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Weightandbalance
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- 3. 33 Lesson ObjectivesLesson Objectives Atthe conclusion of this lesson you will…At the conclusion of this lesson you will… Understand why weight and balance is criticalUnderstand why weight and balance is critical to safety of flightto safety of flight Be familiar with the terms associated withBe familiar with the terms associated with weight and balanceweight and balance Be familiar with the methods of calculatingBe familiar with the methods of calculating weight and balanceweight and balance Understand the effect weight and balance hasUnderstand the effect weight and balance has on aircraft performanceon aircraft performance
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- 5. 55 Importance of WeightandImportance of Weight and BalanceBalance Aircraft are designed to be operatedAircraft are designed to be operated within specific Center of Gravity limits.within specific Center of Gravity limits. Wings can only produce so much lift.Wings can only produce so much lift. Weight in excess of what the wing isWeight in excess of what the wing is designed to carry is hazardous.designed to carry is hazardous. Increases in weight also effect theIncreases in weight also effect the general performance.general performance.
- 6. 66 Weight TermsWeight Terms Empty AircraftEmpty Aircraft Standard Empty Weight – weight of aStandard Empty Weight – weight of a standard airplane including unusable fuel, fullstandard airplane including unusable fuel, full operating fluids and full oiloperating fluids and full oil Basic Empty WeightBasic Empty Weight – Standard Empty– Standard Empty Weight plus optional equipmentWeight plus optional equipment • Starting Point of Weight and BalanceStarting Point of Weight and Balance
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- 8. 88 Weight TermsWeight Terms FuelFuel Usable Fuel – fuel which can be used for flightUsable Fuel – fuel which can be used for flight planningplanning Unusable Fuel – fuel which cannot be use inUnusable Fuel – fuel which cannot be use in flight due to fuel tank designflight due to fuel tank design 6 lbs per gallon6 lbs per gallon
- 9. 99 Weight TermsWeight Terms Useful Load – total usable fuel,Useful Load – total usable fuel, passengers, and cargopassengers, and cargo Maximum Ramp Weight – Basic Empty Weight = Useful LoadMaximum Ramp Weight – Basic Empty Weight = Useful Load Payload – passengers and cargoPayload – passengers and cargo What essentially could be revenue generatingWhat essentially could be revenue generating
- 10. 1010 Weight TermsWeight Terms Loaded AircraftLoaded Aircraft Maximum Ramp WeightMaximum Ramp Weight • Maximum allowable mass for ground operationsMaximum allowable mass for ground operations • Assures ground maneuverabilityAssures ground maneuverability • Includes fuel for taxi, run-up and startIncludes fuel for taxi, run-up and start Maximum Takeoff WeightMaximum Takeoff Weight • Maximum allowable mass for initiation of takeoff rollMaximum allowable mass for initiation of takeoff roll • Failure to meet weight…Failure to meet weight… Maximum Landing WeightMaximum Landing Weight • Maximum allowable mass at touchdownMaximum allowable mass at touchdown • Generally limitation of landing gearGenerally limitation of landing gear Baggage Compartment LimitsBaggage Compartment Limits • Could cause structural failure in floorCould cause structural failure in floor
