Cessna 172 POH - Wayman Flight School

gear depressed, all tires and nose strut properly inflated, and flashing beacon installed. Propeller ground clearance is 11 3/4". 3. Wheel base length is 65". 4. 5. 6. Wing area is 174 square feet. Minimum turning radius (*pivot point to outboard wing tip) is 27' 5½". DESCRIPTIVE DATA ENGINE Number of Engines: 1. Engine Manufacturer: Avco Lycoming. Engine Model Number: O-320-H2AD. Engine Type: Normally-aspirated, direct-drive, air-cooled, horizontally- opposed, carburetor equipped, four-cylinder engine with 320 cu. in. displacement. Horsepower Rating and Engine Speed: 160 rated BHP at 2700 RPM. PIVOT POINT 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. 8'-4½" Figure 1-1. Three View FUEL Approved Fuel Grades (and Colors): 100LL Grade Aviation Fuel (Blue). 100 (Formerly 100/130) Grade Aviation Fuel (Green). 1-3 SECTION 1 GENERAL CESSNA MODEL 172N CESSNA MODEL 172N 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. NOTE To ensure maximum fuel capacity when refueling, place the fuel selector valve in either LEFT or RIGHT position 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 consumption has stabilized. Recommended Viscosity for Temperature Range: MIL-L-6082 Aviation Grade Straight Mineral Oil: SAE 50 above 16°C (60°F). SAE 40 between -1°C (30°F) and 32°C (90°F). SAE 30 between -18°C (0°F) and 21°C (70°F). SAE 20 below -12°C (10°F). MIL-L-22851 Ashless Dispersant Oil: SAE 40 or SAE 50 above 16°C (60°F). SAE 40 between -1°C (30°F) and 32°C (90°F). SAE 30 or SAE 40 between -18°C (0°F) and 21°C (70°F). SAE 30 below -12°C (10°F). Oil Capacity: Sump: 6 Quarts. Total: 7 Quarts (if oil filter installed). MAXIMUM CERTIFICATED WEIGHTS Takeoff, Normal Category: 2300 lbs. Utility Category: 2000 lbs. Landing, Normal Category: 2300 lbs. Utility Category: 2000 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: 1393 lbs. Skyhawk II: 1419 lbs. Maximum Useful Load: Skyhawk: Skyhawk II: Normal Category 907 lbs. 881 lbs. CABIN AND ENTRY DIMENSIONS Utility Category 607 lbs. 581 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: 13.2 lbs./sq. ft. Power Loading: 14.4 lbs./hp. 1-4 1-5 SECTION 1 GENERAL CESSNA MODEL 172N CESSNA MODEL 172N SECTION 1 GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS 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. KIAS Knots Indicated Airspeed is the speed shown on the airspeed indicator and expressed in knots. KTAS VA VFE VNO VNE Vs Standard Tempera- ture Pressure Altitude It is expressed in either degrees Celsius (formerly Centi- grade) 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). Knots True Airspeed is the airspeed expressed in knots ENGINE POWER TERMINOLOGY 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 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. ВНР RPM Static RPM 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. AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon- strated Crosswind Velocity Usable Fuel GPH 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. Unusable Fuel 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. NMPG Vx Vy METEOROLOGICAL TERMINOLOGY OAT Outside Air Temperature is the free air static temperature. 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. 1-6 1-7 SECTION 1 GENERAL CESSNA MODEL 172N CESSNA MODEL 172N 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 Gross (Loaded) Weight Maximum Takeoff Weight 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 takeoff weight and the basic empty weight. Gross (Loaded) Weight is the loaded weight of the airplane. Maximum Takeoff Weight is the maximum weight ap- proved for the start of the takeoff run. 1-8 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. 