Weight and Balance. 2 3 Lesson Objectives At the conclusion of this lesson you will… Understand why weight and balance is critical to safety of flight

Weight and Balance

2

33

Lesson ObjectivesLesson ObjectivesAt the conclusion of this lesson you will…At the conclusion of this lesson you will… Understand why weight and balance is critical Understand why weight and balance is critical

to safety of flightto safety of flight Be familiar with the terms associated with Be familiar with the terms associated with

weight and balanceweight and balance Be familiar with the methods of calculating Be familiar with the methods of calculating

weight and balanceweight and balance Understand the effect weight and balance has Understand the effect weight and balance has

on aircraft performanceon aircraft performance

4

55

Importance of Weight and Importance of Weight and BalanceBalance

Aircraft are designed to be operated Aircraft 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 is Weight in excess of what the wing is designed to carry is hazardous.designed to carry is hazardous.

Increases in weight also effect the Increases in weight also effect the general performance.general performance.

66

Weight TermsWeight Terms

Empty AircraftEmpty Aircraft– Standard Empty Weight – weight of a standard Standard Empty Weight – weight of a standard

airplane including unusable fuel, full operating airplane including unusable fuel, full operating fluids and full oilfluids and full oil

– Basic Empty WeightBasic Empty Weight – Standard Empty Weight – Standard Empty Weight plus optional equipmentplus optional equipment Starting Point of Weight and BalanceStarting Point of Weight and Balance

7

88


FuelFuel– Usable Fuel – fuel which can be used for flight Usable Fuel – fuel which can be used for flight

planningplanning– Unusable Fuel – fuel which cannot be use in Unusable 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

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

1010


Loaded AircraftLoaded Aircraft– Maximum Ramp Weight Maximum 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 Weight Maximum 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 Weight Maximum Landing Weight Maximum allowable mass at touchdownMaximum allowable mass at touchdown Generally limitation of landing gear Generally limitation of landing gear

– Baggage Compartment LimitsBaggage Compartment Limits Could cause structural failure in floorCould cause structural failure in floor

11

1212

Balance TermsBalance Terms

Weight Weight – Force that acts straight down to the center of Force 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 Datum Reference 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


Arm Arm – Distance from the datum measured along the Distance 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


Moment Moment – Weight multiplied by its armWeight multiplied by its arm– Tendency of a mass to cause a rotation about Tendency 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 if suspendedPoint where aircraft would balance if suspended– Point where all three axis interceptPoint where all three axis intercept– Divide total moment of aircraft by weight of Divide 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 the The 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

Basic W&B RelationshipsBasic W&B Relationships Balanced ConditionBalanced Condition

2020

Basic W&B RelationshipsBasic W&B Relationships 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 Gravity Center of Gravity forward of Center of forward of Center of PressurePressure

Downward force Downward force produced at tail to produced at tail to stabilize interaction stabilize interaction of lift and weightof lift and weight

http://www.aero.und.edu/multimedi

http://www.aero.und.edu/multimedi

2222


Center of Gravity LimitsCenter of Gravity Limits

2323

Results of Aircraft OverloadingResults of Aircraft Overloading

Stall Speed Stall Speed Increases Increases Takeoff and Landing Distance Takeoff and Landing Distance Increases Increases Climb Rate Climb Rate Reduced Reduced Cruise Speed Cruise Speed Reduced Reduced Fuel Consumption Fuel Consumption Greater Greater Range and Endurance Range and Endurance Reduced Reduced Stability Stability Increased Increased

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 Roll Takeoff Roll Increased Increased Cruise Speed Cruise Speed Decreased Decreased

– A greater tail down force must be produced. This is done A greater tail down force must be produced. This is done aerodynamically, increasing drag.aerodynamically, increasing drag.

