Cessna 152 Pilot's Operating Handbook

The above performance figures are based on the indicated weights, standard atmospheric conditions, level hard-surface dry runways and no wind. They are calculated values derived from flight tests conducted by the Cessna Aircraft Company under carefully documented conditions and will vary with individual airplanes and numerous factors affecting flight performance. LOG OF EFFECTIVE PAGES Dates of issue for original and revised pages are: Original Revision 1 Page Title Assignment Record i thru ii *iii 18 April 1980 18 April 1980 18 April 1980. 31 March 1983 18 April 1980 18 April 1980 5-20 Blank 6-1 18 April 1980 31 March 1983 Date Page Date *5-14 thru 5-18 5-19 31 March 1983 18 April 1980 18 April 1980 18 April 1980 iv 6-2 Blank 18 April 1980 1-1 thru 1-2 6-3 thru 6-23 18 April 1980 *1-3 thru 1-4 31 March 1983 6-24 Blank 18 April 1980 1-5 thru 1-8 *2-1 18 April 1980 7-1 thru 7-33 18 April 1980 31 March 1983 *2-2 Blank 2-3 thru 2-11 2-12 Blank 31 March 1983 7-34 Blank 8-1 18 April 1980 18 April 1980 3-1 thru 3-15 3-16 Blank 18 April 1980 18 April 1980 18 April 1980 18 April 1980 18 April 1980 31 March 1983 18 April 1980 18 April 1980 18 April 1980 31 March 1983 18 April 1980. 18 April 1980 18 April 1980 5-2 Blank 5-3 thru 5-13 18 April 1980 18 April 1980 tems. 4-1 thru 4-14 *4-15 thru 4-18 4-19 thru 4-23 4-24 Blank 5-1 8-2 Blank 8-3 thru 8-9 *8-10 thru 8-11 8-12 thru 8-17 8-18 Blank *9-1 thru 9-2 NOTE 18 April 1980 31 March 1983 Refer to Section 9 Table of Contents for supplements applicable to optional sys- ii 18 April 1980 18 April 1980 Revision 1 31 March 1983/D1190-1-13PH iii TABLE OF CONTENTS iv CESSNA MODEL 152 TABLE OF CONTENTS SECTION GENERAL..... 1 LIMITATIONS.... 2 EMERGENCY PROCEDURES.. 3 NORMAL PROCEDURES.. 4 PERFORMANCE……. 5 WEIGHT & BALANCE/ EQUIPMENT LIST AIRPLANE & SYSTEMS DESCRIPTIONS 6 7 AIRPLANE HANDLING, SERVICE & MAINTENANCE ……………….. 8 SUPPLEMENTS (Optional Systems Description & Operating Procedures) 9 18 April 1980 CESSNA MODEL 152 SECTION 1 GENERAL TABLE OF CONTENTS SECTION 1 GENERAL Page Specific Loadings Three View Introduction Descriptive Data Engine Propeller Fuel Oil Maximum Certificated Weights Standard Airplane Weights Cabin And Entry Dimensions Baggage Space Dimensions Symbols, Abbreviations And Terminology 1-2 1-3 1-3 1-3 1-3 1-3 1-4 1-5 1-5 1-5 1-5 1-5 1-5 General Airspeed Terminology And Symbols 1-5 Meteorological Terminology 1-6 Engine Power Terminology 1-7 Airplane Performance And Flight Planning Terminology 1-7 Weight And Balance Terminology 1-7 18 April 1980 1-1 SECTION 1 GENERAL 1-2 PIVOT POINT 69" MAX. CESSNA MODEL 152 8'-6" MAX. CESSNA MODEL 152 THIS DATA APPLICABLE ONLY TO AIRPLANES WITH LYCOMING 0-235-L2C ENGINE. FOR AIRPLANES WITH ENGINE MODIFIED TO O-235-N2C, REFER TO DATA IN SECTION 9 SUPPLEMENT. 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. 24'-1" 10'-0" NOTES: 1. Wing span shown with conical cam- ber wing tips and strobe lights in- stalled. If standard wing tips with- out strobe lights are installed, wing span is 32' 8 1/2". 2. Maximum height shown when equipped with 6.00- 6 main gear tires, flashing beacon in- stalled, nose gear depressed, and all tires and nose strut properly inflated. 3. Wheel base length is 58". 4. Propeller ground clearance is 12". 5. Wing area is 159 1/2 square feet. 6. Minimum turning radius (pivot point to outboard wing tip) is 24'-8" 0 0 * PIVOT POINT DESCRIPTIVE DATA ENGINE Number of Engines: 1. Engine Manufacturer: Avco Lycoming. Engine Model Number: O-235-L2C. Engine Type: Normally-aspirated, direct-drive, air-cooled, horizontally- opposed, carburetor equipped, four-cylinder engine with 233.3 cu. in. displacement. Horsepower Rating and Engine Speed: 110 rated BHP at 2550 RPM. PROPELLER Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: 1A103/TCM6958. Number of Blades: 2. Propeller Diameter, Maximum: 69 inches. Minimum: 67.5 inches. Propeller Type: Fixed pitch. 