Cessna 172N Skyhawk Airplane Flight Manual

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: i thru ii 6-2 Blank 6-3 thru 6-16 30 May 1980 30 May 1980 30 May 1980 Original 30 May 1980 Revision 2 1 October 1994 Revision 1 1 December 1983 Page Date Page Date Title 30 May 1980 6-1 Assignment Record 30 May 1980 30 May 1980 1 October 1994 * 6-17 30 May 1980 30 May 1980 30 May 1980 30 May 1980 30 May 1980 30 May 1980 * iii iv 1-1 thru 1-9 1-10 Blank 2.1 2-2 Blank 2-3 thru 2-4 2-5 thru 2-6 2-7 thru 2-13 2-14 Blank 3-1 thru 3-9 3-10 Blank 1 October 1994 6-18 thru 6-27 6-28 Blank 7-1 thru 7-16 17-17 7-18 thru 7-37 7-38 8-1 1 October 1994 30 May 1980 30 May 1980 30 May 1980 1 October 1994 30 May 1980 30 May 1980 30 May 1980 30 May 1980 8-2 Blank 30 May 1980 30 May 1980 8-3 thru 8-17 30 May 1980 30 May 1980 8-18 Blank 30 May 1980 30 May 1980 9-1 thru 9-3 30 May 1980 3-11 thru 3-18 30 May 1980. 9-4 Blank 30 May 1980 4-1 thru 4-24 30 May 1980 30 May 1980 NOTE 30 May 1980 5-3 thru 5-23 30 May 1980 5-24 Blank 30 May 1980 5-1 5-2 Blank Refer to Section 9 Table of Contents for supplements applcable to optional systems. ii 30 May 1980 30 May 1980 Revision 21 October 1994/D1192-2-13PH iii CESSNA MODEL 172P CESSNA MODEL 172P SECTION 1 GENERAL TABLE OF CONTENTS TABLE OF CONTENTS SECTION 1 iv SECTION 1 GENERAL GENERAL LIMITATIONS 2 " TABLE OF CONTENTS EMERGENCY PROCEDURES 3 .... Page NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT & BALANCE / EQUIPMENT LIST 6 AIRPLANE & SYSTEMS Three View Introduction Descriptive Data Engine Propeller Fuel Oil Maximum Certificated Weights Standard Airplane Weights Cabin And Entry Dimensions Baggage Space And Entry Dimensions Specific Loadings 1-2 1-3 1-3 1-3 1-3 1-3 1-4 1-5 1-5 1-5 1-5 1-5 Symbols, Abbreviations And Terminology 1-6 DESCRIPTIONS 7 General Airspeed Terminology And Symbols 1-6 Meteorological Terminology 1-6 Engine Power Terminology 1-7 AIRPLANE HANDLING, Airplane Performance And Flight Planning Terminology 1-7 Weight And Balance Terminology SERVICE & MAINTENANCE 1-8 . 8 SUPPLEMENTS (Optional Systems Description & Operating Procedures) .. 9 30 May 1980 30 May 1980 1-1 SECTION 1 GENERAL 1-2 NOTES: 1. Wing span shown with strobe lights installed. 2. Maximum height shown with nose gear depressed, all tires and nose strut properly inflated, and flashing beacon installed. 3. Wheel base length is 65". 4. Propeller ground clearance is 11". 5. Wing ares is 174 square feet. 6. Minimum turning radius (✶ pivot point to outboard wing tip) is 27'-5%" -26'-11″ -11'-4" * PIVOT POINT 0 0 75" MAX. -36′-0″. -8'-4 1/2"- Figure 1-1. Three View PIVOT POINT CESSNA MODEL 172P 8'-9 1/2" MAX. CESSNA MODEL 172P 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-320-D2J. Engine Type: Normally-aspirated, direct-drive, air-cooled, horizontally- opposed, carburetor equipped, four-cylinder engine with 319.8 cu. in. displacement. Horsepower Rating and Engine Speed: 160 rated BHP at 2700 RPM. PROPELLER Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: 1C160/DTM7557. Number of Blades: 2. Propeller Diameter, Maximum: 75 inches. Minimum: 74 inches. Propeller Type: Fixed pitch. 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. 30 May 1980 30 May 1980 1-3 27 SECTION 1 GENERAL CESSNA MODEL 172P CESSNA MODEL 172P SECTION 1 GENERAL Fuel Capacity: OIL Standard Tanks: Total Capacity: 43 gallons. Total Capacity Each Tank: 21.5 gallons. Total Usable: 40 gallons. Long Range Tanks: Total Capacity: 54 gallons. Total Capacity Each Tank: 27 gallons. Total Usable: 50 gallons. Integral Tanks: Total Capacity: 68 gallons. Total Capacity Each Tank: 34 gallons. Total Usable: 62 gallons. 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: 1-4 Sump: 7 Quarts. Total: 8 Quarts. 