1-9/(1-10 blank) CESSNA MODEL 172N SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS TABLE OF CONTENTS Introduction Page 2-3 Airspeed Limitations 2-4 Airspeed Indicator Markings 2-5 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 Maneuver Limits Utility Category Normal Category Utility Category Flight Load Factor Limits Normal Category Utility Category Kinds Of Operation Limits Fuel Limitations Placards 2-7 2-7 2-7 2-7 2-8 2-8 2-8 2-9 2-9 2-10 2-1/(2-2 blank) CESSNA MODEL 172N 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 have been approved by the Federal Aviation Administration. When applicable, limitations associated with optional systems or equip- ment are included in Section 9. 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. 172N. 2-3 SECTION 2 LIMITATIONS AIRSPEED LIMITATIONS CESSNA MODEL 172N 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 shown on the operational limitations placard. CESSNA MODEL 172N AIRSPEED INDICATOR MARKINGS SECTION 2 LIMITATIONS Airspeed indicator markings and their color code significance are shown in figure 2-2. MARKING KIAS VALUE OR RANGE SPEED KCAS KIAS REMARKS White Arc 41-85 VNE Never Exceed Speed 158 160 Do not exceed this speed in any operation. VNO Maximum Structural Cruising Speed 126 128 Do not exceed this speed except in smooth air, and then only with caution. Green Arc 47-128 SIGNIFICANCE 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. VA Maneuvering Speed: 2300 Pounds 96 97 1950 Pounds 88 89 1600 Pounds 80 80 Do not make full or abrupt control movements above this speed. Yellow Arc 128-160 VFE Maximum Flap Extended 86 85 Speed Do not exceed this speed with flaps down. Red Line 160 Maximum speed for all operations. Maximum Window Open Speed 158 160 Do not exceed this speed with windows open. Figure 2-2. Airspeed Indicator Markings POWER PLANT LIMITATIONS 2-4 Figure 2-1. Airspeed Limitations Engine Manufacturer: Avco Lycoming. Engine Model Number: 0-320-H2AD. Engine Operating Limits for Takeoff and Continuous Operations: Maximum Power: 160 BHP. Maximum Engine Speed: 2700 RPM. NOTE The static RPM range at full throttle (carburetor heat off and full rich mixture) is 2280 to 2400 RPM. Maximum Oil Temperature: 118°C (245°F). Oil Pressure, Minimum: 25 psi. Maximum: 100 psi. Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: 1C160/DTM7557. Propeller Diameter, Maximum: 75 inches. Minimum: 74 inches. 2-5 SECTION 2 LIMITATIONS CESSNA CESSNA MODEL 172N MODEL 172N POWER PLANT INSTRUMENT MARKINGS UTILITY CATEGORY Power plant instrument markings and their color code significance Maximum Takeoff Weight: 2000 lbs. are shown in figure 2-3. INSTRUMENT RED LINE GREEN ARC YELLOW ARC RED LINE MINIMUM LIMIT NORMAL OPERATING CAUTION RANGE MAXIMUM LIMIT Maximum Landing Weight: 2000 lbs. SECTION 2 LIMITATIONS Maximum Weight in Baggage Compartment: In the utility category, the baggage compartment and rear seat must be not occupied. Tachometer Oil Temperature 2200 2700 RPM CENTER OF GRAVITY LIMITS 2700 RPM NORMAL CATEGORY 100º-245°F 245°F Oil Pressure 25 psi 60-90 psi Carburetor Air Temperature Center of Gravity Range: Forward: 35.0 inches aft of datum at 1950 lbs. or less, with straight line variation to 38.5 inches aft of datum at 2300 lbs. Aft: 47.3 inches aft of datum at all weights. Reference Datum: Lower portion of front face of firewall. 100 psi UTILITY CATEGORY -15° to 5ºC Figure 2-3. Power Plant Instrument Markings Center of Gravity Range: Forward: 35.0 inches aft of datum at 1950 lbs. or less, with straight line variation to 35.5 inches aft of datum at 2000 lbs. Aft: 40.5 inches aft of datum at all weights. Reference Datum: Lower portion of front face of firewall. WEIGHT LIMITS NORMAL CATEGORY Maximum Takeoff Weight: 2300 lbs. Maximum Landing Weight: 2300 lbs. Maximum Weight in Baggage Compartment: 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. 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 instructor, certain maneuvers are required by the FAA. All of these maneuvers are permitted in this airplane when operated in the utility category. 