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- 12. 1212 Balance TermsBalance Terms WeightWeight Force that acts straight down to the center ofForce that acts straight down to the center of the Earththe Earth Not always constantNot always constant • Decreases with fuel burnDecreases with fuel burn
- 13. 1313 Balance TermsBalance Terms Reference DatumReference Datum Reference base for location of componentsReference base for location of components Imaginary vertical planeImaginary vertical plane Location specified from manufacturerLocation specified from manufacturer Lies on longitudinal axisLies on longitudinal axis Ex. 78.4 inches from wing leading edgeEx. 78.4 inches from wing leading edge
- 14. 1414 Balance TermsBalance Terms ArmArm Distance from the datum measured along theDistance from the datum measured along the longitudinal axislongitudinal axis • If located in front of datum, negativeIf located in front of datum, negative • If located in back of datum, positiveIf located in back of datum, positive
- 15. 1515 Balance TermsBalance Terms MomentMoment Weight multiplied by its armWeight multiplied by its arm Tendency of a mass to cause a rotation aboutTendency of a mass to cause a rotation about the Center of Gravitythe Center of Gravity Force acting at that pointForce acting at that point
- 16. 1616 Balance TermsBalance Terms Center of Gravity (CG)Center of Gravity (CG) Point of a mass through which gravity actsPoint of a mass through which gravity acts Point where aircraft would balance ifPoint where aircraft would balance if suspendedsuspended Point where all three axis interceptPoint where all three axis intercept Divide total moment of aircraft by weight ofDivide total moment of aircraft by weight of aircraftaircraft
- 17. 1717 Basic W&B RelationshipsBasicW&B Relationships For the next few examples…For the next few examples… • The seesaw is synonymous with the aircraft.The seesaw is synonymous with the aircraft. • The people are synonymous with the weight of fuel,The people are synonymous with the weight of fuel, equipment, passengers, etc…equipment, passengers, etc… • The fulcrum can be thought of as lift, supporting theThe fulcrum can be thought of as lift, supporting the entire mass.entire mass. • The datum can be considered the nose of the aircraft.The datum can be considered the nose of the aircraft.
- 18. 1818 Basic W&B MathBasicW&B Math Moment = Weight X ArmMoment = Weight X Arm Center of Gravity =Center of Gravity = Basic Empty WeightBasic Empty Weight + Payload+ Payload + Usable Fuel+ Usable Fuel =Ramp Weight=Ramp Weight - Fuel used for start, taxi and run-up- Fuel used for start, taxi and run-up = Takeoff Weight= Takeoff Weight - Fuel used for flight- Fuel used for flight = Landing Weight= Landing Weight Sum of All Moments Gross Weight
- 19. 1919 Basic W&B RelationshipsBasicW&B Relationships Balanced ConditionBalanced Condition
- 20. 2020 Basic W&B RelationshipsBasicW&B Relationships Unbalanced ConditionUnbalanced Condition
- 21. 2121 Basic W&B RelationshipsBasicW&B Relationships Forces Acting on an Aircraft in FlightForces Acting on an Aircraft in Flight www.aero.und.eduwww.aero.und.edu/multimedia/multimedia Center of GravityCenter of Gravity forward of Center offorward of Center of PressurePressure Downward forceDownward force produced at tail toproduced at tail to stabilize interactionstabilize interaction of lift and weightof lift and weight
- 22. 2222 Basic W&B RelationshipsBasicW&B Relationships Center of Gravity LimitsCenter of Gravity Limits
