Normal Procedures for the Cessna 152 Aerobat

Section 1 provides basic data and information of general interest. It also contains definitions or explanations of symbols, abbreviations, and terminology commonly used. -10'-0". NOTES: 1. Wing span shown with strobe lights installed. 2. Maximum height shown with nose gear de- pressed, all tires and nose strut property in- flated, and flashing beacon installed. 3. Wheel base length is 58". 4. Propeller ground clearance is 12". 5. Wing area is 160 square feet. 6. outboard wing tip) is 24' 8". Minimum turning radius (* pivot point to 00 PIVOT POINT 33'-4" 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. -7'-7"- Figure 1-1. Three View FUEL Approved Fuel Grades (and Colors): 100LL Grade Aviation Fuel (Blue). 100 (Formerly 100/130) Grade Aviation Fuel (Green). Fuel Capacity: Standard Tanks: Total Capacity: 26 gallons. Total Capacity Each Tank: 13 gallons. Total Usable: 24.5 gallons. 1-3 SECTION 1 GENERAL CESSNA MODEL 152 CESSNA MODEL 152 SECTION 1 GENERAL 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. MAXIMUM CERTIFICATED WEIGHTS 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 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. 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: 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: The maximum combined weight capacity for baggage areas 1 and 2 is 120 lbs. STANDARD AIRPLANE WEIGHTS Standard Empty Weight, 152: 1081 lbs. 152 II: 1118 lbs. Maximum Useful Load, 152: 589 lbs. 152 II: 552 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. 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). 1-4 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. 1-5 SECTION 1 GENERAL KIAS KTAS V VFE VNO VNE Vs ༨༠ CESSNA MODEL 152 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 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. METEOROLOGICAL TERMINOLOGY OAT Standard Tempera- ture Outside Air Temperature is the free air static temperature. 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. CESSNA MODEL 152 ENGINE POWER TERMINOLOGY BHP RPM Static RPM SECTION 1 GENERAL 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 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. WEIGHT AND BALANCE TERMINOLOGY Reference Datum Station 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 1-7 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 have been approved by the Federal Aviation Administration. When applicable, limitations associated with optional systems or equip- ment are included in Section 9. 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 Do not make full or abrupt 1500 Pounds 96 98 control movements above 1350 Pounds 91 93 this speed. VFE Maximum Flap Extended Do not exceed this speed Speed 87 85 with flaps down. Maximum Window Open Speed 139 143 Do not exceed this speed with windows open. 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 White Arc Green Arc Yellow Arc KIAS VALUE OR RANGE 35-85 133-35 40-111 111 - 149 Vno-111 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. CESSNA MODEL 152 SECTION 2 LIMITATIONS POWER PLANT INSTRUMENT MARKINGS Power plant instrument markings and their color code significance are shown in figure 2-3. NORMAL OPERATING MAXIMUM LIMIT RED LINE GREEN ARC RED LINE INSTRUMENT MINIMUM LIMIT 1900 2550 RPM 2550 RPM 100° - 245°F 245°F 60 - 90 psi 100 psi Tachometer Oil Temperature Oil Pressure 25 psi Figure 2-3. Power Plant Instrument Markings Red Line VIVE 149 Maximum speed for all operations. Figure 2-2. Airspeed Indicator Markings POWER PLANT LIMITATIONS Engine Manufacturer: Avco Lycoming. Engine Model Number: O-235-L2C. Engine Operating Limits for Takeoff and Continuous Operations: Maximum Power: 110 BHP. Maximum Engine Speed: 2550 RPM. NOTE The static RPM range at full throttle (carburetor heat off and mixture leaned to maximum RPM) is 2280 to 2380 RPM. Maximum Oil Temperature: 118°C (245°F). Oil Pressure, Minimum: 25 psi. Maximum: 100 psi. Hopeller Manufacturer: McCauley Accessory Division. Hopeller Model Number: 1A103/TCM6958. Propeller Diameter, Maximum: 69 inches. Minimum: 67.5 inches. WEIGHT LIMITS Maximum Takeoff Weight: 1670 lbs. Maximum Landing Weight: 1670 lbs. Maximum 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. 