33'-4" 7'-7 1/4" Figure 1-1. Three View 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. 18 April 1980 18 April 1980 Revision 1 - 31 March 1983 1-3 SECTION 1 GENERAL THIS DATA APPLICABLE ONLY TO AIRPLANES WITH LYCOMING O-235-L2C ENGINE. FOR AIRPLANES WITH ENGINE MODIFIED TO O-235-N2C, REFER TO DATA IN SECTION 9 SUPPLEMENT. CESSNA MODEL 152 CESSNA MODEL 152 SECTION 1 GENERAL Fuel Capacity: Standard Tanks: Total Capacity: 26 gallons. Total Capacity Each Tank: 13 gallons. Total Usable: 24.5 gallons. Long Range Tanks: Total Capacity: 39 gallons. Total Capacity Each Tank: 19.5 gallons. Total Usable: 37.5 gallons. NOTE Due to cross-feeding between fuel tanks, the tanks should be re-topped after each refueling to assure maximum capacity. 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: 6 Quarts. Total: 7 Quarts (with oil filter). MAXIMUM CERTIFICATED WEIGHTS Ramp: 1675 lbs. Takeoff: 1670 lbs. Landing: 1670 lbs. Weight in Baggage Compartment: Baggage Area 1 (or passenger on child's seat) - Station 50 to 76: 120 lbs. See note below. Baggage Area 2 - Station 76 to 94: 40 lbs. See note below. NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 120 lbs. STANDARD AIRPLANE WEIGHTS Standard Empty Weight, 152: 1107 lbs. 152 II: 1141 lbs. Maximum Useful Load, 152: 568 lbs. 152 II: 534 lbs. CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6. BAGGAGE SPACE DIMENSIONS Baggage area dimensions are illustrated in detail in Section 6. SPECIFIC LOADINGS Wing Loading: 10.5 lbs./sq. ft. Power Loading: 15.2 lbs./hp. SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS 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. KCAS 1-4 18 April 1980 Revision 1 - 31 March 1983 18 April 1980 1-5 SECTION 1 GENERAL CESSNA MODEL 152 CESSNA MODEL 152 SECTION 1 GENERAL KIAS Knots Indicated Airspeed is the speed shown on the airspeed indicator and expressed in knots. ENGINE POWER TERMINOLOGY BHP KTAS Knots True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature. RPM Static RPM A VFE V NO VNE Vs Vx VY 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. 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 Unusable Fuel GPH NMPG Best Rate-of-Climb Speed is the speed which results in the greatest gain in altitude in a given time. g 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. 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. WEIGHT AND BALANCE TERMINOLOGY Reference Datum Station Standard Temperature is 15°C at sea level pressure alti- tude and decreases by 2°C for each 1000 feet of altitude. Arm 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). Moment 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 1-6 18 April 1980 18 April 1980 1-7 SECTION 1 GENERAL Center of Gravity (C.G.) C.G. Arm C.G. Limits Standard Empty Weight Basic Empty Weight Useful Load Maximum Ramp Weight Maximum Takeoff Weight Maximum Landing Weight Tare CESSNA MODEL 152 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. 