30 May 1980 MAXIMUM CERTIFICATED WEIGHTS Ramp, Normal Category: 2407 lbs. Utility Category: 2107 lbs. Takeoff, Normal Category: 2400 lbs. Utility Category: 2100 lbs. Landing, Normal Category: 2400 lbs. Utility Category: 2100 lbs. Weight in Baggage Compartment, Normal Category: Baggage Area 1 (or passenger on child's seat) - Station 82 to 108; 120 lbs. See note below. Baggage Area 2 - Station 108 to 142: 50 lbs. See note below. NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 120 lbs. Weight in Baggage Compartment, Utility Category: In this category, the baggage compartment and rear seat must not be occupied. STANDARD AIRPLANE WEIGHTS Standard Empty Weight, Skyhawk: 1414 lbs. Skyhawk II: 1440 lbs. Maximum Useful Load: Skyhawk: Skyhawk II: Normal Category 993 lbs. 967 lbs. CABIN AND ENTRY DIMENSIONS Utility Category 693 lbs. 667 lbs. 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: 13.8 lbs./sq. ft. Power Loading: 15.0 lbs./hp. 30 May 1980 1-5 CESSNA CESSNA MODEL 172P MODEL 172P SECTION 1 GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS KIAS 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. SECTION 1 GENERAL Standard Tempera- ture Pressure Altitude 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 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 Brake Horsepower is the power developed by the engine. Revolutions Per Minute is engine speed. Static RPM is engine speed attained during a full-throttle engine runup when the airplane is on the ground and stationary. KTAS Knots True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature. BHP RPM V Α Static RPM VFE VNO VNE VS √so vx Y 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 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. AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon- strated Crosswind Velocity Usable Fuel Unusable Fuel GPH NMPG g 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. 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. METEOROLOGICAL TERMINOLOGY OAT 1-6 Outside Air Temperature is the free air static temperature. 30 May 1980 30 May 1980 1-7 SECTION 1 GENERAL 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 Maximum Ramp Weight Maximum Takeoff CESSNA MODEL 172P 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. 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 ap- proved for the start of the takeoff run. Weight 1-8 CESSNA MODEL 172P Maximum Landing Weight Tare SECTION 1 GENERAL 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. 30 May 1980 30 May 1980 (1-10 blank) CESSNA MODEL 172P SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS TABLE OF CONTENTS 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 Normal Category 2-6 Utility Category 2-7 Center Of Gravity Limits 2-7 Normal Category 2-7 Utility Category 2-7 Maneuver Limits Normal Category Utility Category 2-7 2-7 2-7 Flight Load Factor Limits 2-8 Normal Category Utility Category 2-8 2-8 Kinds Of Operation Limits 2-9 Other Limitations Fuel Limitations Flap Limitations 2-9 2-10 2-10 Placards 2-10 30 May 1980 2-1/(2-2 blank) ) 30 May 1980 CESSNA MODEL 172P SECTION 2 LIMITATIONS INTRODUCTION Section 2 includes operating limitations, instrument markings, and basic placards necessary for the safe operation of the airplane, its engine, standard systems and standard equipment. The limitations included in this section and in Section 9 have been approved by the Federal Aviation Administration. Observance of these operating limitations is required by Federal Aviation Regulations. NOTE Refer to Section 9 of this Pilot's Operating Handbook for amended operating limitations, operating procedures, performance data and other necessary information for airplanes equipped with specific options. NOTE The airspeeds listed in the Airspeed Limitations chart (figure 2-1) and the Airspeed Indicator Markings chart (figure 2-2) are based on Airspeed Calibration data shown in Section 5 with the normal static source. If