Cessna 172S Pilot's Operating Handbook

Section 1 provides basic data and information of general interest. It also contains definitions or explanations of symbols, abbreviations, and terminology commonly used. NOTES: 1. 2. Wing span shown with strobe lights installed. Maximum height shown with nose gear depressed, all tires and nose strut properly inflated, and flashing beacon installed. Wheel ase length is 65". 3. 4. Propeller ground clearance is 11 3/4". 5. Wing area is 174 square feet. 6. Minimum turning radius (*pivot point to outboard wing tip) is 27' 5%". PIVOT POINT DESCRIPTIVE DATA ENGINE Number of Engines: 1. Engine Manufacturer: Avco Lycoming. Engine Model Number: 0-320-E2D. 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: 150 rated BHP at 2700 RPM. PROPELLER Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: 1C160/DTM7553. Number of Blades: 2. Propeller Diameter, Maximum: 75 inches. Minimum: 74 inches. Propeller Type: Fixed pitch. FUEL Fuel Grade (and Color): 80/87 Minimum Grade Aviation Fuel (red). Alternate fuels which are also approved are: 100/130 Low Lead AVGAS (green). (Maximum lead content of 2 cc per gallon.) 100/130 Aviation Grade Fuel (green). (Maximum lead content of 4.6 cc per gallon.) NOTE When substituting a higher octane fuel, low lead AVGAS 100 should be used whenever possible since it will result in less lead contamination of the engine. 1-3 SECTION 1 GENERAL CESSNA MODEL 172M CESSNA MODEL 172M SECTION 1 GENERAL Fuel Capacity: OIL Standard Tanks: Total Capacity: 42 gallons. Total Capacity Each Tank: 21 gallons. Total Usable: 38 gallons. Long Range Tanks: Total Capacity: 52 gallons. Total Capacity Each Tank: 26 gallons. Total Usable: 48 gallons. NOTE To ensure maximum fuel capacity when refueling, place 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, 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: Maximum Useful Load: Skyhawk: Skyhawk II: 1387 lbs. Skyhawk II: 1412 lbs. Normal Category 913 lbs. 888 lbs. CABIN AND ENTRY DIMENSIONS Utility Category 613 lbs. 588 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 illus- trated in detail in Section 6. SPECIFIC LOADINGS Wing Loading: 13. 2 lbs./sq. ft. Power Loading: 15.3 lbs./hp. 1-4 1-5 SECTION 1 GENERAL CESSNA CESSNA MODEL 172M MODEL 172M SECTION 1 GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS KIAS KTAS VA V FE VNO V NE Vs √ So 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. 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 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 ex- ceeded 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. Standard Tempera- ture Pressure Altitude 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). ENGINE POWER TERMINOLOGY 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 en- gine runup when the airplane is on the ground and stationary. AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon- 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 in not considered to be limiting. Usable Fuel Usable Fuel is the fuel available for flight planning. Unusable Unusable Fuel is the quantity of fuel that can not be safely used in flight. Fuel GPH NMPG Vx Best Angle-of-Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance. g Best Rate-of-Climb Speed is the speed which results in the greatest gain in altitude in a given time. VY METEOROLOGICAL TERMINOLOGY 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 OAT Outside Air Temperature is the free air static temperature. It is expressed in either degrees Celsius (formerly Centi- grade) or degrees Fahrenheit. Station 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. 1-6 1-7 SECTION 1 GENERAL Arm Moment Center of Gravity (C. G.) C. G. Arm C. G. Limits Standard Empty Weight CESSNA MODEL 172M 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.) 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 Basic Empty Weight is the standard empty weight plus the Weight weight of optional equipment. Useful Load Gross (Loaded) Weight Maximum Takeoff Weight Maximum Landing Weight Tare 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. 