Weight & Balance for 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: 7. Wing span shown with conical camber wing tips and strobe lights installed. standard wing tips without strobe light are installed, wing span is 32' 8%". 2. Maximum height shown with nose gear depressed, all tires and nose strut prop erly inflated and flashing beacon in- stalled. DESCRIPTIVE DATA 3. Wheel base length is 58". 4 Propeller ground clearance is 12". 5. Wing area is 157 square feet. ENGINE 6. to outboard wing tip) is 24' 8". * Minimuni turning radius (* pivot point Number of Engines: 1. PIVOT POINT Engine Manufacturer: Avco Lycoming. Engine Model Number: 0-235-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. * PIVOT POINT 0 0 33'-4' 5'-9"MAX. Οι 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'-7¾". 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 CESSN MODEL A15 CESSNA MODEL A152 SECTION 1 GENERAL Fuel Capacity: Standard Tanks: OIL 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 Grade (Specification): MIL-L-6082 Aviation Grade Straight Mineral Oil: Use to replenis 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 of 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 firs 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: 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 The maximum combined weight capacity for baggage areas 1 and 2 is 120 lbs. STANDARD AIRPLANE WEIGHTS Standard Empty Weight: 1125 lbs. Maximum Useful Load: 545 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). 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. 1-4 1-5 SECTION 1 GENERAL CESSN MODEL A1 CESSNA MODEL A152 SECTION 1 GENERAL KIAS Knots Indicated Airspeed is the speed shown on the ENGINE POWER TERMINOLOGY airspeed indicator and expressed in knots. KTAS Knots True Airspeed is the airspeed expressed in knot relative to undisturbed air which is KCAS corrected fo altitude and temperature. BHP RPM V A Manuevering Speed is the maximum speed at which yo may use abrupt control travel. Static RPM V. FE V. NO V. NE 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. Maximum Flap Extended Speed is the highest speed AIRPLANE PERFORMANCE AND FLIGHT PLANNING permissible with wing flaps in a prescribed extende TERMINOLOGY position. Demon- Maximum Structural Cruising Speed is the speed that strated should not be exceeded except in smooth air, then only with Crosswind caution. Velocity Never Exceed Speed is the speed limit that may not be exceeded at any time. Usable Fuel GPH V S Stalling Speed or the minimum steady flight speed which the airplane is controllable. Unusable Fuel Stalling Speed or the minimum steady flight speed 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. V. Vx Vy METEOROLOGICAL TERMINOLOGY OAT 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 Outside Air Temperature is the free air static temperature Reference It is expressed in either degrees Celsius (formerly Datum Centigrade) or degrees Fahrenheit. Standard Temperature is 15°C at sea level pressure Station altitude and decreases by 2°C for each 1000 feet of altitude.] Standard Tempera- ture 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 SECTION 1 GENERAL 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 Maximum Landing Weight Tare CESSN MODEL A1 CESSNA MODEL A152 SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS by its arm. (Moment divided by the constant 1000 is used this handbook to simplify balance calculations by redu ing the number of digits.) Center of Gravity is the point at which an airplane, equipment, would balance if suspended. Its distance fro the reference datum is found by dividing the total momer by the total weight of the airplane. Center of Gravity Arm is the arm obtained by adding th airplane's individual moments and dividing the sum the total weight. Center of Gravity Limits are the extreme center of gravit locations within which the airplane must be operated at given weight. TABLE OF CONTENTS Introduction Airspeed Limitations Airspeed Indicator Markings Standard Empty Weight is the weight of a standar Power Plant Limitations airplane, including unusable fuel, full operating fluids an Power Plant Instrument Markings full engine oil. Basic Empty Weight is the standard empty weight plus th weight of optional equipment. Useful Load is the difference between takeoff weight