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. 2-5 SECTION 2 LIMITATIONS MANEUVER LIMITS CESSNA MODEL 152 CESSNA MODEL 152 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, instrument pilot and flight instructor, certain maneuv- ers are required. All of these maneuvers are permitted in this airplane. No aerobatic maneuvers are approved except those listed below: MANEUVER Chandelles Lazy Eights Steep Turns Spins Stalls (Except Whip Stalls) MAXIMUM ENTRY SPEED* .95 knots .95 knots 95 knots Use Slow Deceleration Use Slow Deceleration *Higher speeds can be used if abrupt use of the controls is avoided. 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. SECTION 2 LIMITATIONS 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: 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. NOTE Due to cross-feeding between fuel tanks, the tanks should be re-topped after each refueling to assure maximum capacity. 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. NOTE Takeoffs have not been demonstrated with less than 2 gallons total fuel (1 gallon per tank). Approved Fuel Grades (and Colors): 100LL Grade Aviation Fuel (Blue). 100 (Formerly 100/130) Grade Aviation Fuel (Green). 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- 2-6 2-7 SECTION 2 LIMITATIONS PLACARDS CESSNA MODEL 152 CESSNA MODEL 152 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.) 3. Near fuel shutoff valve (standard tanks): FUEL 24.5 GALS ON-OFF - - Near fuel shutoff valve (long range tanks): SECTION 2 LIMITATIONS This airplane is approved in the utility category and must be operated in compliance with the operating limitations as stated in the form of placards, markings and manuals. MAXIMUMS MANEUVERING SPEED (IAS) GROSS WEIGHT 104 knots 1670 lbs +4.4, -1.76 Flaps Down +3.5 FLIGHT LOAD FACTOR Flaps Up NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW 4. FUEL 37.5 GALS-ON-OFF - Near fuel tank filler cap (standard tanks): FUEL 100LL/100 MIN. GRADE AVIATION GASOLINE CAP. 13 U.S. GAL. 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 Maneuver Recm. Entry Speed Chandelles 95 knots Maneuver Spins Lazy Eights Steep Turns 95 knots 95 knots Recm. Entry Speed Slow Deceleration Stalls (except whip stalls). Slow Deceleration Abrupt use of controls prohibited above 104 knots. Intentional spins with flaps extended are prohibited. Altitude loss in stall recovery 160 ft. 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 - 123 2. 4. 5. On the instrument panel near the altimeter: SPIN RECOVERY VERIFY AILERONS NEUTRAL AND THROTTLE CLOSED APPLY FULL OPPOSITE RUDDER MOVE CONTROL WHEEL BRISKLY FORWARD TO BREAK STALL NEUTRALIZE RUDDER AND RECOVER FROM DIVE 2-8 2. In the baggage compartment: 120 lbs. maximum baggage and/or auxiliary seat passenger. For additional loading instructions see Weight and Balance Data. 2-9/(2-10 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 Forced Landings 3-4 Emergency Landing Without Engine Power Precautionary Landing With Engine Power Ditching 3-4 3-4 3-5 Fires 3-5 During Start On Ground 3-5 Icing Engine Fire In Flight Electrical Fire In Flight Cabin Fire Wing Fire Inadvertent Icing Encounter 3-5 3-6 3-6 3-7 3-7 3-7 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 Forced Landings Landing Without Elevator Control Fires 3-9 3-10 3-10 3-10 3-1 SECTION 