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. CESSNA MODEL 172M SECTION 2 LIMITATIONS TABLE OF CONTENTS Introduction Airspeed Limitations Airspeed Indicator Markings Power Plant Limitations Normal Category Utility Category SECTION 2 LIMITATIONS Page 2-3 2-4 2-5 2-5 Power Plant Instrument Markings Weight Limits 2-6 2-6 2-6 2-7 2-7 2-7 2-7 2-7 2-7 2-7 2-8 2-8 2-8 2-9 2-9 2-10 Center of Gravity Limits Normal Category . Utility Category Maneuver Limits Normal Category Utility Category Flight Load Factor Limits Normal Category Utility Category Kinds of Operation Limits Fuel Limitations Placards 1-8 2-1/(2-2 blank) CESSNA MODEL 172M INTRODUCTION SECTION 2 LIMITATIONS 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. NOT E 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 alter- nate static source is being used, ample margins should be observed to allow for the airspeed calibration varia- tions 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. 172M. 2-3 SECTION 2 LIMITATIONS AIRSPEED LIMITATIONS CESSNA MODEL 172M Airspeed limitations and their operational significance are shown in figure 2-1. CESSNA MODEL 172M SECTION 2 LIMITATIONS AIRSPEED INDICATOR MARKINGS 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 126 128 Cruising Speed Do not exceed this speed except in smooth air, and then only with caution. Green Arc 47-128 SIGNIFICANCE VA Maneuvering Speed: 2300 Pounds 96 97 Do not make full or abrupt 1950 Pounds 89 control movements above 1600 Pounds 80 80 this speed. Yellow Arc 128-160 Full Flap Operating Range. Lower limit is maximum weight VS。 in landing configuration. Upper limit is maximum speed permissible with flaps extended. Normal Operating Range. Lower limit is maximum weight Vs with flaps retracted. Upper limit is maxi- mum structural cruising speed. Operations must be conducted with caution and only in smooth air. VFE Maximum Flap Extended 86 85 Speed Do not exceed this speed with flaps down. Red Line 160 Maximum Window Open Speed 158 160 Do not exceed this speed Maximum speed for all operations. Figure 2-2. Airspeed Indicator Markings with windows open. 2-4 Figure 2-1. Airspeed Limitations POWER PLANT LIMITATIONS Engine Manufacturer: Avco Lycoming. Engine Model Number: 0-320-E2D. Engine Operating Limits for Takeoff and Continuous Operations: Maximum Power: 150 BHP. Maximum Engine Speed: 2700 RPM. NOTE The static RPM range at full throttle (carburetor heat off) is 2300 to 2420 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/DTM7553. Propeller Diameter, Maximum: 75 inches. Minimum: 74 inches. 2-5 SECTION 2 LIMITATIONS CESSNA MODEL 172M POWER PLANT INSTRUMENT MARKINGS Power plant instrument markings and their color code significance are shown in figure 2-3. RED LINE GREEN ARC YELLOW ARC RED LINE INSTRUMENT MINIMUM LIMIT NORMAL OPERATING CAUTION RANGE Tachometer At Sea Level At 5000 Ft. At 10,000 Ft. 2200 - 2500 RPM 2200 - 2600 RPM MAXIMUM LIMIT 2700 RPM 2700 RPM 2700 RPM 245°F Oil Temperature 2200 - 2700 RPM 100°-245°F Oil Pressure 25 psi 60-90 psi 100 psi -15° to 5ºC Carburetor Air Temperature Figure 2-3. Power Plant Instrument Markings 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. CESSNA MODEL 172M UTILITY CATEGORY Maximum Takeoff Weight: 2000 lbs. Maximum Landing Weight: 2000 lbs. SECTION 2 LIMITATIONS 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 38.5 inches aft of datum at 2300 lbs. Aft: 47. 3 inches aft of datum at all weights. Reference Datum: 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 35. 5 inches aft of datum at 2000 lbs. Aft: 40.5 inches aft of datum at all weights. Reference Datum: 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) and turns in which the angle of bank is not more than 60°. UTILITY CATEGORY This airplane is not designed for purely aerobatic flight. However, in the acquisition of various certificates such as commercial pilot, instru- ment pilot and flight instructor, certain maneuvers are required by the FAA. All of these maneuvers are permitted in this airplane when oper- ated in the utility category. In the utility category, the baggage compartment and rear seat must 2-6 2-7 SECTION 2 LIMITATIONS CESSNA MODEL 172M not be occupied. No aerobatic maneuvers are approved except those list- ed below: MANEUVER Chandelles. Lazy Eights Steep Turns Spins RECOMMENDED ENTRY SPEED* 105 knots 105 knots 95 knots CESSNA MODEL 172M KINDS OF OPERATION LIMITS 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 re- quired instrumentation and equipment for these operations. The refer- ence to types of flight operations on the operating limitations placard re- flects equipment installed at the time of Airworthiness Certificate issuance. Flight into known icing conditions is prohibited. Stalls (Except Whip Stalls). 