Weightandbalance

33
Lesson ObjectivesLesson Objectives
At the 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

55
Importance of Weight andImportance 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.

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

88
 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

99
 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

1010
 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

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

1313
 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

1414
 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

1515
 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

1616
 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

1717
Basic W&B RelationshipsBasic W&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.

1818
Basic W&B MathBasic W&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

1919
 Balanced ConditionBalanced Condition

2020
 Unbalanced ConditionUnbalanced Condition

2121
 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

2222
 Center of Gravity LimitsCenter of Gravity Limits

2323
Results of Aircraft OverloadingResults 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

2424
Results of a Forward 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

2525
Effects of an Aft 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

Weight and BalanceWeight and Balance
DocumentationDocumentation

2727
POH Section 6POH Section 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

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

2929
Equipment ListsEquipment Lists

3030
Weight &Weight &
Balance -Balance -
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

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

3232
CENTER FORAEROSPACE SCIENCES
UNIVERSITY OF 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 -
RevisionRevision

CalculationCalculation

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

3535
Weight & BalanceWeight & Balance
ComputationsComputations
Weight Shift FormulasWeight Shift Formulas

3636
Miscellaneous W&B SolutionsMiscellaneous W&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
=
=

3737
Weight & Balance ProblemWeight & 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

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.

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.

4040
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.

4141
Step 1Step 1

find the zero fuel conditionfind the zero fuel condition

4242
Weight Arm MomentWeight Arm Moment
(lbs.) (in.) (lbs.-(lbs.) (in.) (lbs.-
in.)in.)
Basic Empty WeightBasic Empty Weight 1,5001,500
128,850128,850

4343
(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

4444
(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

4545
Step 2Step 2

find the ramp condition andfind the ramp condition and
takeoff conditiontakeoff condition

determine that it is within limitsdetermine that it is within limits

4646
WeightWeight ArmArm 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

4848
Step 3Step 3

find the landing conditionfind the landing condition

4949
WeightWeight ArmArm
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

5050
Step 4Step 4

confirm that landing weight & C.G. fallconfirm that landing weight & C.G. fall
within limitswithin limits

5252
Weight & Balance - CessnaWeight & Balance - Cessna
P210P210
Computation
Method

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)

5555
Zero Fuel ConditionZero Fuel 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

5656
Ramp ConditionRamp Condition
 Add 64 gallons of fuelAdd 64 gallons of fuel
Zero-FuelZero-Fuel 36323632 53.8953.89 195740195740
FuelFuel 384384 4343 1651216512
Ramp WeightRamp Weight 40164016 52.8552.85 212252212252

5757
Takeoff ConditionTakeoff Condition
 Run-up minus 16 lbs of fuelRun-up minus 16 lbs of fuel
Ramp WeightRamp Weight 40164016 52.8552.85 212252212252
Run-upRun-up -16-16 4343 -688-688
TakeoffTakeoff 40004000 52.8952.89 211564211564

6060
Shift a PassengerShift a 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

6161

Weight MovedWeight Moved Distance 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

6363
Fuel BurnFuel Burn
 2.5 hour flight at 20 gallons per hour2.5 hour flight at 20 gallons per hour
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

6565
ExampleExample
 BEWBEW 26322632 109000109000
 Front SeatFront Seat 150 + 210150 + 210
 Center SeatCenter Seat 190190
 Aft SeatAft Seat 150 + 190150 + 190
 Baggage ABaggage A 1010
 Baggage BBaggage B 2525

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.

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.

6868
Piper ArrowPiper Arrow
 Graph MethodGraph Method

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.

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
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

7272
 Fuel (72 gallon maximum)Fuel (72 gallon maximum)

50 gallons50 gallons
• 300 lbs.300 lbs.
• MomentMoment

2900029000

7373
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

7575
 Fuel used in 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

7676
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

7878
Problem!Problem!
 BEWBEW 17741774 147695147695
 Front PaxFront Pax 400400
 Rear PaxRear Pax 150150
 FuelFuel 200200

ComputationComputation
Table MethodTable Method
Beech DebonairBeech Debonair

8080
 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.

8181
 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.

8282
Beech B33 DebonairBeech B33 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.)

8686
CalculationsCalculations
BEWBEW 19801980 15841584
Front PaxFront Pax 370370 314314
Rear PaxRear Pax 250250 295295
BaggageBaggage 5050 7070
Zero FuelZero Fuel 26502650 22632263

8888
Adding FuelAdding Fuel
 Fuel (64 gallons maximum)Fuel (64 gallons maximum)

60 gallons60 gallons
• 360 lbs.360 lbs.

8989
Ramp ConditionRamp Condition
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

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.

9292
Landing ConditionLanding Condition
Takeoff WeightTakeoff Weight 30003000 25252525
Fuel flightFuel flight 264264 198198
LandingLanding
WeightWeight
27362736 23272327

9494
Problem!!Problem!!
 BEWBEW 1980 lbs. (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

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