3 EMERGENCY PROCEDURES CESSNA MODEL 152 CESSNA MODEL 152 TABLE OF CONTENTS (Continued) Page Emergency Operation In Clouds (Vacuum System Failure) Executing A 180° Turn In Clouds 3-11 3-11 Emergency Descent Through Clouds 3-11 Recovery From A Spiral Dive 3-12 Flight In Icing Conditions 3-12 Spins 3-12 Rough Engine Operation Or Loss Of Power 3-13 Carburetor Icing 3-13 Spark Plug Fouling 3-13 Magneto Malfunction 3-14 Low Oil Pressure 3-14 Electrical Power Supply System Malfunctions 3-14 Excessive Rate Of Charge 3-14 3-2 Insufficient Rate Of Charge 3-15 SECTION 3 EMERGENCY PROCEDURES INTRODUCTION Section 3 provides checklist and amplified procedures for coping with emergencies that may occur. Emergencies caused by airplane or engine malfunctions are extremely rare if proper preflight inspections and maintenance are practiced. Enroute weather emergencies can be minim- ized or eliminated by careful flight planning and good judgment when unexpected weather is encountered. However, should an emergency arise, the basic guidelines described in this section should be considered and applied as necessary to correct the problem. Emergency procedures associated with ELT and other optional systems can be found in Section 9. AIRSPEEDS FOR EMERGENCY OPERATION Engine Failure After Takeoff Maneuvering Speed: 60 KIAS 1670 Lbs 1500 Lbs 1350 Lbs Maximum Glide Precautionary Landing With Engine Power Landing Without Engine Power: Wing Flaps Up Wing Flaps Down OPERATIONAL CHECKLISTS ENGINE FAILURES ENGINE FAILURE DURING TAKEOFF RUN 1. Throttle 2. -- IDLE. Brakes APPLY. -- 3. Wing Flaps -- RETRACT. 4. Mixture --> IDLE CUT-OFF. 5. Ignition Switch OFF. 6. -- Master Switch -- OFF. ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1. Airspeed 60 KIAS. 2. Mixture -- IDLE CUT-OFF. 104 KIAS 98 KIAS 93 KIAS 60 KIAS 55 KIAS 65 KIAS 60 KIAS 3-3 SECTION 3 EMERGENCY PROCEDURES 3. Fuel Shutoff Valve 4. 5. 6. -- OFF. Ignition Switch -- OFF. Wing Flaps -- AS REQUIRED. Master Switch -- OFF. ENGINE FAILURE DURING FLIGHT 1. Airspeed 60 KIAS. Carburetor Heat ON. -- Primer IN and LOCKED. Fuel Shutoff Valve -- ON. CESSNA MODEL 152 CESSNA MODEL 152 DITCHING SECTION 3 EMERGENCY PROCEDURES 1. Radio TRANSMIT MAYDAY on 121.5 MHz, giving location an* intentions. 2. 3. -- Heavy Objects (in baggage area) -- SECURE OR JETTISON. INTO THE WIND. Approach -- High Winds, Heavy Seas Light Winds, Heavy Swells -- PARALLEL TO SWELLS. Power ESTABLISH 300 FT/MIN DESCENT AT 55 KIAS. Cabin Doors UNLATCH. 4. Wing Flaps -- 30°. 2. 5. -- 3. 6. 4. 7. 5. Mixture RICH. -- 8. 6. Ignition Switch -- BOTH (or START if propeller is stopped). 9. FORCED LANDINGS EMERGENCY LANDING WITHOUT ENGINE POWER 1. Airspeed -- 65 KIAS (flaps UP). 60 KIAS (flaps DOWN). Mixture IDLE CUT-OFF. Fuel Shutoff Valve -- OFF. Ignition Switch -- OFF. OFF. Wing Flaps AS REQUIRED (30° recommended). 2. 3. 4. 5. 6. 7. Doors -- 8. 9. Master Switch -- UNLATCH PRIOR TO TOUCHDOWN. Touchdown -- SLIGHTLY TAIL LOW. Brakes APPLY HEAVILY. PRECAUTIONARY LANDING WITH ENGINE POWER -- 20°. Selected Field -- FLY OVER, noting terrain and obstructions, then retract flaps upon reaching a safe altitude and airspeed. 1. Airspeed - -- 60 KIAS. 2. Wing Flaps 3. 4. Radio and Electrical Switches -- OFF. 5. Wing Flaps -- 30° (on final approach). -- OFF. -- 6. Airspeed -- 55 KIAS. 7. Master Switch Doors UNLATCH PRIOR TO TOUCHDOWN. Touchdown -- SLIGHTLY TAIL LOW. -- OFF. APPLY HEAVILY. 8. 9. 10. Ignition Switch 11. Brakes 10. Touchdown LEVEL ATTITUDE AT 300 FT/MIN DESCENT. Face CUSHION at touchdown with folded coat. -- Airplane EVACUATE through cabin doors. If necessary, open windows and flood cabin to equalize pressure so doors can be opened. Life Vests and Raft INFLATE. FIRES -- DURING START ON GROUND 1. Cranking CONTINUE, to get a start which would suck the flames and accumulated fuel through the carburetor and into the engine. If engine starts: 2. Power 1700 RPM for a few minutes. -- 3. Engine -- SHUTDOWN and inspect for damage. If engine fails to start: 4. 