Cessna 1976 Cardinal RG Pilot's Operating Handbook

Specific Loadings 1-5 Symbols, Abbreviations and Terminology 1-5 General Airspeed Terminology and Symbols 1-5 Meteorological Terminology. 1-6 Engine Power Terminology 1-7 Airplane Performance and Flight Planning Terminology 1-7 Weight and Balance Terminology 1-7 1-1 SECTION 1 GENERAL 1-2 * PIVOT POINT 78" MAX. .8 27'-3" 3°27' CESSNA MODEL 177RG 8'-7" MAX. 11'-10" NOTES: 1. Wing span shown with strobe lights installed. 2. Maximum height shown with nose gear depressed and all tires and nose strut properly inflated. 3. Wheel base length is 90". 4. Propeller ground clearance is 8 1/8". 5. Wing area is 174 square feet. 6. Minimum turning radius (*pivot point to outboard wing tip) is 30'-9". 35'-6" 7'-10" Figure 1-1. Three View * PIVOT POINT CESSNA MODEL 177RG 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: Avco Lycoming. Engine Model Number: IO-360-A1B6D. Engine Type: Normally-aspirated, direct-drive, air-cooled, horizontally- opposed, fuel-injected, four-cylinder engine with 361 cu. in. displace- ment. Horsepower Rating and Engine Speed: 200 rated BHP at 2700 RPM. PROPELLER Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: B2D34C207/78TCA-0. Number of Blades: 2. Propeller Diameter, Maximum: 78 inches. Minimum: 76.5 inches. Propeller Type: Constant speed and hydraulically actuated, with a low pitch setting of 12.9° and a high pitch setting of 27.5° (30 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. Total Capacity: 61 gallons. Total Capacity Each Tank: 30.5 gallons. Total Usable: 60 gallons. NOTE To ensure desired fuel capacity when refueling, place 1-3 SECTION 1 GENERAL OIL CESSNA MODEL 177RG 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: 8 Quarts. Total: 9 Quarts. MAXIMUM CERTIFICATED WEIGHTS Takeoff: 2800 lbs. Landing: 2800 lbs. Weight in Baggage Compartment: Baggage Area "A" (on and forward of wheel well)-Station 145 to 172: See note below. Baggage Area "B" (aft of wheel well) and Hatshelf-Station 172 to 195: See note below. 1-4 NOTE The maximum baggage load, including the hatshelf, is 120 lbs. This load may be distributed as desired be- tween baggage areas, provided 12 lbs. is not exceeded on the hatshelf. CESSNA MODEL 177RG STANDARD AIRPLANE WEIGHTS Standard Empty Weight, Cardinal RG: 1707 lbs. Cardinal RG II: Maximum Useful Load, Cardinal RG: 1768 lbs. 1093 lbs. Cardinal RG II: 1032 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 ENTRY DIMENSIONS Dimensions of the baggage area and baggage door opening are illus- trated in detail in Section 6. SPECIFIC LOADINGS Wing Loading: 16.1 lbs./sq. ft. Power Loading: 14.0 lbs./hp. SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS KIAS KTAS 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. 1-5 SECTION 1 GENERAL CESSNA MODEL 177RG VA VFE VLE VLO V NO V. NE Vs √ 60 VX VY 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 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. 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 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 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). 1-6 CESSNA MODEL 177RG SECTION 1 GENERAL ENGINE POWER TERMINOLOGY BHP RPM MP Brake Horsepower is the power developed by the engine. 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). AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demo- 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 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.) 1-7 SECTION 1 GENERAL CESSNA MODEL 177RG Center of Gravity (C. G.) C. G. Arm C.G. Limits Standard Empty Weight Basic Empty Weight Useful Load Gross (Loaded) Weight Maximum Takeoff 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 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. Weight 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. -8 CESSNA MODEL 177RG SECTION 2 LIMITATIONS TABLE OF CONTENTS SECTION 2 LIMITATIONS Page Introduction Airspeed Limitations 2-3 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 . 2-7 Fuel Limitations . Placards 2-8 2-8 2-1/(2-2 blank)