colors): 100LL Grade Aviation Fuel (Blue). 100 (Formerly 100/130) Grade Aviation Fuel (Green). Total Capacity: 90 gallons. Total Capacity Each Tank: 45 gallons. Total Usable: 89 gallons. 1-3 SECTION 1 GENERAL CESSNA MODEL 210M OIL 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 cor- rosion preventive aircraft engine oil. This oil should be drained after the first 25 hours of operation. Continental Motors Specification MHS-24A, 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 4°C (40°F). SAE 10W30 or SAE 30 below 4°C (40°F). NOTE Multi-viscosity oil with a range of SAE 10W30 is recom- mended for improved starting in cold weather. Oil Capacity: Sump: 10 Quarts. Total: 11 Quarts (if oil filter installed). MAXIMUM CERTIFICATED WEIGHTS Takeoff: 3800 lbs. Landing: 3800 lbs. Weight in Baggage Compartment: Baggage Forward of wheel well on folded down aft seat (Station 89 - to 110): 120 lbs. Baggage On and aft of wheel well (Station 110 to 152): 120 lbs. STANDARD AIRPLANE WEIGHTS Standard Empty Weight, Centurion: 2175 lbs. Centurion II: 2248 lbs. 1625 lbs. Centurion II: 1552 lbs. Maximum Useful Load, Centurion: 1-4 CESSNA MODEL 210M SECTION 1 GENERAL 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 is not considered to be limiting. Usable Fuel Usable Fuel is the fuel available for flight planning. Unusable Fuel РРН NMPG g Unusable Fuel is the quantity of fuel that can not be safely used in flight. Pounds Per Hour is the amount of fuel (in pounds) consumed per hour. Nautical Miles Per Gallon is the distance (in nautical milės) 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 Arm Moment Center of Gravity (C. G.) C. G. Arm 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 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 ref- erence 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. 1-7 SECTION 1 GENERAL CESSNA MODEL 210M C. G. Limits Standard Empty Weight Basic Empty Weight Useful Load Gross (Loaded) Weight Maximum Takeoff 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 Weight is the standard empty weight plus the weight of optional equipment. Useful Load is the difference between takeoff weight and the basic empty weight. Gross (Loaded) Weight is the loaded weight of the airplane. Maximum Landing Weight Tare Maximum Takeoff Weight is the maximum weight approved for the start of the takeoff run. 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 readings. Tare is deducted from the scale reading to obtain the actual (net) airplane weight. 1-8 CESSNA MODEL 210M SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS TABLE OF CONTENTS Page Introduction 2-3 Airspeed Limitations 2-4 Airspeed Indicator Markings 2-4 Power Plant Limitations 2-5 Power Plant Instrument Markings 2-6 Weight Limits . 2-6 Center of Gravity Limits 2-6 Maneuver Limits. 2-7 Flight Load Factor Limits Kinds of Operation Limits. Fuel Limitations Placards 2-7 2-7 2-7 · . 2-8 2-1/(2-2 blank) CESSNA MODEL 210M 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. 3A21 as Cessna Model No. 210M. 2-3 SECTION 2 LIMITATIONS AIRSPEED LIMITATIONS CESSNA MODEL 210M Airspeed limitations and their operational significance are shown in figure 2-1. SPEED KCAS KIAS REMARKS VNE Never Exceed Speed 195 199 Do not exceed this speed in any operation. VNO Maximum Structural 165 168 Cruising Speed Do not exceed this speed except in smooth air, and then only with caution. VA Maneuvering Speed: 1720*3800 Pounds 117 119 143 3150 Pounds 107 109 136, 2500 Pounds 95 96 Do not make full or abrupt control movements above this speed. VFE Maximum Flap Extended Speed: To 10° Flaps 138 140 10° - 30° Flaps 105 105 Do not exceed these speeds with the given flap settings. VLO Maximum Landing Gear 138 140 Do not extend or retract Operating Speed landing gear above this speed. VLE Maximum Landing Gear 138 140 Do not exceed this speed Extended Speed with landing gear extended. Maximum Window Open 195 199 Speed Do not exceed this speed with windows open. Figure 2-1. Airspeed Limitations AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their color code significance are shown in figure 2-2. 2-4 CESSNA MODEL 210M SECTION 2 LIMITATIONS KIAS VALUE MARKING OR RANGE White Arc Green Arc 55-105 68 - 168 Yellow Arc 168 - 199 Red Line 199 SIGNIFICANCE Full Flap Operating Range, Lower limit is maximum weight VS。 in landing configuration. Upper limit is maximum speed permissible with flaps extended. Normal Operating Range. Lower limit is maximum weight Vs at most forward C.G. with flaps retracted. Upper limit is maximum structural cruising speed. Operations must be conducted with caution and only in smooth air. Maximum speed for all operations. Figure 2-2. Airspeed Indicator Markings POWER PLANT LIMITATIONS Engine Manufacturer: Teledyne Continental. Engine Model Number: 10-520-L. Engine Operating Limits for Takeoff and Continuous Operations: Maximum Power, 5 Minutes - Takeoff: 300 BHP. Continuous: 285 BHP. Maximum Engine Speed, 5 Minutes - Takeoff: 2850 RPM. Continuous: 2700 RPM. Maximum Cylinder Head Temperature: 238°C (460°F). Maximum Oil Temperature: 116°C (240°F). Oil Pressure, Minimum: 10 psi. Maximum: 100 psi. Fuel Pressure, Minimum: 3.5 psi. Maximum: 19.5 psi (151 lbs/hr). Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: D3A32C88/82NC-2. Propeller Diameter, Maximum: 80 inches. Minimum: 78.5 inches. Propeller Blade Angle at 30 Inch Station, Low: 11.5° High: 28.1° 2-5