Climb Rate Climb Rate Reduced Reduced Range and Endurance Range and Endurance Reduced Reduced Stall Speed Stall Speed Increased Increased

2525

Effects of an Aft CGEffects of an Aft CG

Takeoff Roll Takeoff Roll Reduced Reduced– Tendency to Over-RotateTendency to Over-Rotate

Cruise Speeds Cruise Speeds Increased Increased– Less tail down force, is less dragLess tail down force, is less drag

Climb Rates Climb Rates Increased Increased Fuel Consumption Fuel Consumption Decreased Decreased Range and Endurance Range and Endurance Increased Increased Stall Speeds Stall Speeds Reduced Reduced

– Recovery hindered due to nose up tendencyRecovery hindered due to nose up tendency

Weight and Balance Weight and Balance DocumentationDocumentation

2727

POH Section 6POH Section 6

Section 6 contains…Section 6 contains…– Weight and Balance Calculation procedure for Weight and Balance Calculation procedure for

the aircraftthe aircraft– Basic Empty Weight and Moment of the aircraftBasic Empty Weight and Moment of the aircraft– Changes to the Weight and BalanceChanges to the Weight and Balance

2828

Weight & Weight & Balance - Balance -

Equipment List Equipment 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 EMPTY AIRPLANE TOTAL ADDED OR SUBTRACTED REVISED EMPTY AIRPLANE 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

2929

Weight & Balance - Weight & Balance - Equipment List RevisionEquipment List Revision

Weight & Balance - Weight & Balance - Equipment List RevisionEquipment List Revision


E.W. C.G. MOMENT

PREVIOUS EMPTY AIRPLANE

TOTAL ADDED 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

3030

CENTER FOR AEROSPACE SCIENCES UNIVERSITY OF NORTH DAKOTA

WEIGHT AND BALANCE, AND EQUIPMENT LIST REVISION

AIRCRAFT MODEL N SERIAL NO. DATE

AMOUNT


E.W.

PREVIOUS EMPTY AIRPLANE TOTAL ADDED OR SUBTRACTED REVISED EMPTY AIRPLANE 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

1467.1

-2.7

1464.4

84.9

867.6

1

124625.5

-156.0

124469.5

SUPERCEDED 5-1-94





Weight and Balance Weight and Balance CalculationCalculation

3232

Weight & Balance Weight & 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

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

3333



Weight Shift FormulasWeight Shift FormulasWeight Shift FormulasWeight Shift Formulas

3434

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 / DeletionWeight to be Added/RemovedWeight to be Added/Removed Distance CG MovesDistance CG Moves

New Aircraft Gross Weight Distance Weight Moves

=

=

3535

Weight & Balance Problem Weight & Balance Problem Set UpSet Up

Weight & Balance Problem Weight & 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

Computation - - Piper WarriorComputation - - Piper Warrior Computation - - Cessna P210Computation - - Cessna P210 Graph - - Piper ArrowGraph - - Piper Arrow Table - - Beech B33 DebonairTable - - Beech B33 Debonair

3636

Computation MethodComputation Method

This method uses the basic weight and This method uses the basic weight and balance formula to determine center of balance 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.

3737

Computation MethodComputation Method

ProcedureProcedure1.1. Determine the Basic Empty Weight of the aircraft.Determine the Basic Empty Weight of the aircraft.

2.2. Find the moment of each weight to be carried.Find the moment of each weight to be 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. This Divide the total moment by the total weight. This number is your Center of Gravitynumber is your Center of Gravity

5.5. Compare this number to the CG limits for the aircraft.Compare this number to the CG limits for the aircraft.

3838

Weight & Balance - Weight & Balance - Piper WarriorPiper Warrior


For our first For our first problem, we problem, we use a weight use a weight and balance and balance form for a form for a Piper Piper Warrior.Warrior.

For our first For our first problem, we problem, we use a weight use a weight and balance and balance form for a form for a Piper Piper Warrior.Warrior.

3939

Step 1Step 1– find the zero fuel conditionfind the zero fuel condition

Step 1Step 1– find the zero fuel conditionfind the zero fuel condition



4040

Piper WarriorPiper WarriorPiper WarriorPiper Warrior

Weight Arm Weight Arm MomentMoment (lbs.) (in.) (lbs.) (in.) (lbs.-in.)(lbs.-in.)

Basic Empty WeightBasic Empty Weight 1,500 1,500 128,850128,850

Weight Arm Weight Arm MomentMoment (lbs.) (in.) (lbs.) (in.) (lbs.-in.)(lbs.-in.)


4141


Weight Arm MomentWeight Arm Moment

(lbs.)(lbs.) (in.) (lbs.-in.) (in.) (lbs.-in.)