and the basic empty weight. Weight Limits Page 2-3 2-3 2-4 2-4 2-5 2-5 2-5 2-6 Inverted Flight Limitations Engine Speed Limitations 2-6 2-6 Flap Extension Limitations 2-7 2-7 2-7 2-7 2-9 Center Of Gravity Limits Maneuver Limits Flight Load Factor Limits Kinds Of Operation Limits Gross (Loaded) Weight is the loaded weight of the airplane Fuel Limitations Maximum Takeoff Weight is the maximum weight ap proved 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 readings. Tare is deducted from the scale reading to obtain the actual (net) airplane weight. Placards 1-8 2-1/(2-2 blank) CESSNA MODEL A152 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. Your Cessna is certificated under FAA Type Certificate No. 3A19 as Cessna Model No. A152. AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in figure 2-1. SPEED KCAS KIAS REMARKS VNE Never Exceed Speed 168 172 Do not exceed this speed in any operation. VNO Maximum Structural 122 125 Cruising Speed VA Maneuvering Speed: 1670 Pounds 106 108 1500 Pounds 106 108 1350 Pounds 106 108 VFE Maximum Flap Extended 87 85 Speed Do not exceed this speed except in smooth air, and then only with caution. Do not make full or abrupt control movements above this speed. Do not exceed this speed with flaps down. Maximum Window Open 139 Speed 143 Do not exceed this speed with windows open. Figure 2-1. Airspeed Limitations 2-3 SECTION 2 LIMITATIONS AIRSPEED INDICATOR MARKINGS CESSN MODEL A1 CESSNA MODEL A152 SECTION 2 LIMITATIONS POWER PLANT INSTRUMENT MARKINGS Power plant instrument markings and their color code significance are shown in figure 2-3. Airspeed indicator markings and their color code significance shown in figure 2-2. MARKING KIAS VALUE OR RANGE SIGNIFICANCE White Arc 35 - 85 Green Arc 40 - 125 Yellow Arc 125-172 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 re- tracted. Upper limit is maximum structural cruising speed. Operations must be conducted with caution and only in smooth air. RED LINE INSTRUMENT MINIMUM LIMIT GREEN ARC NORMAL OPERATING RED LINE MAXIMUM LIMIT Tachometer 1900 - 2550 RPM 2550 RPM Oil Temperature 100° - 245°F 245°F Oil Pressure 25 psi 60 - 90 psi 100 psi Figure 2-3. Power Plant Instrument Markings Red Line 172 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. Propeller Manufacturer: McCauley Accessory Division. Propeller 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. 2-4 2-5 SECTION 2 LIMITATIONS CESSN MODEL A15 CESSNA MODEL A152 SECTION 2 LIMITATIONS MANEUVER LIMITS This airplane is certificated in the acrobatic category. The followin maneuvers are approved: MANEUVER Chandelles Lazy Eights RECOMMENDED ENTRY SPEE FLAP EXTENSION LIMITATIONS The use of flaps in the execution of approved aerobatic maneuvers is prohibited. 105 knot FLIGHT LOAD FACTOR LIMITS Steep Turns 105 knot 100 knot Stalls (Except Whip Stalls) Spins Use Slow Deceleration Use Slow Deceleratio 115 knot Loops Cuban Eights 130 knot Immelmanns 130 knot Aileron Rolls 115 knot 115 knot Barrel Rolls 80 knot Flight Load Factors: *Flaps Up: +6.0g, -3.0g *Flaps Down: +3.5g *The design load factors are 150% of the above, and in all cases, the structure meets or exceeds design loads. Snap Rolls Vertical Reversements INVERTED FLIGHT LIMITATIONS 80 knot KINDS OF OPERATION LIMITS During training operations, momentary negative g flight may some times be encountered. Since this will cause a slight amount of engine oilt be lost from the oil breather line, it is recommended that a minimum of quarts of oil be carried as a matter of good operating practice (actual minimum allowable is 4 quarts). Continuous inverted flight maneuver are not approved because the gravity fuel system and conventiona carburetor will not permit continuous engine operation in this negative condition. In addition, the loss of oil pressure (with a windmilling propeller) and a loss of a quart or more of oil through the breather could b harmful to the engine. ENGINE SPEED LIMITATIONS The fixed-pitch propeller installation, combined with high entry speeds required for some maneuvers, can result in engine overspeeds a higher power settings. To prevent the possibility of excessive engine wear or damage, the throttle setting should be reduced as required during maneuvering flight to prevent the engine speed from exceeding 2550 RPM A complete throttle reduction to the idle position at high speed wil never be needed during the execution of the approved maneuvers. Power off dives can produce undesirable engine/propeller roughness character istics at speeds above 130 knots. This condition should be avoided as much as practicable. 