Pilot's Operating Handbook

6-2 Blank 6-3 thru 6-13 6-14 Blank 6-15 thru 6-17 *6-18 6-19 thru 6-23 6-24 Blank 7-1 thru 7-18 *7-19 7-20 thru 7-46 8-1 8-2 Blank 8-3 thru 8-13 8-14 8-15 thru 8-17 8-18 Blank Date 1 July 1979 1 July 1979 1 July 1979 1 July 1979 1 July 1979 1 December 1983 1 July 1979 1 July 1979 1 July 1979 1 December 1983 1 July 1979 1. July 1979 15 July 1983 1 July 1979 1 July 1979 1 July 1979 1 July 1979 15 July 1983 1 July 1979 1 July 1979 1 July 1979 1 July 1979 1 July 1979 9-1 thru 9-2 1 July 1979 4-12 Blank 1 July 1979 4-13 thru 4-24 1 July 1979 NOTE 5-1 1 July 1979 5-2 Blank 1 July 1979 5-3 thru 5-27 1 July 1979 5-28 Blank 1 July 1979 Refer to Section 9 Table of Contents for supple- ments applicable to optional systems. 1 July 1979 Revision 2 1 December 1983/D1174-2-13PH iii TABLE OF CONTENTS CESSNA MODEL 172RG iv TABLE OF CONTENTS GENERAL.. LIMITATIONS.. EMERGENCY PROCEDURES... NORMAL PROCEDURES... PERFORMANCE. SECTION • • • • • • • 1 2 3 4 5 WEIGHT & BALANCE/ EQUIPMENT LIST AIRPLANE & SYSTEMS DESCRIPTIONS • 6 7 • ... AIRPLANE HANDLING, SERVICE & MAINTENANCE SUPPLEMENTS (Optional Systems Description & Operating Procedures) 8 9 1 July 1979 CESSNA MODEL 172RG SECTION 1 GENERAL TABLE OF CONTENTS Three View Introduction Descriptive Data Engine Propeller Fuel Oil Maximum Certificated Weights Standard Airplane Weights Cabin And Entry Dimensions Baggage Space And Entry Dimensions Symbols, Abbreviations And Terminology Specific Loadings General Airspeed Terminology And Symbols Meteorological Terminology Engine Power Terminology Airplane Performance And Flight Planning Terminology Weight And Balance Terminology SECTION 1 GENERAL Page 1-2 1-3 1-3 1-3 1-3 1-3 1-4 1-4 1-5 1-5 1-5 1-5 1-6 1-6 1-7 1-7 1-7 1-8 1 July 1979 1-1 SECTION 1 GENERAL 1-2 * PIVOT POINT MAX. 76 1/2”. 0 -27'-5" CESSNA MODEL 172RG 8'-9 1/2" MAX. NOTES: 11'-3". 1. Dimensions shown are based on standard empty weight and proper nose gear and tire inflation. 2. Wing span shown with strobe lights installed. 3. Maximum height shown with nose gear depressed, as far as possible and flashing beacon installed. 4. Wheel base length is 64". 5. Propeller ground clearance is 10". 6: Wing area is 174 square feet. 7. Minimum turning radius (* pivot point 0 36'-0": to outboard wing tip) is 27'-0". * PIVOT POINT '8'-6' Figure 1-1. Three View 1 July 1979 CESSNA MODEL 172RG 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: Avco Lycoming. Engine Model Number: O-360-F1A6. Engine Type: Normally-aspirated, direct-drive, air-cooled, horizontally- opposed, carburetor equipped, four-cylinder engine with 361 cu. in. displacement. Horsepower Rating and Engine Speed: 180 rated BHP at 2700 RPM. PROPELLER Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: B2D34C220/80VHA-3.5 Number of Blades: 2. Propeller Diameter, Maximum: 76.5 inches. Minimum: 75.5 inches. Propeller Type: Constant speed and hydraulically actuated, with a low pitch setting of 12.0° and a high pitch setting of 26.5° (30 inch station). FUEL Approved Fuel Grades (and Colors): 100LL Grade Aviation Fuel (Blue). 100 (Formerly 100/130) Grade Aviation Fuel (Green). NOTE Isopropyl alcohol or ethylene glycol monomethyl ether may be added to the fuel supply. Additive concentrations shall not exceed 1% for isopropyl alcohol or .15% for ethylene glycol monomethyl ether. Refer to Section 8 for additional information. 