- 23. 2323 Results of AircraftOverloadingResults of Aircraft Overloading Stall SpeedStall Speed IncreasesIncreases Takeoff and Landing DistanceTakeoff and Landing Distance IncreasesIncreases Climb RateClimb Rate ReducedReduced Cruise SpeedCruise Speed ReducedReduced Fuel ConsumptionFuel Consumption GreaterGreater Range and EnduranceRange and Endurance ReducedReduced StabilityStability IncreasedIncreased
- 24. 2424 Results of aForward CGResults of a Forward CG Longitudinal Stability becomes excessiveLongitudinal Stability becomes excessive Rotation and Flare are more difficultRotation and Flare are more difficult Takeoff RollTakeoff Roll IncreasedIncreased Cruise SpeedCruise Speed DecreasedDecreased A greater tail down force must be produced. This is doneA greater tail down force must be produced. This is done aerodynamically, increasing drag.aerodynamically, increasing drag. Climb RateClimb Rate ReducedReduced Range and EnduranceRange and Endurance ReducedReduced Stall SpeedStall Speed IncreasedIncreased
- 25. 2525 Effects of anAft CGEffects of an Aft CG Longitudinally StabilityLongitudinally Stability ReducedReduced Takeoff RollTakeoff Roll ReducedReduced Tendency to Over-RotateTendency to Over-Rotate Landing RollLanding Roll ReducedReduced Tendency to Over-FlareTendency to Over-Flare Cruise SpeedsCruise Speeds IncreasedIncreased Less tail down force, is less dragLess tail down force, is less drag Climb RatesClimb Rates IncreasedIncreased Fuel ConsumptionFuel Consumption DecreasedDecreased Range and EnduranceRange and Endurance IncreasedIncreased Stall SpeedsStall Speeds ReducedReduced Recovery hindered due to nose up tendencyRecovery hindered due to nose up tendency
- 26. Weight and BalanceWeightand Balance DocumentationDocumentation
- 27. 2727 POH Section 6POHSection 6 Section 6 contains…Section 6 contains… Weight and Balance Calculation procedure forWeight and Balance Calculation procedure for the aircraftthe aircraft Basic Empty Weight and Moment of theBasic Empty Weight and Moment of the aircraftaircraft Changes to the Weight and BalanceChanges to the Weight and Balance
- 28. 2828 Equipment ListEquipment List Contains all of the equipment installed inContains all of the equipment installed in the aircraft, its location, and it’s weightthe aircraft, its location, and it’s weight Format of Equipment Lists may varyFormat of Equipment Lists may vary Located in the back of the POHLocated in the back of the POH
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- 30. 3030 Weight &Weight & Balance-Balance - Equipment ListEquipment List RevisionRevision CENTER FOR AEROSPACE SCIENCES UNIVERSITY OF NORTH DAKOTA WEIGHT AND BALANCE, AND EQUIPMENT LIST REVISION AIRCRAFT MODEL N SERIAL NO. DATE AMOUNT NAME CERTIFICATE NO. E.W. PREVIOUS EMPTYAIRPLANE TOTAL ADDED OR SUBTRACTED REVISED EMPTYAIRPLANE USEFUL LOAD DESCRIPTION WEIGHT (LB) ARM (IN) MOMENT C.G. MOMENT Jim Gilstad OGSR092N PA 28-161 142 ND 2841229 5-1-94 1 Fire Extinguisher +2.7 57.9 +156 1464.4 +2.7 1467.1 85.0 804.9 85.0 124469.5 +156.0 124625.5
- 31. 3131 Weight & Balance-Weight & Balance - Equipment List RevisionEquipment List Revision NAME CERTIFICATE NO. E.W. C.G. MOMENT PREVIOUS EMPTY AIRPLANE TOTALADDED OR SUBTRACTED REVISED EMPTY AIRPLANE USEFUL LOAD Jim Gilstad OGSR092N 1464.4 +2.7 1467.1 85.0 804.9 85.0 124469.5 +156.0 124625.5