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 reference 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. 2-6 2-7 SECTION 2 LIMITATIONS CESSN MODEL A15 CESSNA MODEL A152 SECTION 2 LIMITATIONS 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). 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.) This airplane is approved in the acrobatic category and must be operated in compliance with the operating limitations as stated in the form of placards, markings and manuals. 2-8 MAXIMUMS MANEUVERING SPEED (IAS) 108 knots GROSS WEIGHT 1670 lbs FLIGHT LOAD FACTOR Flaps Up +6.0, -3.0 Flaps Down +3.5 Aerobatic maneuvers with flaps extended are prohibited. Inverted flight is prohibited. Baggage compartment and/or child's seat must not be occupied during aerobatics. THE FOLLOWING AEROBATIC MANEUVERS ARE APPROVED Maneuver Chandelles Steep Turns Barrel Rolls Snap Rolls Loops Vertical • Recm. Entry Speed 105 knots Reversements . 100 knots 115 knots 80 knots Maneuver Recm. Entry Speed Lazy Eights Spins . Aileron Rolls Immelmanns Cuban Eights 105 knots Slow Deceleration 115 knots 130 knots 115 knots 130 knots Stalls (Except 80 knots Whip Stalls) Slow Deceleration Abrupt use of controls prohibited above 108 knots. Altitude loss in a stall recovery - 160 feet. Flight into known icing conditions prohibited. This airplane is certified for the following flight operations as of date of original airworthi- ness certificate: DAY NIGHT - VFR - IFR 2-9 SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS CESSN MODEL A15 CESSNA MODEL A152 2. In the baggage compartment: 6. On door near window latch: 120 lbs. maximum baggage and/or auxiliary seat passenger. For additional loading instructions see Weight and Balance Data. DO NOT OPEN WINDOW ABOVE 143 KNOTS IAS 7. On the instrument panel near the altimeter: 3. Near fuel shutoff valve (standard tanks): SPIN RECOVERY FUEL - 24.5 GALS - ON-OFF 1. VERIFY AILERONS NEUTRAL AND THROTTLE CLOSED Near fuel shutoff valve (long range tanks): 2. APPLY FULL OPPOSITE RUDDER 3. MOVE CONTROL WHEEL BRISKLY FORWARD TO BREAK STALL FUEL - 37.5 GALS ON-OFF 4. NEUTRALIZE RUDDER AND RECOVER FROM DIVE 4. Near fuel tank filler cap (standard tanks): 2-10 5. 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 On front door posts: EMERGENCY DOOR RELEASE 1. UNLATCH DOOR 2. PULL "D" RING 2-11/(2-12 blank) CESSNA MODEL A152 SECTION 3 EMERGENCY PROCEDURES W 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 3-3 Engine Failure Immediately After Takeoff Engine Failure During Flight 3-3 3-4 Forced Landings 3-4 Emergency Landing Without Engine Power Precautionary Landing With Engine Power Ditching 3-4 3-4 3-4 Fires 3-5 During Start On Ground 3-5 Engine Fire In Flight 3-5 Electrical Fire In Flight 3-6 Icing Cabin Fire Wing Fire 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 Over-Voltage Light Illuminates Ammeter Shows Discharge • 3-8 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 TABLE OF CONTENTS (Continued) Emergency Operation In Clouds (Vacuum System Failure) Executing A 180° Turn In Clouds CESSN MODEL A15 CESSNA MODEL A152 SECTION 3 EMERGENCY PROCEDURES Page 3- 3-1 3-1 3-3 3-1 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 (At All Weights) Maximum Glide Precautionary Landing With Engine Power Landing Without Engine Power: Wing Flaps Up Wing Flaps Down 60 KIAS 108 KIAS 60 KIAS 55 KIAS 65 KIAS 60 KIAS Emergency Descent Through Clouds Recovery From A Spiral Dive Flight In Icing Conditions Spins Rough Engine Operation Or Loss Of Power Carburetor Icing Spark Plug Fouling Magneto Malfunction Low Oil Pressure 3-1 Electrical Power Supply System Malfunctions 3-1 Excessive Rate Of Charge 3-1 Insufficient Rate Of Charge 3-1 Bail-Out 3-1 3-2 OPERATIONAL CHECKLISTS ENGINE FAILURES ENGINE FAILURE DURING TAKEOFF RUN 1. Throttle -- · IDLE. 2. Brakes -- APPLY. 3. Wing Flaps 53 RETRACT. 4. Mixture -- IDLE CUT-OFF. 5. Ignition Switch -- OFF. -- OFF. 6. Master Switch ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1. Airspeed 60 KIAS. Mixture -- IDLE CUT-OFF. Fuel Shutoff Valve OFF. 2. 3. 4. Ignition Switch -- OFF. 3-3