Department of Management and Engineering Division of Flumes Master of Science in Mechanical Engineering LIU-IEI-TEK-A--12/01409—SE

Conceptual Design Tool for Aircraft Electrical System Master Thesis by

Venkata Krishnan Gangadharan

Supervisor Patrick Berry Lecturer, Linköping University Examiner Christopher Jouannet Assistant Professor, Linköping University i

Upphovsrätt Detta dokument hålls tillgängligt på Internet – eller dess framtida ersättare – under 25 år från publiceringsdatum under förutsättning att inga extraordinära omständigheter uppstår. Tillgång till dokumentet innebär tillstånd för var och en att läsa, ladda ner, skriva ut enstaka kopior för enskilt bruk och att använda det oförändrat för ickekommersiell forskning och för undervisning. Överföring av upphovsrätten vid en senare tidpunkt kan inte upphäva detta tillstånd. All annan användning av dokumentet kräver upphovsmannens medgivande. För att garantera äktheten, säkerheten och tillgängligheten finns lösningar av teknisk och administrativ art. Upphovsmannens ideella rätt innefattar rätt att bli nämnd som upphovsman i den omfattning som god sed kräver vid användning av dokumentet på ovan beskrivna sätt samt skydd mot att dokumentet ändras eller presenteras i sådan form eller i sådant sammanhang som är kränkande för upphovsmannens litterära eller konstnärliga anseende eller egenart. För ytterligare information om Linköping University Electronic Press se förlagets hemsida http://www.ep.liu.se/ Copyright The publishers will keep this document online on the Internet – or its possible replacement – for a period of 25 years starting from the date of publication barring exceptional circumstances. The online availability of the document implies permanent permission for anyone to read, to download, or to print out single copies for his/hers own use and to use it unchanged for noncommercial research and educational purpose. Subsequent transfers of copyright cannot revoke this permission. All other uses of the document are conditional upon the consent of the copyright owner. The publisher has taken technical and administrative measures to assure authenticity, security and accessibility. According to intellectual property law the author has the right to be mentioned when his/her work is accessed as described above and to be protected against infringement. For additional information about the Linköping University Electronic Press and its procedures for publication and for assurance of document integrity, please refer to its www home page: http://www.ep.liu.se/.

© Venkata Krishnan Gangadharan

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Abbreviation AC- Alternating Current APU- Auxiliary Power Unit ATA –Air Transport Association CATIA- Computer Aided Three-dimensional Interactive Application DC- Direct Current KVA- kilovolt-ampere MTOW- Maximum Take-off Weight VBA- Visual Basic for Applications

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Abstract The conceptual design stage of an aircraft involves many uncertainties with regard to prediction of weight of systems. The current trend is that electrical systems increasingly replace hydraulic and pneumatic systems in an aircraft. This leads to greater uncertainty in weight, size and power requirement prediction. This work is an attempt at developing a sizing tool that will allow users to estimate the power requirements and weight of electrical systems for a given size of an aircraft specified either by passenger capacity or by aircraft operating empty weight or by maximum take-off weight. As with all predictive tools, the results of this work are based on currently available data, i.e., the specification of existing aircraft. This collection of specification of existing aircrafts would constitute the data library. The accuracy of the result of this work depends greatly on the variety of aircrafts and the level of detail for which the data is available. The tool is made in Microsoft Excel with some codes made in VBA to perform Excel calculations.

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Acknowledgement This Master’s thesis work was carried out in the Department of Management and Engineering, Division of Flumes at the Linköping University, Sweden. It was a great experience either to be a student or to work under the staff at the Division of Flumes. I would like to thank especially my supervisor Patrick Berry for his constant pursuit in obtaining materials necessary for this thesis work and providing valuable guidance throughout the course of work without which this would have not been possible. I also extend my gratitude to Christopher Jouannet and Edris Safavi for his timely guidance. Friends and family have been my greatest source of motivation and support for which I would always remain indebted.