- 32. 3232 CENTER FORAEROSPACE SCIENCES UNIVERSITYOF NORTH DAKOTA WEIGHTAND BALANCE,AND EQUIPMENTLIST REVISION AIRCRAFTMODEL N SERIAL NO. DATE AMOUNT NAME CERTIFICATE NO. E.W. PREVIOUS EMPTYAIRPLANE TOTALADDED OR SUBTRACTED REVISED EMPTYAIRPLANE USEFUL LOAD DESCRIPTION WEIGHT (LB) ARM (IN) MOMENT C.G. MOMENT JimGilstad OGSR092N PA 28-161 142 ND 2841229 5-1-94 1 Fire Extinguisher -2.7 57.9 -156 1467.1 -2.7 1464.4 84.9 867.6 1 124625.5 -156.0 124469.5 SUPERCEDED 5-1-94 Weight &Weight & Balance -Balance - Equipment ListEquipment List RevisionRevision
- 33. Weight and BalanceWeightand Balance CalculationCalculation
- 34. 3434 Weight & BalanceWeight& Balance ComputationsComputations Weight and balance informationWeight and balance information Weight and balance formulasWeight and balance formulas Weight shift formulasWeight shift formulas Weight and balance problem set upWeight and balance problem set up
- 35. 3535 Weight & BalanceWeight& Balance ComputationsComputations Weight Shift FormulasWeight Shift Formulas
- 36. 3636 Miscellaneous W&B SolutionsMiscellaneousW&B Solutions Weight ShiftWeight Shift Weight to be MovedWeight to be Moved Distance CG MovesDistance CG Moves Gross Weight Distance Weight Moves Weight Addition / DeletionWeight Addition / Deletion Weight to be Added/RemovedWeight to be Added/Removed Distance CG MovesDistance CG Moves New Aircraft Gross Weight Distance Weight Moves = =
- 37. 3737 Weight & BalanceProblemWeight & Balance Problem Set UpSet Up Computation - - Piper WarriorComputation - - Piper Warrior Computation - - Cessna P210Computation - - Cessna P210 Graph - - Piper ArrowGraph - - Piper Arrow Table - - Beech B33 DebonairTable - - Beech B33 Debonair
- 38. 3838 Computation MethodComputation Method This method uses the basic weight andThis method uses the basic weight and balance formula to determine center ofbalance formula to determine center of gravity.gravity. This method can be used for most aircraft.This method can be used for most aircraft. Extremely accurate, less arithmetic errors.Extremely accurate, less arithmetic errors.
- 39. 3939 Computation MethodComputation Method ProcedureProcedure 1.1. Determine the Basic Empty Weight of theDetermine the Basic Empty Weight of the aircraft.aircraft. 2.2. Find the moment of each weight to beFind the moment of each weight to be carried.carried. 3.3. Add all moments and all weights.Add all moments and all weights. 4.4. Divide the total moment by the total weight.Divide the total moment by the total weight. This number is your Center of GravityThis number is your Center of Gravity 5.5. Compare this number to the CG limits for theCompare this number to the CG limits for the aircraft.aircraft.
- 40. 4040 Weight & Balance-Weight & Balance - Piper WarriorPiper Warrior For our firstFor our first problem, weproblem, we use a weightuse a weight and balanceand balance form for aform for a PiperPiper Warrior.Warrior.
- 41. 4141 Step 1Step 1 findthe zero fuel conditionfind the zero fuel condition Weight & Balance -Weight & Balance - Piper WarriorPiper Warrior
- 42. 4242 Piper WarriorPiper Warrior WeightArm MomentWeight Arm Moment (lbs.) (in.) (lbs.-(lbs.) (in.) (lbs.- in.)in.) Basic Empty WeightBasic Empty Weight 1,5001,500 128,850128,850
- 43. 4343 Piper WarriorPiper Warrior WeightArm MomentWeight Arm Moment (lbs.)(lbs.) (in.) (lbs.-in.)(in.) (lbs.-in.) Basic Empty WeightBasic Empty Weight 1,5001,500 128,850128,850 Pilot, Front Passengers 340Pilot, Front Passengers 340 80.5 27,37080.5 27,370 Rear PassengersRear Passengers 340340 118.1 40,154118.1 40,154
