Pilot's Operating Handbook for Cessna T-207 Turbo Stationair 7

AIRPLANE & SYSTEMS DESCRIPTIONS. AIRPLANE HANDLING, SERVICE & MAINTENANCE. SUPPLEMENTS (Optional Systems Description & Operating Procedures) 5 6 7 • . 8 9 iii/(iv blank) CESSNA MODEL 207 SECTION 1 GENERAL TABLE OF CONTENTS SECTION 1 GENERAL Page Three View Introduction Descriptive Data Engine 1-2 1-3 1-3 1-3 Propeller 1-3 Fuel 1-3 Oil 1-4 Maximum Certificated Weights. 1-4 Standard Airplane Weights. 1-5 Cabin and Entry Dimensions. 1-5 Baggage Space and Cargo Door Entry Dimensions 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 Weight and Balance Terminology . 1-7 1-7 1-1 SECTION 1 GENERAL 1-2 9'-6" MAX. * PIVOT POINT 31'-9". 4°30' T 13" ·36' 10' CESSNA MODEL 207 NOTES: 1. Dimensions shown reflect standard nose and main gear tire installation. 2. Wing span shown with strobe lights installed. 3. Maximum height shown with nose gear depressed and all tires and nose strut properly inflated. 4. Wheel base length is 83 1/4". 5. Propeller ground clearance is 10". 6. Wing area is 174 square feet. 7. Minimum turning radius (*pivot point to outboard * PIVOT POINT ·6'-10" Figure 1-1. Three View wing tip) is 27' 3". CESSNA MODEL 207 SECTION 1 GENERAL INTRODUCTION This handbook contains 9 sections, and includes the material re- quired to be furnished to the pilot by FAR Part 23. It also contains sup- plemental 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-F. 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: D2A 34C58/90AT-8. Number of Blades: 2. Propeller Diameter, Maximum: 82 inches. Minimum: 80 inches. Propeller Type: Constant speed and hydraulically actuated, with a low pitch setting of 9.5° and a high pitch setting of 25.8° (36 inch station). FUEL Fuel Grade (and Color): 100/130 Minimum Grade Aviation Fuel (green). 100/130 low lead aviation fuel (blue) with a lead content limited to 2 cc per gallon is also approved. Fuel Capacity: Standard Tanks: Total Capacity: 61 gallons. Total Capacity Each Tank: 30.5 gallons. Total Usable: 54 gallons. 1-3 SECTION 1 GENERAL Long Range Tanks: Total Capacity: 80 gallons. Total Capacity Each Tank: 40 gallons. Total Usable: 73 gallons. CESSNA MODEL 207 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: 12 Quarts. Total: 13 Quarts (if oil filter installed). MAXIMUM CERTIFICATED WEIGHTS Takeoff: 3800 lbs. Landing: 3800 lbs. Weight in Baggage Compartments: Forward, Station -14 to 0: 120 lbs. Aft, Station 142 to 168: 180 lbs. NOTE Refer to Section 6 of this handbook for loading arrange- ments with one or more seats removed for cargo accom- modation. 1-4 CESSNA MODEL 207 STANDARD AIRPLANE WEIGHTS Standard Empty Weight (1 Seat): 1964 lbs. Maximum Useful Load (1 Seat): 1836 lbs. 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 CARGO DOOR ENTRY DIMENSIONS Dimensions of the baggage/cargo areas and forward baggage door and cargo door openings are illustrated in detail in Section 6. SPECIFIC LOADINGS Wing Loading: 21.8 lbs./sq. ft. Power Loading: 12.7 lbs./hp. SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS KIAS KTAS VA 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 undistrubed air which is KCAS corrected for altitude and temperature. Maneuvering Speed is the maximum speed at which you may use abrupt control travel. 1-5 SECTION 1 GENERAL CESSNA MODEL 207 VFE VNO VNE Vs VSo VX VY 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 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 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 Standard Tempera- ture 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 altitude and decreases by 2°C for each 1000 feet of altitude. Pressure 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 ВНР RPM MP Brake Horsepower is the power developed by the engine. Percent power values in this handbook are based on the max- imum 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 207 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 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 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 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. 1-7 SECTION 1 GENERAL CESSNA MODEL 207 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 Takeoff Weight is the maximum weight approved for the start of the takeoff run. Maximum Landing Weight Tare 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 207 SECTION 2 LIMITATIONS TABLE OF CONTENTS SECTION 2 LIMITATIONS 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 2-7 Maneuver Limits. 2-7 Flight Load Factor Limits 2-7 Kinds of Operation Limits Fuel Limitations Placards 2-7 2-8 2-8 2-1/(2-2 blank)