Venkata Krishnan Gangadharan Linköping

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Contents Abbreviation ................................................................................................................................................ iv Abstract ......................................................................................................................................................... v Acknowledgement ....................................................................................................................................... vi Contents ...................................................................................................................................................... vii List of Equations ........................................................................................................................................ viii List of Figures ............................................................................................................................................ viii Chapter-1 Introduction .................................................................................................................................. 1 1.1

The Aircraft Electrical System:..................................................................................................... 1

1.2

The need for a Sizing Tool............................................................................................................ 2

Chapter-2 Theory .......................................................................................................................................... 3 2.1 The Data Library: ................................................................................................................................ 3 2.2 Sizing of Power:.................................................................................................................................. 3 2.3 Sizing of Weight and Size:.................................................................................................................. 4 Chapter-3 Implementation- The Sizing Tool ................................................................................................ 5 3.1 The Data Library: ................................................................................................................................ 5 3.2 Power Consumption Analysis ............................................................................................................. 5 3.3 Weight Prediction ............................................................................................................................... 6 Chapter-4 Results .......................................................................................................................................... 9 Chapter-5 Conclusion and Future Work ..................................................................................................... 12 References ................................................................................................................................................... 13 Appendix ..................................................................................................................................................... 14

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List of Equations Equation 1 Power and Voltage relation ........................................................................................................ 1 Equation 2 Cessna method of electrical system weight estimation .............................................................. 7

List of Figures Figure 1 Aircraft Electrical System overview ............................................................................................... 2 Figure 2 DC Power consumption vs. MTOW............................................................................................... 6 Figure 3 DC Power consumption vs. Operating Empty weight .................................................................... 6 Figure 4 Electrical System weight vs. MTOW ............................................................................................. 8 Figure 5 Electrical System weight vs. Operating Empty weight .................................................................. 8 Figure 6 ATR 43-500 Simulation Result – DC Power Consumption ........................................................... 9 Figure 7 Simulation Result- Electrical System Weight Estimation ............................................................ 10 Figure 8 ATR 72-500 Simulation Result- DC Power Consumption........................................................... 10 Figure 9 Airbus A320-200 Simulation Result- DC Power Consumption ................................................... 11 Figure 10 Boeing 737-600 Simulation Result- DC Power Consumption ................................................... 11

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Chapter-1 Introduction 1.1 The Aircraft Electrical System: Aircrafts use hydraulic, pneumatic and electrical energy for various purposes. For example, bleed air from the engine is used in the Environmental Control System, hydraulics are used to drive the primary, secondary controls, landing gear and electrical energy is used to drive the avionics, lighting, in-flight entertainment, etc. The use of electricity in aircrafts began from the technologies developed during World War II, where systems like radar were first used. Since that, the number and complexity of systems using electrical power has increased vastly. Initially the power system employed was 28V DC and with increase in load, 115V AC three phase alternator was used[1]. Power= Voltage x Current Equation 1 Power and Voltage relation

From the equation 1, it can be seen that by increasing the voltage, the amount of current transmitted can be reduced which means conductors of smaller diameter can be used to save weight. Also, voltage drops and power losses can be reduced. In a typical commercial aircraft, electrical power is generated from generators connected to the turbine shaft of the engine. As there is requirement for both AC and DC power supply, a part of the generated power is converted either to DC via Transformer Rectifier Units or AC by inverters respectively. This is then distributed through supply system of wires called the busbars. They are separated into left, right and center busbars on most aircrafts with two or more than two generators[1].

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Generation (Generators, APU, RAT, Battery supply)

Distribution (AC and DC busbars)

Consumption (All connected loads: lighting, avionics, etc.) Figure 1 Aircraft Electrical System overview

The electrical circuit is built redundantly in such a manner that in the event of failure of one primary power source, the systems are powered from the remaining operational generators. The failed power source can be compensated by the remaining secondary sources, usually the APU. If all the primary and secondary sources fail, the vital controls are supplied from an emergency source like a battery back-up or a ram-air turbine or a generator powered by the emergency hydraulic reservoir.

1.2 The need for a sizing tool The conceptual stage in design of a commercial aircraft begins with inputs such as payload capacity or number of passengers. The challenge at this stage is to establish the size and weight of the aircraft as per the requirements. With every new generation, engineers strive to reduce its operating empty weight. Usage of composite materials instead of metal in construction of fuselage, replacing hydraulic and pneumatic systems with electrical systems contributes to significant savings in weight of structure and systems. Replacing hydraulic and pneumatic systems with electrical systems also improves the maintenance, reliability and running costs. As the importance of electrical systems increases in aircrafts, so does the need to establish its sizing. This work attempts to estimate the weight of the electrical systems and also the power consumption according to the requirements such as MTOW, number of passengers or operating empty weight known in the conceptual stage.