the alternate static source is being used, ample margins should be observed to allow for the airspeed calibration variations between the normal and alternate static sources as shown in Section 5. Your Cessna is certificated under FAA Type Certificate No. 3A12 as Cessna Model No. 172P. ) 2-3 CESSNA MODEL 172P CESSNA MODEL 172P SECTION 2 LIMITATIONS AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in figure 2-1. Maneuvering speeds shown apply to normal category opera- tions. The utility category maneuvering speed is 102 KIAS at 2100 pounds. then only with caution. MARKING KIAS VALUE OR RANGE White Arc 33 85 Green Arc 44 -127 158 SPEED KCAS KIAS REMARKS VNE Never Exceed Speed 152 158 Do not exceed this speed in any operation. Yellow Arc 127 158 VNO Maximum Structural Cruising Speed 123 127 Do not exceed this speed except in smooth air, and Red Line VA Maneuvering Speed: 2400 Pounds 97 99 2000 Pounds 91 92 1600 Pounds 81 82 VFE Maximum Flap Extended Speed: 10° Flaps 108 110 Do not exceed this speed 10° -30° Flaps 84 85 with flaps down. Maximum Window Open Speed 152 158 Do not exceed this speed with windows open. 38800 Do not make full or abrupt control movements above this speed. Figure 2-1. Airspeed Limitations AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their color code significance are shown in figure 2-2. SIGNIFICANCE SECTION 2 MITATIONS Full Flap Operating Range. Lower limit is maximum weight Vso in landing configuration. Upper limit is maximum speed permissible with flaps extended. Normal Operating Range. Lower limit is maximum weight Vs at most forward C.G. with flaps retracted. Upper limit is maximum structural cruising speed. Operations must be conducted with caution and only in smooth air. Maximum speed for all operations. Figure 2-2. Airspeed Indicator Markings POWERPLANT LIMITATIONS Engine Manufacturer: Avco Lycoming. Engine Model Number: 0-320-D2J. Maximum Power: 160 BHP rating. Engine Operating Limits for Takeoff and Continuous Operations: Maximum Engine Speed: 2700 RPM. NOTE The static RPM range at full throttle (carburetor heat off and mixture leaned to maximum RPM) is 2300 to 2420 RPM. Maximum Oil Temperature: 245°F (118°C). Oil Pressure, Minimum: *25 psi. Maximum: 115 psi. Fuel Grade: See Fuel Limitations. Oil Grade (Specification): MIL-L-6082 Aviation Grade Straight Mineral Oil or MIL-L-22851 Ashless Dispersant Oil. Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: 1C160/DTM7557. Propeller Diameter, Maximum: 75 inches. Minimum: 74 inches. *20 psi on airplanes modified by Service Kit SK172-81, SK172-82 or SK172-123A. 30 May 1980 2-4 30 May 1980 Revision 2-1 October 1994 2-5 SECTION 2 LIMITATIONS CESSNA MODEL 172P POWERPLANT INSTRUMENT MARKINGS Powerplant instrument markings and their color code significance are shown in Figure 2-3. INSTRUMENT RED LINE MINIMUM LIMIT GREEN ARC NORMAL OPERATING RED LINE MAXIMUM LIMIT CESSNA MODEL 172P SECTION 2 LIMITATIONS NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 120 lbs. UTILITY CATEGORY Maximum Ramp Weight: 2107 lbs. Maximum Takeoff Weight: 2100 lbs. Tachometer: Sea Level 5000 Feet 10000 Feet Oil Temperature Oil Pressure 2100 2450 RPM 2100 2575 RPM 2100 2700 RPM 2700 RPM 100° - 245°F 245°F * * 25 psi E 60 - 90 psi 115 psi E Fuel Quantity (Standard Tanks) Fuel Quantity (Long Range Tanks) Fuel Quantity (Integral (1.5 Gal. Unusable Each Tank) (2.0 Gal. Unusable Each Tank) E (3.0 Gal. Unusable Tanks) Suction --- Each Tank) 4.5 - 5.4 in. Hg Figure 2-3. Powerplant Instrument Markings WEIGHT LIMITS NORMAL CATEGORY Maximum Ramp Weight: 2407 lbs. Maximum Takeoff Weight: 2400 lbs. Maximum Landing Weight: 2400 lbs. Maximum Weight in Baggage Compartment: Baggage Area 1 (or passenger on child's seat) - Station 82 to 108: 120 lbs. See following note. Baggage Area 2 - Station 108 to 142: 50 lbs. See following note. 