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 ex- tended are prohibited. FUEL LIMITATIONS 2 Standard Tanks: 21 U. S. gallons each. Total Fuel: 42 U.S. gallons. Usable Fuel (all flight conditions): 38 U. S. gallons. Unusable Fuel: 4.0 U.S. gallons. 2 Long Range Tanks: 26 U.S. gallons each. Total Fuel: 52 U.S. gallons. Usable Fuel (all flight conditions): 48 U.S. gallons. Unusable Fuel: 4.0 U.S. gallons. FLIGHT LOAD FACTOR LIMITS NORMAL CATEGORY NOTE To ensure maximum fuel capacity when refueling, place the fuel selector valve in either LEFT or RIGHT posi- tion to prevent cross-feeding. NOTE 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 Takeoff and land with the fuel selector valve handle in the BOTH position. Fuel Grade (and Color): 80/87 Minimum Grade Aviation Fuel (red). Alternate fuels which are also approved are: 100/130 Low Lead AVGAS (green). (Maximum lead content of 2 cc per gallon.) 100/130 Aviation Grade Fuel (green). (Maximum lead content of 4. 6 cc per gallon.) Flight Load Factors (Gross Weight - 2000 lbs.) *Flaps Up . *Flaps Down . +4.4g, -1.76g +3.0g 2-8 NOTE *The design load factors are 150% of the above, and in all cases, the structure meets or exceeds design loads. When substituting a higher octane fuel, low lead AVGAS 100 should be used whenever possible since it will result in less lead contamination of the engine. 2-9 SECTION 2 LIMITATIONS CESSNA MODEL 172M CESSNA MODEL 172M PLACARDS 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 (3) On the fuel selector valve (standard tanks): 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) 97 knots . GROSS WEIGHT 2300 lbs. 97 knots 2000 lbs. . FLIGHT LOAD FACTOR Flaps Up Flaps Down +3.8, -1.52 +3.0 . +4.4, -1.76 +3.0 BOTH - 38 GAL. ALL FLIGHT ATTITUDES LEFT 19 GAL. LEVEL FLIGHT ONLY RIGHT - 19 GAL. LEVEL FLIGHT ONLY OFF On the fuel selector valve (long range tanks): Normal Category - No acrobatic maneuvers including spins approved. Utility Category not be occupied. Baggage compartment and rear seat must NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW Maneuver Recm. Entry Speed Chandelles. . 105 knots Lazy Eights Steep Turns . 105 knots 95 knots Altitude loss in stall recovery -- - Maneuver Recm. Entry Speed Spins Slow Deceleration Stalls (except whip stalls) Slow Deceleration 180 feet. - neutralize Abrupt use of controls prohibited above 97 knots. Spin Recovery: opposite rudder forward elevator 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 BOTH LEFT RIGHT OFF - - 48 GAL. ALL FLIGHT ATTITUDES 24 GAL. LEVEL FLIGHT ONLY - 24 GAL. LEVEL FLIGHT ONLY (4) Near fuel tank filler cap (standard tanks): FUEL 80/87 MIN. GRADE AVIATION GASOLINE CAP. 21 U. S. GAL. Near fuel tank filler cap (long range tanks): FUEL 80/87 MIN. GRADE AVIATION GASOLINE CAP. 26 U. S. GAL. 2-10 SECTION 2 LIMITATIONS 2-11 SECTION 2 LIMITATIONS 2-12 (5) Near flap indicator: AVOID SLIPS WITH FLAPS EXTENDED (6) 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 CESSNA MODEL 172M CESSNA MODEL 172M SECTION 3 EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS (7) On the instrument panel near over-voltage light: Forced Landings HIGH VOLTAGE Page Introduction 3-3 Airspeeds For Safe 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 3-3 3-4 3-4 Emergency Landing Without Engine Power Precautionary Landing With Engine Power Ditching. 3-4 3-4 3-5 Fires 3-5 Engine Fire During Start On Ground 3-5 Engine Fire In Flight . 3-6 Electrical Fire In Flight 3-6 Cabin Fire 3-6 Wing Fire 3-7 Icing 3-7 Inadvertent Icing Encounter 3-7 Static Source Blockage (Erroneous Instrument Reading Suspected). 3-8 Landing With A Flat Main Tire 3-8 Electrical Power Supply System Malfunctions 3-8 Over-Voltage Light Illuminates 3-8 Ammeter Shows Discharge 3-8 AMPLIFIED PROCEDURES Engine Failure . 3-9 Forced Landings 3-10 3-1