- 44. 4444 Piper WarriorPiper Warrior WeightArm MomentWeight Arm Moment (lbs.)(lbs.) (in.) (lbs.-in.)(in.) (lbs.-in.) Basic Empty WeightBasic Empty Weight 1,5001,500 128,850128,850 Pilot, Front Passengers 340Pilot, Front Passengers 340 80.5 27,37080.5 27,370 Rear PassengersRear Passengers 340340 118.1 40,154118.1 40,154 Baggage (200 lb. Max)Baggage (200 lb. Max) Zero Fuel ConditionZero Fuel Condition 2,1802,180 196,374196,374
- 45. 4545 Step 2Step 2 findthe ramp condition andfind the ramp condition and takeoff conditiontakeoff condition determine that it is within limitsdetermine that it is within limits Weight & Balance -Weight & Balance - Piper WarriorPiper Warrior
- 46. 4646 Piper WarriorPiper Warrior WeightWeightArmArm MomentMoment (lbs.)(lbs.) (in.)(in.) (lbs.-in.)(lbs.-in.) Zero Fuel ConditionZero Fuel Condition 2,1802,180 196,374196,374 Fuel (48 gallons max)Fuel (48 gallons max) 267267 9595 25,36525,365 Ramp ConditionRamp Condition 2,4472,447 221,739221,739 Taxi, start, runup fuelTaxi, start, runup fuel - 7- 7 9595 - 665- 665 Takeoff conditionTakeoff condition 2,4402,440 90.6 221,07490.6 221,074
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- 48. 4848 Step 3Step 3 findthe landing conditionfind the landing condition Weight & Balance -Weight & Balance - Piper WarriorPiper Warrior
- 49. 4949 Piper WarriorPiper Warrior WeightWeightArmArm MomentMoment (lbs.)(lbs.) (in.)(in.) (lbs.-(lbs.- in.)in.) Takeoff conditionTakeoff condition 2,440 90.6 221,0742,440 90.6 221,074 Cruise fuel (30 gallons) -180Cruise fuel (30 gallons) -180 95.0 -17,10095.0 -17,100 Landing conditionLanding condition 2,2602,260 90.2590.25 203,974203,974
- 50. 5050 Step 4Step 4 confirmthat landing weight & C.G. fallconfirm that landing weight & C.G. fall within limitswithin limits Weight & Balance -Weight & Balance - Piper WarriorPiper Warrior
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- 52. 5252 Weight & Balance- CessnaWeight & Balance - Cessna P210P210 Computation Method
- 53. 5353 Cessna P210Cessna P210 BEW: 2,632 lbs. (Moment 109,000)BEW: 2,632 lbs. (Moment 109,000) Front Seat (170 lbs.)Front Seat (170 lbs.) Center Seat (160 and 150 lbs)Center Seat (160 and 150 lbs) Aft Seat (200 and 170 lbs)Aft Seat (200 and 170 lbs) Baggage Area A (150 lbs)Baggage Area A (150 lbs) Baggage Area B (0)Baggage Area B (0)
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- 55. 5555 Zero Fuel ConditionZeroFuel Condition ItemItem WeightWeight ArmArm MomentMoment BEWBEW 26322632 109000109000 Front SeatFront Seat 170170 3737 62906290 Center SeatCenter Seat 310310 7171 2201022010 Aft SeatAft Seat 370370 102102 3774037740 Baggage ABaggage A 150150 138138 2070020700 Zero-FuelZero-Fuel 36323632 53.8953.89 195740195740
- 56. 5656 Ramp ConditionRamp Condition Add 64 gallons of fuelAdd 64 gallons of fuel ItemItem WeightWeight ArmArm MomentMoment Zero-FuelZero-Fuel 36323632 53.8953.89 195740195740 FuelFuel 384384 4343 1651216512 Ramp WeightRamp Weight 40164016 52.8552.85 212252212252
- 57. 5757 Takeoff ConditionTakeoff Condition Run-up minus 16 lbs of fuelRun-up minus 16 lbs of fuel ItemItem WeightWeight ArmArm MomentMoment Ramp WeightRamp Weight 40164016 52.8552.85 212252212252 Run-upRun-up -16-16 4343 -688-688 TakeoffTakeoff 40004000 52.8952.89 211564211564
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- 60. 6060 Shift a PassengerShifta Passenger Move the 200 pound passenger from theMove the 200 pound passenger from the aft seat to the front seat.aft seat to the front seat. EquationEquation Weight MovedWeight Moved Distance CG MovesDistance CG Moves Total WeightTotal Weight Distance between CG LocationDistance between CG Location