Pilot, Front Passengers 340Pilot, Front Passengers 340 80.5 27,370 80.5 27,370

Rear PassengersRear Passengers 340 340 118.1 40,154 118.1 40,154






4242




Basic Empty WeightBasic Empty Weight 1,500 1,500 128,850 128,850



Baggage (200 lb. Max) Baggage (200 lb. Max)

Zero Fuel ConditionZero Fuel Condition 2,1802,180 196,374196,374



Basic Empty WeightBasic Empty Weight 1,500 1,500 128,850 128,850



Baggage (200 lb. Max) Baggage (200 lb. Max)

Zero Fuel ConditionZero Fuel Condition 2,1802,180 196,374196,374

4343

Step 2Step 2– find the ramp condition and takeoff find the ramp condition and takeoff

conditioncondition

– determine that it is within limitsdetermine that it is within limits

Step 2Step 2– find the ramp condition and takeoff find the ramp condition and takeoff

conditioncondition

– determine that it is within limitsdetermine that it is within limits



4444


WeightWeight Arm Arm Moment Moment

(lbs.)(lbs.) (in.) (in.) (lbs.-in.) (lbs.-in.)

Zero Fuel ConditionZero Fuel Condition 2,180 2,180 196,374 196,374

Fuel (48 gallons max)Fuel (48 gallons max) 267 267 95 95 25,365 25,365

Ramp ConditionRamp Condition 2,4472,447 221,739221,739

Taxi, start, runup fuelTaxi, start, runup fuel - 7 - 7 95 95 - 665 - 665

Takeoff condition Takeoff condition 2,4402,440 90.6 221,074 90.6 221,074

WeightWeight Arm Arm Moment Moment

(lbs.)(lbs.) (in.) (in.) (lbs.-in.) (lbs.-in.)

Zero Fuel ConditionZero Fuel Condition 2,180 2,180 196,374 196,374

Fuel (48 gallons max)Fuel (48 gallons max) 267 267 95 95 25,365 25,365

Ramp ConditionRamp Condition 2,4472,447 221,739221,739

Taxi, start, runup fuelTaxi, start, runup fuel - 7 - 7 95 95 - 665 - 665

Takeoff condition Takeoff condition 2,4402,440 90.6 221,074 90.6 221,074

4545

4646

Step 3Step 3– find the landing conditionfind the landing condition

Step 3Step 3– find the landing conditionfind the landing condition



4747


WeightWeight Arm Arm MomentMoment

(lbs.)(lbs.) (in.) (in.) (lbs.- (lbs.-in.)in.)

Takeoff conditionTakeoff condition 2,440 90.6 221,074 2,440 90.6 221,074

Cruise fuel (30 gallons) -180Cruise fuel (30 gallons) -180 95.0 -17,100 95.0 -17,100

Landing conditionLanding condition 2,2602,260 90.25 203,974 90.25 203,974

WeightWeight Arm Arm MomentMoment

(lbs.)(lbs.) (in.) (in.) (lbs.- (lbs.-in.)in.)

Takeoff conditionTakeoff condition 2,440 90.6 221,074 2,440 90.6 221,074

Cruise fuel (30 gallons) -180Cruise fuel (30 gallons) -180 95.0 -17,100 95.0 -17,100

Landing conditionLanding condition 2,2602,260 90.25 203,974 90.25 203,974

4848

Step 4Step 4– confirm that landing weight & C.G. fall confirm that landing weight & C.G. fall

within limitswithin limits

Step 4Step 4– confirm that landing weight & C.G. fall confirm that landing weight & C.G. fall

within limitswithin limits



4949

5050

Weight & Balance - Cessna Weight & Balance - Cessna P210P210

Weight & Balance - Cessna Weight & Balance - Cessna P210P210

Computation Method

5151

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)

5252

102

5353

Zero Fuel ConditionZero Fuel ConditionItemItem WeightWeight ArmArm MomentMoment

BEWBEW 26322632 109000109000

Front SeatFront Seat 170170 3737 62906290Center 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

5454

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 1651216512Ramp WeightRamp Weight 40164016 52.8552.85 212252212252

5555

Takeoff ConditionTakeoff Condition

Run-up minus 16 lbs of fuelRun-up minus 16 lbs of fuel

ItemItem WeightWeight ArmArm MomentMomentRamp WeightRamp Weight 40164016 52.8552.85 212252212252

Run-upRun-up -16-16 4343 -688-688

TakeoffTakeoff 40004000 52.8952.89 211564211564

5656

5757

5858

Shift a PassengerShift a Passenger

Move the 200 pound passenger from the aft Move the 200 pound passenger from the aft seat to the front seat.seat to the front seat.