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. CESSNA MODEL 152 SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS THIS DATA APPLICABLE ONLY TO AIRPLANES WITH LYCOMING O-235-L2C ENGINE. FOR AIRPLANES WITH ENGINE MODIFIED TO O-235-N2C, REFER TO DATA IN SECTION 9 SUPPLEMENT. TABLE OF CONTENTS Introduction Airspeed Limitations Airspeed Indicator Markings Power Plant Limitations Power Plant Instrument Markings Weight Limits Center Of Gravity Limits Maneuver Limits Flight Load Factor Limits Kinds Of Operation Limits Fuel Limitations Other Limitations Flap Limitations Placards Page 2-3 2-3 2-4 2-4 2-5 2-6 2-6 2-6 2-7 2-7 2-7 2-8 2-8 2-9 1-8 18 April 1980 18 April 1980 Revision 1 - 31 March 1983 2-1/(2-2 blank) CESSNA MODEL 152 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. Your Cessna is certificated under FAA Type Certificate No. 3A19 as Cessna Model No. 152. AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in figure 2-1. SPEED KCAS KIAS REMARKS VNE Never Exceed Speed 145 149 Do not exceed this speed in any operation. VNO Maximum Structural 108 111 Cruising Speed Do not exceed this speed except in smooth air, and then only with caution. VA Maneuvering Speed: 1670 Pounds 101 104 1500 Pounds 96 98 1350 Pounds 91 93 Do not make full or abrupt control movements above this speed. VFE Maximum Flap Extended Speed 87 85 Do not exceed this speed with flaps down. Maximum Window Open Speed 145 149 Do not exceed this speed with windows open. 18 April 1980 Figure 2-1. Airspeed Limitations 2-3 SECTION 2 LIMITATIONS AIRSPEED INDICATOR MARKINGS CESSNA MODEL 152 Airspeed indicator markings and their color code significance are shown in figure 2-2. MARKING KIAS VALUE OR RANGE White Arc 35 - 85 SIGNIFICANCE CESSNA MODEL 152 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: 1A103/TCM6958. Propeller Diameter, Maximum: 69 inches. Minimum: 67.5 inches. Green Arc Yellow Arc Red Line 40 - 111 111 - 149 149 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 POWER PLANT LIMITATIONS Engine Manufacturer: Avco Lycoming. Engine Model Number: O-235-L2C. Maximum Power: 110 BHP rating. Engine Operating Limits for Takeoff and Continuous Operations: Maximum Engine Speed: 2550 RPM. 2-4 NOTE The static RPM range at full throttle (carburetor heat off and mixture leaned to maximum RPM) is 2280 to 2380 RPM. SECTION 2 LIMITATIONS POWER PLANT INSTRUMENT MARKINGS Power plant instrument markings and their color code significance are shown in figure 2-3. INSTRUMENT RED LINE MINIMUM LIMIT GREEN ARC RED LINE NORMAL OPERATING MAXIMUM LIMIT Tachometer: Sea Level 4000 Feet - 1900 2350 RPM 1900 2450 RPM 2550 RPM 8000 Feet 1900 2550 RPM Oil Temperature 100° - 245°F 245°F Oil Pressure 25 psi 60 - 90 psi 115 psi Fuel Quantity E (0.75 Gal. Unusable Each Tank) Suction 4.5 5.4 in. Hg 18 April 1980 18 April 1980 Figure 2-3. Power Plant Instrument Markings 2-5 SECTION 2 LIMITATIONS WEIGHT LIMITS Maximum Ramp Weight: 1675 lbs. Maximum Takeoff Weight: 1670 lbs. Maximum Landing Weight: 1670 lbs. Maximum Weight in Baggage Compartment: CESSNA MODEL 152 CESSNA MODEL 152 Baggage Area 1 (or passenger on child's seat) - Station 50 to 76: 120 lbs. See note below. Baggage Area 2 - Station 76 to 94: 40 lbs. See note below. SECTION 2 LIMITATIONS 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. NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 120 lbs. CENTER OF GRAVITY LIMITS Center of Gravity Range: Forward: 31.0 inches aft of datum at 1350 lbs. or less, with straight line variation to 32.65 inches aft of datum at 1670 lbs. Aft: 36.5 inches aft of datum at all weights. Reference Datum: Front face of firewall. MANEUVER LIMITS This airplane is certificated in the utility category and is designed for limited aerobatic flight. In the acquisition of various certificates such as commercial pilot and flight instructor, certain maneuvers are required. All of these maneuvers are permitted in this airplane. No aerobatic maneuvers are approved except those listed below: MANEUVER Chandelles RECOMMENDED ENTRY SPEED* .95 knots .95 knots .95 knots FLIGHT LOAD FACTOR LIMITS Flight Load Factors: *Flaps Up: +4.4g, -1.76g *Flaps Down: +3.5g *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. Lazy Eights Steep Turns Spins Stalls (Except Whip Stalls) Use Slow Deceleration Use Slow Deceleration *Higher speeds can be used if abrupt use of the controls is avoided. The baggage compartment and/or child's seat must not be occupied during aerobatics. FUEL LIMITATIONS 2 Standard Tanks: 13 U.S. gallons each. Total Fuel: 26 U.S. gallons. Usable Fuel (all flight conditions): 24.5 U.S. gallons. Unusable Fuel: 1.5 U.S. gallons. 