- 61. 6161 Weight MovedWeight MovedDistance CG MovesDistance CG Moves Total WeightTotal Weight Distance between CG LocationDistance between CG Location 200 lbs200 lbs ?????????????????????????????????????? 4000 lbs4000 lbs (102-37) 65’(102-37) 65’ (65 x 200)/4000(65 x 200)/4000 13000/4000 = 3.2513000/4000 = 3.25 52.89 – 3.25 = 49.6452.89 – 3.25 = 49.64
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- 63. 6363 Fuel BurnFuel Burn 2.5 hour flight at 20 gallons per hour2.5 hour flight at 20 gallons per hour ItemItem WeightWeight ArmArm MomentMoment TakeoffTakeoff 40004000 49.6449.64 198560198560 Fuel BurnFuel Burn (2.5 x 20 x 6)(2.5 x 20 x 6) -300-300 4343 -12900-12900 LandingLanding 37003700 50.1850.18 185660185660
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- 65. 6565 ExampleExample BEWBEW 26322632109000109000 Front SeatFront Seat 150 + 210150 + 210 Center SeatCenter Seat 190190 Aft SeatAft Seat 150 + 190150 + 190 Baggage ABaggage A 1010 Baggage BBaggage B 2525
- 66. 6666 Chart MethodChart Method This method depends on charts provided by theThis method depends on charts provided by the manufacturer to determine the moments.manufacturer to determine the moments. Accuracy of the chart method tends to decreaseAccuracy of the chart method tends to decrease as the size of the aircraft increases.as the size of the aircraft increases. Accuracy in general is generally within a fewAccuracy in general is generally within a few hundred pound – inches.hundred pound – inches. The procedure may vary from aircraft to aircraft.The procedure may vary from aircraft to aircraft.
- 67. 6767 Chart MethodChart Method Procedure (General)Procedure (General) 1.1. Find the charts provided by the manufacturerFind the charts provided by the manufacturer in Section 6 of the POH. (These may or mayin Section 6 of the POH. (These may or may not be provided)not be provided) 2.2. Correlate the weights to the appropriateCorrelate the weights to the appropriate chart to determine the moment.chart to determine the moment. 3.3. Add the moments determined from theAdd the moments determined from the charts and correlate them to the CG Limitcharts and correlate them to the CG Limit chart.chart.
- 68. 6868 Weight & Balance-Weight & Balance - Piper ArrowPiper Arrow Graph MethodGraph Method
- 69. 6969 PA28-R-201 ARROWPA28-R-201 ARROW BEW - 1774.2 lbs. (moment 147,695.8)BEW - 1774.2 lbs. (moment 147,695.8) Pilot and Front Passenger - 370 lbs.Pilot and Front Passenger - 370 lbs. Rear passenger - 210 lbs.Rear passenger - 210 lbs. Baggage - 100 lbs.Baggage - 100 lbs.
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- 71. 7171 MomentMoment BEW -147,695.8BEW - 147,695.8 Front Seat - 30,000Front Seat - 30,000 Back Seat - 25,000Back Seat - 25,000 Baggage - 14,200Baggage - 14,200 ItemItem WeightWeight ArmArm MomentMoment BEWBEW 1774.21774.2 147695.8147695.8 Front Pas.Front Pas. 370370 3000030000 Rear Pas.Rear Pas. 210210 2500025000 BaggageBaggage 100100 1420014200 Zero FuelZero Fuel 2454.22454.2 88.3888.38 216895.8216895.8
- 72. 7272 Fuel (72gallon maximum)Fuel (72 gallon maximum) 50 gallons50 gallons • 300 lbs.300 lbs. • MomentMoment 2900029000
- 73. 7373 ItemItem WeightWeight ArmArmMomentMoment Zero FuelZero Fuel 2454.22454.2 88.3888.38 216895.8216895.8 FuelFuel 300300 2900029000 Ramp WeightRamp Weight 2754.22754.2 245895.8245895.8 Run-upRun-up -8-8 -1000-1000 TakeoffTakeoff 2746.22746.2 89.1789.17 244895.8244895.8