1 July 1979 1-3 SECTION 1 GENERAL Total Capacity: 66 gallons. Total Capacity Each Tank: 33 gallons. Total Usable: 62 gallons. CESSNA MODEL 172RG NOTE To ensure maximum fuel capacity when refueling and minimize cross-feeding when parked on a sloping surface, place the fuel selector valve in either LEFT or RIGHT position. 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. 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: MIL-L-6082 Aviation Grade Straight Mineral Oil: All temperatures use SAE 20W-50 or Above 16°C (60°F) use SAE 50 -1°C (30°F) to 32°C (90°F) use SAE 40 -18°C (0°F) to 21°C (70°F) use SAE 30 Below -12°C (10°F) use SAE 20 MIL-L-22851 Ashless Dispersant Oil: All temperatures use SAE 20W-50 or Above 16°C (60°F) use SAE 40 or SAE 50 -1°C (30°F) to 32°C (90°F) use SAE 40 -18°C (0°F) to 21°C (70°F) use SAE 40 or SAE 30 Below -12°C (10°F) use SAE 30 Oil Capacity: Sump: 8 Quarts. Total: 9 Quarts. MAXIMUM CERTIFICATED WEIGHTS Ramp: 2658 lbs. Takeoff: 2650 lbs. 1-4 1 July 1979 CESSNA MODEL 172RG SECTION 1 GENERAL Landing: 2650 lbs. Weight in Baggage Compartment: Baggage Area 1 - Station 82 to 108: 200 lbs. See note below. Baggage Area 2 - Station 108 to 124: 50 lbs. See note below. NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 200 lbs. STANDARD AIRPLANE WEIGHTS Standard Empty Weight, Cutlass RG: 1558 lbs. Cutlass RG II: 1598 lbs. Cutlass RG II: 1060 lbs. Maximum Useful Load, Cutlass RG: 1100 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 illustrated in detail in Section 6. SPECIFIC LOADINGS Wing Loading: 15.2 lbs./sq. ft. Power Loading: 14.7 lbs./hp. 1 July 1979 1-5 SECTION 1 GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY CESSNA MODEL 172RG GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS KIAS KTAS A V FE VLE VLO VNO VNE VS 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. 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. 1-6 1 July 1979 CESSNA MODEL 172RG SECTION 1 GENERAL Vx VX 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 or degrees Fah- renheit. Standard Temperature is 15°C at sea level pressure alti- tude and decreases by 2°C for each 1000 feet of altitude. Pressure Altitude Pressure Altitude is the altitude read from 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. 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 Demon- strated Crosswind Velocity Usable Fuel Unusable Fuel GPH 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. Gallons Per Hour is the amount of fuel (in gallons) consumed per hour. 1 July 1979 1-7 SECTION 1 GENERAL CESSNA MODEL 172RG NMPG 80 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.) C.G. Arm C.G. Limits Standard Empty Weight Basic Empty Weight Useful Load 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. 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. 1-8 1 July 1979 CESSNA MODEL 172RG SECTION 1 GENERAL Maximum Ramp Weight Maximum Takeoff Weight Maximum Landing Weight Tare Maximum Ramp Weight is the maximum weight approved for ground maneuver. (It includes the weight of start, taxi and runup fuel.) 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 read- ings. Tare is deducted from the scale reading to obtain the actual (net) airplane weight. 1 July 1979 1-9/(1-10 blank)