2 Long Range Tanks: 19.5 U.S. gallons each. Total Fuel: 39 U.S. gallons. Usable Fuel (all flight conditions): 37.5 U.S. gallons. Unusable Fuel: 1.5 U.S. gallons. 2-6 18 April 1980 18 April 1980 2-7 SECTION 2 LIMITATIONS CESSNA MODEL 152 CESSNA MODEL 152 SECTION 2 LIMITATIONS NOTE Due to cross-feeding between fuel tanks, the tanks should be re-topped after each refueling to assure maximum capacity. Takeoffs have not been demonstrated with less than 2 gallons of total fuel (1 gallon per tank). 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). OTHER LIMITATIONS FLAP LIMITATIONS Approved Takeoff Range: 0° to 10°. Approved Landing Range: 0° to 30°. 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 operating limitations which must be complied with when operat- ing this airplane in the Utility Category. Other operating limita- tions which must be complied with when operating this airplane in this category are contained in the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW Rec. Entry Speed Slow Decel. Maneuver Rec. Entry Speed Maneuver Chandelles 95 KIAS Lazy 8's 95 KIAS Steep Turns 95 KIAS Spins.. Stalls (Ex- cept Whip Stalls).. Slow Decel. Intentional spins prohibited with flaps extended. 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 2. In the baggage compartment: 120 LBS. MAXIMUM BAGGAGE AND/OR AUXILIARY SEAT PAS- SENGER. FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA. 2-8 18 April 1980 18 April 1980 2-9 SECTION 2 LIMITATIONS 3. Near fuel shutoff valve (standard tanks): FUEL - 24.5 GALS - ON-OFF Near fuel shutoff valve (long range tanks): FUEL 37.5 GALS - - ON-OFF 4. Near fuel tank filler cap (standard tanks): 5. CESSNA MODEL 152 CESSNA MODEL 152 6. SECTION 2 LIMITATIONS A calibration card is provided to indicate the accuracy of the magnetic compass in 30° increments. 7. On oil filler cap: 8. On control lock: OIL 6 QTS CONTROL LOCK; REMOVE BEFORE STARTING ENGINE FUEL 100LL/100 MIN. GRADE AVIATION GASOLINE CAP. 13 U.S. GAL. 9. Near airspeed indicator: Near fuel tank filler cap (long range tanks): FUEL 100LL/100 MIN. GRADE AVIATION GASOLINE CAP. 19.5 U.S. GAL. CAP 13.0 U.S. GAL. TO BOTTOM OF FILLER COLLAR On the instrument panel near the altimeter: SPIN RECOVERY 1. VERIFY AILERONS NEUTRAL AND THROTTLE CLOSED APPLY FULL OPPOSITE RUDDER 2. 3. 4. MOVE CONTROL WHEEL BRISKLY FORWARD TO BREAK STALL NEUTRALIZE RUDDER AND RECOVER FROM DIVE 2-10 MANEUVER SPEED - 104 KIAS 18 April 1980 18 April 1980 2-11/(2-12 blank) CESSNA MODEL 152 SECTION 3 EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS Page Introduction 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 3-3 3-4 • Fires Forced Landings Emergency Landing Without Engine Power Precautionary Landing With Engine Power Ditching During Start On Ground 3-4 3-4 3-4 3-5 3-5 3-5 Engine Fire In Flight Electrical Fire In Flight 3-5 3-6 Cabin Fire Wing Fire Icing Inadvertent Icing Encounter Landing With A Flat Main Tire Electrical Power Supply System Malfunctions 3-6 3-7 3-7 3-7 3-8 3-8 Ammeter Shows Excessive Rate Of Charge (Full Scale Deflection) 3-8 Low-Voltage Light Illuminates During Flight (Ammeter Indicates Discharge) 3-8 AMPLIFIED PROCEDURES Engine Failure Forced Landings Landing Without Elevator Control Fires 18 April 1980 3-9 3-10 3-10 3-10 3-1