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- 75. 7575 Fuel usedin flightFuel used in flight 3 hours at 11.6 gallons per hour3 hours at 11.6 gallons per hour • 34.8 gallons34.8 gallons 208.8 lbs.208.8 lbs. Moment - 20,000Moment - 20,000
- 76. 7676 ItemItem WeightWeight ArmArmMomentMoment TakeoffTakeoff 2746.22746.2 89.1789.17 244895.8244895.8 FuelFuel -208.8-208.8 -20000-20000 LandingLanding 2537.42537.4 88.6388.63 224895.8224895.8
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- 78. 7878 Problem!Problem! BEWBEW 17741774147695147695 Front PaxFront Pax 400400 Rear PaxRear Pax 150150 FuelFuel 200200
- 79. Weight and BalanceWeightand Balance ComputationComputation Table MethodTable Method Beech DebonairBeech Debonair
- 80. 8080 Table MethodTable Method This method depends on tables provided by theThis method depends on tables provided by the manufacturer.manufacturer. Moment data is provided for specific weightsMoment data is provided for specific weights only.only. Interpolation will be necessary to determineInterpolation will be necessary to determine weights not specifically listed.weights not specifically listed. Accuracy is generally within a few hundredAccuracy is generally within a few hundred pound – inches.pound – inches. This procedure may vary from aircraft to aircraft.This procedure may vary from aircraft to aircraft.
- 81. 8181 Table MethodTable Method ProcedureProcedure 1.1. Find the tabular data provided in Section 6 ofFind the tabular data provided in Section 6 of the POH. (These may or may not bethe POH. (These may or may not be provided)provided) 2.2. Correlate the weight to the appropriate tablesCorrelate the weight to the appropriate tables to determine the moment.to determine the moment. 3.3. Add the moments determined from theAdd the moments determined from the tables and correlate them to the CG Limittables and correlate them to the CG Limit chart.chart.
- 82. 8282 Beech B33 DebonairBeechB33 Debonair BEW - 1980 lbs. (Moment 1584)BEW - 1980 lbs. (Moment 1584) Front Seat (Front Seat (Forward 170 lbs. and 200 lbs.)Forward 170 lbs. and 200 lbs.) Rear Seat (120 lbs. And 130 lbs)Rear Seat (120 lbs. And 130 lbs) Baggage (50 lbs.)Baggage (50 lbs.)
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- 86. 8686 CalculationsCalculations ItemItem WeightWeight ArmArmMomentMoment BEWBEW 19801980 15841584 Front PaxFront Pax 370370 314314 Rear PaxRear Pax 250250 295295 BaggageBaggage 5050 7070 Zero FuelZero Fuel 26502650 22632263
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- 88. 8888 Adding FuelAdding Fuel Fuel (64 gallons maximum)Fuel (64 gallons maximum) 60 gallons60 gallons • 360 lbs.360 lbs.
- 89. 8989 Ramp ConditionRamp Condition ItemItemWeightWeight ArmArm MomentMoment Zero FuelZero Fuel 26502650 22632263 FuelFuel 360360 270270 Ramp WeightRamp Weight 30103010 25332533 Run-upRun-up -10-10 -8-8 Takeoff WeightTakeoff Weight 30003000 25252525
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- 91. 9191 Fuel BurnFuel Burn 3 hour flight (14.7 gallons per hour)3 hour flight (14.7 gallons per hour) 44.1 gallons44.1 gallons 264 lbs.264 lbs.
- 92. 9292 Landing ConditionLanding Condition ItemItemWeightWeight ArmArm MomentMoment Takeoff WeightTakeoff Weight 30003000 25252525 Fuel flightFuel flight 264264 198198 LandingLanding WeightWeight 27362736 23272327
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- 94. 9494 Problem!!Problem!! BEWBEW 1980lbs. (Moment 1584)1980 lbs. (Moment 1584) Front Pax (Aft)Front Pax (Aft) 190 And190 And 160160 Rear PaxRear Pax 150150 BaggageBaggage 200200 30 gallons of fuel30 gallons of fuel