20 psi (red line) and 50-90 psi (green arc) on airplanes modified by Service Kit SK172-81, SK172-82 or SK172-123A. Maximum Landing Weight: 2100 lbs. Maximum Weight in Baggage Compartment: In the utility category, the baggage compartment and rear seat must not be occupied. CENTER OF GRAVITY LIMITS NORMAL CATEGORY Center of Gravity Range: Forward: 35.0 inches aft of datum at 1950 lbs. or less, with straight line variation to 39.5 inches aft of datum at 2400 lbs. Aft: 47.3 inches aft of datum at all weights. Reference Datum: Lower portion of front face of firewall. UTILITY CATEGORY Center of Gravity Range: Forward: 35.0 inches aft of datum at 1950 lbs. or less, with straight line variation to 36.5 inches aft of datum at 2100 lbs. Aft: 40.5 inches aft of datum at all weights. Reference Datum: Lower portion of front face of firewall. MANEUVER LIMITS NORMAL CATEGORY This airplane is certificated in both the normal and utility category. The normal category is applicable to aircraft intended for non-aerobatic operations. These include any maneuvers incidental to normal flying, stalls (except whip stalls), lazy eights, chandelles, and turns in which the angle of bank is not more than 60°. Aerobatic maneuvers, including spins, are not approved. UTILITY CATEGORY This airplane is not designed for purely aerobatic flight. However, in the acquisition of various certificates such as commercial pilot and flight 2-6 30 May 1980 Revision 2-1 October 1994 30 May 1980 2-7 SECTION 2 LIMITATIONS CESSNA MODEL 172P CESSNA MODEL 172P _ECTION 2 LIMITATIONS instructor, certain maneuvers are required by the FAA. All of these maneuvers are permitted in this airplane when operated in the utility category. In the utility category, the baggage compartment and rear seat must not be occupied. No aerobatic maneuvers are approved except those listed below: MANEUVER Chandelles Lazy Eights Steep Turns Spins Stalls (Except Whip Stalls) RECOMMENDED ENTRY SPEED* 105 knots 105 knots 95 knots Slow Deceleration Slow Deceleration *Abrupt use of the controls is prohibited above 99 knots. Aerobatics that may impose high loads should not be attempted. The important thing to bear in mind in flight maneuvers is that the airplane is clean in aerodynamic design and will build up speed quickly with the nose down. Proper speed control is an essential requirement for execution of any maneuver, and care should always be exercised to avoid excessive speed which in turn can impose excessive loads. In the execution of all maneuvers, avoid abrupt use of controls. Intentional spins with flaps extended are prohibited. FLIGHT LOAD FACTOR LIMITS NORMAL CATEGORY Flight Load Factors (Maximum Takeoff Weight - 2400 lbs.): *Flaps Up *Flaps Down +3.8g, -1.52g +3.0g *The design load factors are 150% of the above, and in all cases, the structure meets or exceeds design loads. UTILITY CATEGORY Flight Load Factors (Maximum Takeoff Weight - 2100 lbs.): *Flaps Up *Flaps Down +4.4g, -1.76g +3.0g *The design load factors are 150% of the above, and in all cases, the structure meets or exceeds design loads. KINDS OF OPERATION LIMITS The airplane is equipped for day VFR and may be equipped for night VFR and/or IFR operations. FAR Part 91 establishes the minimum required instrumentation and equipment for these operations. The refer- ence to types of flight operations on the operating limitations placard reflects equipment installed at the time of Airworthiness Certificate issuance. Flight into known icing conditions is prohibited. FUEL LIMITATIONS 2 Standard Tanks: 21.5 U.S. gallons each. Total Fuel: 43 U.S. gallons. Usable Fuel (all flight conditions): 40 U.S. gallons. Unusable Fuel: 3 U.S. gallons. 2 Long Range Tanks: 27 U.S. gallons each. Total Fuel: 54 U.S. gallons. Usable Fuel (all flight conditions): 50 U.S. gallons. Unusable Fuel: 4 U.S. gallons. 