2-6 2-7 SECTION 2 LIMITATIONS CESSNA CESSNA MODEL 172N MODEL 172N In the utility category, the baggage compartment and rear seat must KINDS OF OPERATION LIMITS 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 97 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. SECTION 2 LIMITATIONS 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. FLIGHT LOAD FACTOR LIMITS NOTE To ensure maximum fuel capacity when refueling, place the fuel selector valve in either LEFT or RIGHT position to prevent cross-feeding. NORMAL CATEGORY Flight Load Factors (Gross Weight 2300 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 (Gross Weight - 2000 lbs.): NOTE Takeoff and land with the fuel selector valve handle in the BOTH position. Approved Fuel Grades (and Colors): 100LL Grade Aviation Fuel (Blue). 100 (Formerly 100/130) Grade Aviation Fuel (Green). 2-8 *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. 2-9 SECTION 2 LIMITATIONS PLACARDS CESSNA CESSNA MODEL 172N MODEL 172N The following information is 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.) 2. Forward of fuel selector valve: BOTH TANKS ON FOR TAKEOFF & LANDING This airplane must be operated in compliance with the operating limitations as stated in the form of placards, markings, and manuals. MAXIMUMS. Normal Category Utility Category MANEUVERING SPEED (IAS) GROSS WEIGHT 97 knots 97 knots 2300 lbs. 2000 lbs. FLIGHT LOAD FACTOR Flaps Up +3.8, -1.52 Flaps Down +3.0 +4.4, -1.76 +3.0 - Normal Category No Acrobatic maneuvers including spins approved. Utility Category - Baggage compartment and rear seat must not be occupied. -NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW 3. On the fuel selector valve (standard tanks): SECTION 2 LIMITATIONS BOTH 40 GAL. ALL FLIGHT ATTITUDES LEFT- - 20 GAL. LEVEL FLIGHT ONLY RIGHT 20 GAL. LEVEL FLIGHT ONLY OFF On the fuel selector valve (long range tanks): - BOTH 50 GAL. ALL FLIGHT ATTITUDES LEFT RIGHT OFF 25 GAL. LEVEL FLIGHT ONLY 25 GAL. LEVEL FLIGHT ONLY 4. Maneuver Recm. Entry Speed Chandelles 105 knots . Maneuver Recm. Entry Speed Spins Slow Deceleration Lazy Eights 105 knots 95 knots Stalls (except Steep Turns whip stalls) Slow Deceleration Altitude loss in stall recovery 180 feet. -- Abrupt use of the controls prohibited above 97 knots. Spin Recovery: opposite rudder forward elevator neutralize controls. Intentional spins with flaps extended are prohibited. Flight into known icing conditions prohibited. This airplane is certified for the following flight operations as of date of original airworthiness certificate: DAY - - NIGHT VFR - IFR Near fuel tank filler cap (standard tanks): FUEL 100LL/100 MIN. GRADE AVIATION GASOLINE CAP. 21.5 U.S. GAL. Near fuel tank filler cap (long range tanks): FUEL 100LL/100 MIN. GRADE AVIATION GASOLINE CAP. 27 U.S. GAL. 2-10 2-11 SECTION 2 LIMITATIONS 2-12 5. Near flap indicator: AVOID SLIPS WITH FLAPS EXTENDED 6. In baggage compartment: CESSN MODEL 172 CESSNA MODEL 172N SECTION 3 EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES 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 TABLE OF CONTENTS Introduction Forced Landings Page 3-3 Airspeeds For Emergency Operation 3-3 OPERATIONAL CHECKLISTS Engine Failures 3-3 Engine Failure During Takeoff Run Engine Failure Immediately After Takeoff Engine Failure During Flight 3-3 3-4 3-4 3-4 Emergency Landing Without Engine Power Precautionary Landing With Engine Power Ditching 3-4 3-4 3-5 Fires During Start On Ground Engine Fire In Flight Cabin Fire 3-5 3-5 3-6 Electrical Fire In Flight 3-6 3-6 Static Source Blockage (Erroneous Instrument Reading Electrical Power Supply System Malfunctions Wing Fire Icing Inadvertent Icing Encounter Suspected) • Landing With A Flat Main Tire Over-Voltage Light Illuminates Ammeter Shows Discharge AMPLIFIED PROCEDURES Engine Failure Forced Landings Landing Without Elevator Control Fires 3-11 3-12 3-12 3-12 3-7 3-7 3-7 3-8 3-8 3-8 3-8 3-9 3-1