PILOT'S OPERATING HANDBOOK - Cessna. - flight examiners

stalled, the wing and stabilizer de-ice system. If an autopilot was instal- led and operating. it too could be affected and should be turned off. The dual pump system provides additional reliability for the gyro-operated flight instruments and certain functions of the autopilot. Also, with this installation, the wing and stabilizer de-ice boots are operated by the right vacuum pump, and only in the event of a failure of the right pump would the de-ice boots be inoperative. A placard is required near the suction gage if a wing and stabilizer de-ice system is installed and reads, "DUAL VACUUM SYSTEM INSTALLED. IF RIGHT PUMP FAILS, DE-ICE BOOTS WILL NOT OPERATE." MAKOG U WAC RELIEF VALVE Components included in the dual vacuum pump installation are dual vacuum pumps on the rear of the engine, two vacuum relief valves, a system air filter, and a check valve manifold. A replacement suction gage is provided in the in- stallation kit and incorporates two red warning buttons, marked L and R, which extend visibly in the event either or both vacuum sources fail. During the preflight inspection (be- fore engine start), the suction gage warning buttons should be ex- tended; before takeoff, a check should be made to verify that the suction gage reads in the green arc range and the warning buttons are retracted. A periodic check of the suction gage during cruise flight will alert the pilot of any impend- ing vacuum system failure. COGE ப BE Pr LINFURTER Lat ابوسهلة -37 **** The THE SYSTEM VENT LINE INSTA VIN PLIFIC YALLIFU FL35 CESSNA MODEL 210M TABLE OF CONTENTS TABLE OF CONTENTS GENERAL.... LIMITATIONS…….. . . EMERGENCY PROCEDURES. NORMAL PROCEDURES. PERFORMANCE... WEIGHT & BALANCE/ SECTION 1 2 3 4 5 EQUIPMENT LIST ... AIRPLANE & SYSTEMS DESCRIPTIONS .... AIRPLANE HANDLING, SERVICE & MAINTENANCE ...... SUPPLEMENTS (Optional Systems Description & Operating Procedures) 6 7 8 .9 iii/(iv blank) CESSNA MODEL 210M SECTION 1 GENERAL TABLE OF CONTENTS SECTION 1 GENERAL Page Three View Introduction Descriptive Data Engine Propeller Fuel Oil Maximum Certificated Weights Standard Airplane Weights Cabin And Entry Dimensions Baggage Space And Entry Dimensions 1-2 1-3 1-3 1-3 1-3 1-3 1-4 1-4 1-4 1-5 1-5 Specific Loadings. 1-5 Symbols, Abbreviations And Terminology 1-5 General Airspeed Terminology And Symbols 1-5 Meteorological Terminology 1-6 Engine Power Terminology 1-6 Airplane Performance And Flight Planning Terminology 1-7 Weight And Balance Terminology 1-7 1-1 SECTION 1 GENERAL 1-2 28-2" 13 t 4°7' CESSNA MODEL 210M 9'-5" MAX. NOTES: 1. 2. 3. Maximum height shown with nose gear depressed, all tires and nose strul properly in- Ituted and flashing beacon anstalled Wheel base length is 72" Propeller ground clearance is 10 7/8". 4. Wing area is 175 square feet. 5. Minimum turning radius *pivol paint to outboard wing lip is 26'. PIVOT POINT * * PIVOT POINT 80 MAX. 8-8' Figure 1-1. Three View CESSNA MODEL 210M SECTION 1 GENERAL INTRODUCTION This handbook contains 9 sections, and includes the material required to be furnished to the pilot by CAR Part 3. It also contains supplemental 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. displace. ment. 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: D3A34C404/80VA-0. 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 11.0° and a high pitch setting of 27.0° (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 corro- sion 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: 2168 lbs. Centurion II: 2238 lbs. Centurion II: 1574 lbs. Maximum Useful Load, Centurion: 1644 lbs. 1-4 CESSNA MODEL 210M SECTION 1 GENERAL 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: 21.7 lbs./sq. ft. Power Loading: 12.7 lbs./hp. SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS KIAS KTAS A VFE V. LE VLO 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 Landing Gear Extended Speed is the maximum speed at which an airplane can be safely flown with the landing gear extended. Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safely extended or retracted. 1-5 SECTION 1 GENERAL CESSNA MODEL 210M VNO VNE VS Vx Vy 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 (formerly Centi- grade) or degrees Fahrenheit, 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 froin an altimeter when the altimeter's barometric scale has been set to 29.92 inches of mercury (1013 mb). ENGINE POWER TERMINOLOGY BHP RPM MP 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). 1-6 CESSNA MODEL 210M SECTION 1 GENERAL AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon- strated Crosswind Velocity Usable Fuel Unusable Fuel PPH NMPG br 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. Pounds Per Hour is the amount of fuel (in pounds) con- sumed 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 Center of Gravity (C.G.) 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. 1-7 SECTION 1 GENERAL CESSNA MODEL 210M C.G. Arm C.G. Limits Standard Empty Weight Basic Empty Weight Useful Load Maximum 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.) Gross (Loaded) Weight is the loaded weight of the airplane. Ramp Weight Gross (Loaded) Weight Maximum Takeoff Weight Maximum Landing Weight Tare 1-8 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. CESSNA MODEL 210M SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS TABLE OF CONTENTS Introduction Airspeed Limitations Airspeed Indicator Markings Power Plant Limitations Power Plant Instrument Markings Weight Limits Center Of Gravity Limits Flight Load Factor Limits Maneuver Limits Kinds Of Operation Limits Fuel Limitations Placards Page 2-3 2-4 2-4 2-5 2-6 2-6 2-6 2-7 2-7 2-7 2-7 2-8 2-1/(2-2 blank)