1981-Cessna-182-RG-POH.pdf - Dayton Pilots' Club

A revision bar will extend the full length of new or revised text and/or illustrations added on new or presently existing pages. This bar will be located adjacent to the applicable revised area on the outer margin of the page. All revised pages will carry the revision number and date on the applicable page. The following Log of Effective Pages provides the dates of issue for original and revised pages, and a listing of all pages in the handbook. Pages affected by the current revision are indicated by an asterisk (*) preceding the pages listed. LOG OF EFFECTIVE PAGES Dates of issue for original and revised pages are: Original Revision 1 Page Title 15 August 1980 24 May 1982 Date Page Date Assignment Record i thru ii 15 August 1980 15 August 1980 15 August 1980 5-12 thru 5-28 6-1 6-2 Blank 15 August 1980 15 August 1980 15 August 1980 *iii 24 May 1982 6-3 thru 6-13 15 August 1980 iv 15 August 1980 6-14 Blank 15 August 1980 1-1 thru 1-9 15 August 1980 6-15 thru 6-31 15 August 1980 1-10 Blank 2-1 15 August 1980 15 August 1980 6-32 Blank 15 August 1980 2-2 Blank 15 August 1980 2-3 thru 2-11 15 August 1980 7-1 thru 7-42 8-1 8-2 Blank 15 August 1980 15 August 1980 15 August 1980 2-12 Blank 15 August 1980 8-3 thru 8-17 15 August 1980 3-1 thru 3-19 15 August 1980 8-18 Blank 15 August 1980 3-20 Blank 15 August 1980 4-1 thru 4-11 15 August 1980 9-1 thru 9-3 9-4 Blank 15 August 1980 15 August 1980 4-12 Blank 15 August 1980 4-13 thru 4-24 15 August 1980 NOTE 5-1 15 August 1980 5-2 Blank 15 August 1980 5-3 thru 5-10 *5-11 15 August 1980 24 May 1982 Refer to Section 9 Table of Contents for supplements applicable to optional sys- tems. 15 August 1980 Revision 1 - 24 May 1982 /D1198-1-13PH iii TABLE OF CONTENTS iv CESSNA MODEL R182 TABLE OF CONTENTS GENERAL. LIMITATIONS...... EMERGENCY PROCEDURES.. NORMAL PROCEDURES. SECTION • 1 2 3 4 5 PERFORMANCE. WEIGHT & BALANCE/ EQUIPMENT LIST AIRPLANE & SYSTEMS DESCRIPTIONS AIRPLANE HANDLING, SERVICE & MAINTENANCE SUPPLEMENTS (Optional Systems Description & Operating Procedures) 6 7 8 9 15 August 1980 CESSNA MODEL R182 SECTION 1 GENERAL TABLE OF CONTENTS Three View Introduction Descriptive Data Engine Propeller (2-Bladed) Propeller (3-Bladed) Fuel Oil Maximum Certificated Weights Standard Airplane Weights Cabin And Entry Dimensions Baggage Space And Entry Dimensions Specific Loadings О Symbols, Abbreviations And Terminology 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 1-3 1-4 1-5 1-5 1-5 1-5 1-5 1-6 1-6 1-7 1-7 1-7 1-8 15 August 1980 1-1 SECTION 1 GENERAL 1-2 -28-7 1/2" -11-8" * PIVOT POINT 00 82" MAX. 0 -36'-0"- CESSNA MODEL R182 8'-11" MAX. NOTES: 1. Dimensions shown are based on standard empty weight and proper nose gear and tire inflation. 2. Wing span shown with strobe lights installed. 9'-0" Figure 1-1. Three View 3. Maximum height shown with nose gear depressed as far as possible and flashing beacon installed 4. Wheel base length is 65", 5. Propeller ground clearance is 11 1/2". 6. Wing area is 174 square feet. 7. Minimum turning radius (* pivot point to outboard wing tip) is 27'-5" * PIVOT POINT 15 August 1980 CESSNA MODEL R182 C O SECTION 1 GENERAL MAXIMUM CERTIFICATED WEIGHTS Ramp: 3112 lbs. Takeoff: 3100 lbs. Landing: 3100 lbs. Weight in Baggage Compartment: Baggage Area "A" (or passenger on child's seat) - Station 82 to 110: 120 lbs. See note below. Baggage Area "B" - Station 110 to 134: 80 lbs. See note below. NOTE The maximum combined weight capacity for baggage areas A and B is 200 lbs. STANDARD AIRPLANE WEIGHTS Standard Empty Weight, Skylane RG: 1752 lbs. Maximum Useful Load, Skylane RG: 1360 lbs. Skylane RG II: 1805 lbs. Skylane RG II: 1307 lbs. О 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: 17.8 lbs./sq. ft. Power Loading: 13.2 lbs./hp. 15 August 1980 1-5 SECTION 1 GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY CESSNA MODEL R182 GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS KIAS KTAS A VFE VLE VLO V NO V. NE VS ༨༠ 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 15 August 1980 CESSNA MODEL R182 SECT ON 1 GENEH. 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-540-J3C5D. Engine Type: Normally-aspirated, direct-drive, air-cooled, horizontally- opposed, carburetor equipped, six-cylinder engine with 541.5 cu. in. displacement. Horsepower Rating and Engine Speed: 235 rated BHP at 2400 RPM. PROPELLER (2-BLADED) Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: B2D34C218/90DHB-8. Number of Blades: 2. Propeller Diameter, Maximum: 82 inches. Minimum: 80.5 inches. Propeller Type: Constant speed and hydraulically actuated, with a low pitch setting of 15.8° and a high pitch setting of 29.4° (30 inch station). PROPELLER (3-BLADED) Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: B3D32C407/82NDA-3. Number of Blades: 3. Propeller Diameter, Maximum: 79 inches. Minimum: 78 inches. Propeller Type: Constant speed and hydraulically actuated, with a low pitch setting of 16.0° and a high pitch setting of 31.7° (30 inch station). FUEL Approved Fuel Grades (and Colors): 100LL Grade Aviation Fuel (Blue). 100 (Formerly 100/130) Grade Aviation Fuel (Green). 15 August 1980 1-3 TV ΣΤΟΙ ON 1 AL CESSNA MODEL R182 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. Total Capacity: 92 gallons. Total Capacity Each Tank: 46 gallons. Total Usable: 88 gallons. OIL 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 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. 1-4 15 August 1980 CESSNA MODEL R182 SECTION 1 GENERAL Vx Vy 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 ОАТ Standard Tempera- ture Pressure Altitude Outside Air Temperature is the free air static temperature. It is expressed in either degrees Celsius 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 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 O 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 15 August 1980 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 consumed per hour. 1-7 SECTION 1 GENERAL CESSNA MODEL R182 NMPG g 80 Nautical Miles Per Gallon is the distance which can be expected per gallon of fuel consumed at a specific 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 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. IN 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 15 August 1980 O CESSNA MODEL R182 SECTION GENERA Maximum Ramp Weight Maximum Takeoff Weight Maximum Landing Weight Tare Maximum Ramp Weight is the maximum weight approv for ground maneuver. (It includes the weight of start, t and runup fuel.) Maximum Takeoff Weight is the maximum wei approved for the start of the takeoff run. Maximum Landing Weight is the maximum wei approved for the landing touchdown. Tare is the weight of chocks, blocks, stands, etc. used wł weighing an airplane, and is included in the scale re ings. Tare is deducted from the scale reading to obtain actual (net) airplane weight. 15 August 1980 1-9/(1-10 bla