5. Cranking CONTINUE in an effort to obtain a start. -- Fire Extinguisher -- OBTAIN (have ground attendants obtain if not installed). 6. Engine -- SECURE. a. -- Master Switch OFF. b. Ignition Switch OFF. OFF. Fuel Shutoff Valve -- C. 7. -- -- Fire EXTINGUISH using fire extinguisher, wool blanket, or dirt. 8. Fire Damage INSPECT, repair damage or replace damaged components or wiring before conducting another flight. -- ENGINE FIRE IN FLIGHT 1. Mixture -- IDLE CUT-OFF. 3-4 3-5 SECTION 3 EMERGENCY PROCEDURES 2. Fuel Shutoff Valve -- OFF. 3. Master Switch -- OFF. 4. Cabin Heat and Air CESSNA MODEL 152 CESSNA MODEL 152 5. €6. OFF (except wing root vents). Airspeed 85 KIAS (If fire is not extinguished, increase glide speed to find an airspeed which will provide an incombustible mixture). Forced Landing -- EXECUTE (as described in Emergency Landing Without Engine Power). ELECTRICAL FIRE IN FLIGHT SECTION 3 EMERGENCY PROCEDURES WING FIRE 1. Navigation Light Switch OFF. 2. 3. Strobe Light Switch (if installed) -- OFF. Pitot Heat Switch (if installed) -- OFF. NOTE Perform a side slip to keep the flames away from the fuel tank and cabin, and land as soon as possible, with flaps retracted. 1. 2. 3. 4. Master Switch -- OFF. All Other Switches (except ignition switch) -- OFF. Vents/Cabin Air/Heat -- CLOSED. Fire Extinguisher -- ACTIVATE (if available). WARNING After discharging an extinguisher within a closed cabin, ventilate the cabin. If fire appears out and electrical power is necessary for continuance of flight: -- -- CHECK for faulty circuit, do not reset. Radio/Electrical Switches ICING INADVERTENT ICING ENCOUNTER 1. Turn pitot heat switch ON (if installed). 2. 3. Turn back or change altitude to obtain an outside air temperature that is less conducive to icing. Pull cabin heat control full out to obtain maximum defroster air temperature. For greater air flow at reduced temperatures, adjust the cabin air control as required. 4. Open the throttle to increase engine speed and minimize ice build- up on propeller blades. 5. Master Switch ON. 6. Circuit Breakers 7. -- 8. -- ON one at a time, with delay after each until short circuit is localized. Vents/Cabin Air/Heat completely extinguished. 5. OPEN when it is ascertained that fire is 6. 7. CABIN FIRE 1. Master Switch -- OFF. 2. -- CLOSED (to avoid drafts). Vents/Cabin Air/Heat 3. Fire Extinguisher -- ACTIVATE (if available). WARNING After discharging an extinguisher within a closed cabin, ventilate the cabin. 8. 9. 10. Watch for signs of carburetor air filter ice and apply carburetor heat as required. An unexpected loss in engine speed could be caused by carburetor ice or air intake filter ice. Lean the mixture for maximum RPM, if carburetor heat is used continuously. Plan a landing at the nearest airport. With an extremely rapid ice build-up, select a suitable “off airport" landing site. With an ice accumulation of 1/4 inch or more on the wing leading edges, be prepared for significantly higher stall speed. Leave wing flaps retracted. With a severe ice build-up on the horizontal tail, the change in wing wake airflow direction caused by wing flap extension could result in a loss of elevator effective- ness. Open left window and, if practical, scrape ice from a portion of the windshield for visibility in the landing approach. Perform a landing approach using a forward slip, if necessary, for improved visibility. 11. Approach at 65 to 75 KIAS depending upon the amount of ice accumulation. 3-6 4. Land the airplane as soon as possible to inspect for damage. 12. Perform a landing in level attitude. 3-7