2 Integral Tanks: 34 U.S. gallons each. Total Fuel: 68 U.S. gallons. Usable Fuel (all flight conditions): 62 U.S. gallons. Unusable Fuel: 6 U.S. gallons. 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. Takeoff and land with the fuel selector valve handle in the BOTH position. Maximum slip or skid duration with one tank dry: 30 seconds. With 1/4 tank or less, prolonged uncoordinated flight is prohibited when operating on either left or right tank in level flight. Fuel remaining in the tank after the fuel quantity indicator reads empty (red line) cannot be safely used in flight. Approved Fuel Grades (and Colors): 100LL Grade Aviation Fuel (Blue). 100 (Formerly 100/130) Grade Aviation Fuel (Green). 2-8 30 May 1980 30 May 1980 2-9 SECTION 2 LIMITATIONS OTHER LIMITATIONS FLAP LIMITATIONS Approved Takeoff Range: 0° to 10°. Approved Landing Range: 0° to 30°. CESSNA CESSNA MODEL 172P MODEL 172P 2. SECTION 2 LIMITATIONS On the fuel selector valve (standard tanks): BOTH 40 GAL. ALL FLIGHT ATTITUDES. TAKEOFF, LANDING. LEFT 20 GAL. LEVEL FLIGHT ONLY 20 GAL. LEVEL FLIGHT ONLY RIGHT OFF PLACARDS The following information must be displayed in the form of composite or individual placards. 1. In full view of the pilot: (The "DAY-NIGHT-VFR-IFR" entry, shown on the example below, will vary as the airplane is equipped.) The markings and placards installed in this airplane contain operat- ing limitations which must be complied with when operating this airplane in the Normal Category. Other operating limitations which must be complied with when operating this airplane in this category or in the Utility Category are contained in the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. Normal Category - Utility Category - No acrobatic maneuvers, including spins, approved. No acrobatic maneuvers approved. except those listed in the Operating Handbook. Pilot's Baggage compartment and rear seat must not be occupied. 3. On the fuel selector valve (long range tanks): BOTH 50 GAL. ALL FLIGHT ATTITUDES. TAKEOFF, LANDING. LEFT 25 GAL. LEVEL FLIGHT ONLY RIGHT 25 GAL. LEVEL FLIGHT ONLY OFF On the fuel selector valve (integral tanks): BOTH 62 GAL. ALL FLIGHT ATTITUDES. TAKEOFF, LANDING. LEFT 31 GAL. LEVEL FLIGHT ONLY 31 GAL. LEVEL FLIGHT ONLY RIGHT OFF Near fuel tank filler cap (standard tanks): FUEL 100LL/100 MIN. GRADE AVIATION GASOLINE CAP. 21.5 U.S. GAL. Spin Recovery - Opposite rudder-forward elevator - neutralize controls. Flight into known icing conditions prohibited. This airplane is certified for the following flight operations as of date of original airworthiness certificate: 2-10 DAY NIGHT—VFR-IFR Near fuel tank filler cap (long range tanks): FUEL 100LL/100 MIN. GRADE AVIATION GASOLINE CAP. 27 U.S. GAL. 30 May 1980 30 May 1980 2-11 SECTION 2 LIMITATIONS Near fuel tank filler cap (integral tanks): FUEL CESSNA MODEL 172P CESSNA MODEL 172P 100LL/100 MIN. GRADE AVIATION GASOLINE CAP. 34 U.S. GAL. CAP. 24.0 U.S. GAL. TO BOTTOM OF FILLER COLLAR 4. Near wing flap switch: 9. On control lock: SECTION 2 LIMITATIONS CONTROL LOCK - REMOVE BEFORE STARTING ENGINE 10. Near airspeed indicator: MANEUVER SPEED - 99 KIAS 2-12 AVOID SLIPS WITH FLAPS EXTENDED 5. On flap control indicator: 6. 7. 0° to 10° 10° to 30° (Partial flap range with blue color code and 110 kt callout; also, mechanical detent at 10°.) (Indices at these positions with white color code and 85 kt callout; also, mechanical detent at 10° and 20°.) In baggage compartment: 120 POUNDS MAXIMUM BAGGAGE AND/OR AUXILIARY PASSENGER FORWARD OF BAGGAGE DOOR LATCH 50 POUNDS MAXIMUM BAGGAGE AFT OF BAGGAGE DOOR LATCH MAXIMUM 120 POUNDS COMBINED FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA A calibration card is provided to indicate the accuracy of the magnetic compass in 30° increments. 8. On oil filler cap: OIL 7 QTS 30 May 1980 30 May 1980 2-13/(2-14 blank)