EquationEquation– Weight MovedWeight Moved Distance CG MovesDistance CG Moves– Total WeightTotal Weight Distance between CG LocationDistance between CG Location

5959

– Weight MovedWeight Moved Distance CG MovesDistance CG Moves– Total WeightTotal Weight Distance between CG Distance between CG

LocationLocation

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

6060

6161

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)

-300-3004343 -12900-12900

LandingLanding 37003700 50.1850.18 185660185660

6262

6363

ExampleExample

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

6464

Chart MethodChart Method

This method depends on charts provided by the This method depends on charts provided by the manufacturer to determine the moments.manufacturer to determine the moments.

Accuracy of the chart method tends to decrease Accuracy 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 few Accuracy 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.

6565

Chart MethodChart Method

Procedure (General)Procedure (General)1.1. Find the charts provided by the manufacturer Find the charts provided by the manufacturer

in Section 6 of the POH. (These may or may in Section 6 of the POH. (These may or may not be provided)not be provided)

2.2. Correlate the weights to the appropriate chart Correlate the weights to the appropriate chart to determine the moment.to determine the moment.

3.3. Add the moments determined from the charts Add the moments determined from the charts and correlate them to the CG Limit chart.and correlate them to the CG Limit chart.

6666

Weight & Balance -Weight & Balance -Piper ArrowPiper Arrow

Graph Method Graph Method

6767

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.

6868

6969

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

7070

Fuel (72 gallon maximum)Fuel (72 gallon maximum)– 50 gallons 50 gallons

300 lbs.300 lbs. MomentMoment

– 2900029000

7171


Zero FuelZero Fuel 2454.22454.2 88.3888.38 216895.8216895.8

FuelFuel 300300 2900029000Ramp 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

7272

7373

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

7474


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

7575

7676

Problem!Problem!

BEWBEW 17741774 147695147695 Front PaxFront Pax 400400 Rear PaxRear Pax 150150 FuelFuel 200200

Weight and Balance Weight and Balance ComputationComputation

Table MethodTable Method

Beech DebonairBeech Debonair

7878


This method depends on tables provided by the This method depends on tables provided by the manufacturer.manufacturer.

Moment data is provided for specific weights only.Moment data is provided for specific weights only. Interpolation will be necessary to determine Interpolation will be necessary to determine

weights not specifically listed.weights not specifically listed. Accuracy is generally within a few hundred pound Accuracy is generally within a few hundred pound

– inches.– inches. This procedure may vary from aircraft to aircraft.This procedure may vary from aircraft to aircraft.

7979


ProcedureProcedure1.1. Find the tabular data provided in Section 6 of Find the tabular data provided in Section 6 of

the POH. (These may or may not be provided)the POH. (These may or may not be provided)2.2. Correlate the weight to the appropriate tables Correlate the weight to the appropriate tables

to determine the moment.to determine the moment.3.3. Add the moments determined from the tables Add the moments determined from the tables

and correlate them to the CG Limit chart.and correlate them to the CG Limit chart.

8080

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.)

8181

8282

8383

8484

CalculationsCalculationsItemItem WeightWeight ArmArm MomentMoment

BEWBEW 19801980 15841584

Front PaxFront Pax 370370 314314

Rear PaxRear Pax 250250 295295

BaggageBaggage 5050 7070

Zero FuelZero Fuel 26502650 22632263

8585

8686

Adding FuelAdding Fuel

Fuel (64 gallons maximum)Fuel (64 gallons maximum)– 60 gallons60 gallons

360 lbs.360 lbs.

8787

Ramp ConditionRamp Condition


Zero FuelZero Fuel 26502650 22632263

FuelFuel 360360 270270Ramp WeightRamp Weight 30103010 25332533

Run-upRun-up -10-10 -8-8Takeoff WeightTakeoff Weight 30003000 25252525

8888

8989

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.

9090

Landing ConditionLanding Condition

ItemItem WeightWeight ArmArm MomentMomentTakeoff WeightTakeoff Weight 30003000 25252525

Fuel flightFuel flight 264264 198198Landing Landing WeightWeight

27362736 23272327

9191

9292

Problem!!Problem!!

BEW BEW 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

Documents

Weight and Balance. 2 3 Lesson Objectives At the conclusion of this lesson you will… Understand why weight and balance is critical to safety of flight