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Chapter-2 Theory 2.1 The Data Library: The library would be a repository of information on electrical load analysis, specification of components constituting their power rating, their weight and physical dimensions for various types of aircrafts. This data library is at the core of the sizing tool as the results for the conceptual aircraft are estimated with the help of these available data.

2.2 Sizing of Power: The electrical load analysis is studied for the power consumption of every component connected with the bus at every phase of flight and condition of the generators. The electrical load analysis chart is prepared by listing out all power sources depending on the condition of the generators for the phases of flight starting, taxiing, take-off, climb, cruise, approach and landing. The power consumption does not remain a constant throughout the operation. It varies among components with each phase of flight. For example, components for landing gear operation consume the maximum power only during take-off and approach as only then they are operated. Services like anti-icing or de-icing is used only in adverse weather conditions and they do not contribute to usual load on the generators. Power distribution also varies depending upon the condition of generators. In case of a twin engine aircraft, if any one of the generators fails, the APU could be used as a backup source. In the event of failure of all main generators, depending upon the configuration, the APU or a battery pack or even a ram air turbine would power the essential components. Depending upon the generator condition, the amount and the busses to which power supply flows vary. These data are constructed in the library for the available aircrafts. These are then analyzed to provide the result for the conceptual aircraft.

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2.3 Sizing of Weight and Size: The weights and sizes of components could be estimated in the sizing tool by performing a regression analysis from the data of individual components of all the aircrafts available in the data library. This when correlated with the maximum take-off weight and the number of passengers, this would provide a weight and size estimate for the electrical system of the concept.

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Chapter-3 Implementation- The Sizing Tool 3.1 The Data Library: The library was constructed in Microsoft Excel using the electrical load analysis data of DC power consumption obtained for the aircrafts SAAB 340 and SAAB 2000. The weight split-up for the ATA 24 components of the SAAB 2000 were also obtained.

3.2 Power Consumption Analysis The electrical distribution of the SAAB 340 and the SAAB 2000 are listed out and the power consumption figures for all states of the power source to the corresponding phase of flight are tabulated for both the aircrafts[2]. The user assigns the appropriate flight phase and the generator condition in the sizing input, the sizing tool then obtains the power consumption values for the SAAB 340 and the SAAB 2000 under similar conditions from the data library[3]. An assumption is made that an average of the obtained power consumption values could represent the value for an aircraft with passenger capacity of 46 and MTOW of 18,000 kg as an average value of passenger capacity and MTOW of both the aircrafts. This helps to establish a ratio of power consumption with number of passengers, maximum take-off weight and operating empty weight respectively. This ratio is used to calculate the results for the conceptual aircraft. A scatter diagram is constructed with available data from SAAB 340, SAAB 2000[3], Boeing 737-100 and Boeing 747-100 to predict the trend of change in DC power consumption value with change in MTOW and operating empty weight[4, 5]. This trend line equation is used to predict the values for a given conceptual aircraft.

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Power Consumption KVA

Variation of DC Power Consumption vs MTOW 60 y = 0.0001x + 9.148 R² = 0.9875

50 40

DC Consumption KVA

30 20

Linear (DC Consumption KVA)

10 0 0

100000

200000

300000

400000

MTOW in kg

Figure 2 DC Power consumption vs. MTOW

Power Consumption KVA

Variation of DC Power Consumption vs Operating Empty weight 60 y = 0.0003x + 7.3097 R² = 0.9924

50 40

DC Consumption KVA

30 20

Linear (DC Consumption KVA)

10 0 0

50000

100000

150000

200000

Operating Empty Weight in kg

Figure 3 DC Power consumption vs. Operating Empty weight

3.3 Weight Prediction The ideal method proposed for the weight sizing was to match the power rating of a component obtained from the power sizing value and then match it with its corresponding weight available from the regression analysis. Due to the severe constraints on the data obtained, this method was modified to estimate the weight from the Cessna method[6]. This estimated weight of electrical components is verified to be 95% accurate with the actual weight of the SAAB 2000 and hence

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this method is also adopted in electrical systems weight estimation of the SAAB 340. The Cessna method of weight estimation is given by the following equation[6] Wels=0.0268*WTO Equation 2 Cessna method of electrical system weight estimation

Where, Wels is the weight of electrical systems WTO is the take-off weight of the aircraft With these values, a ratio of the electrical systems weight to the operating empty weight and maximum take-off weight of the aircrafts are made. These values could help establish the electrical systems weight were the designers would know the corresponding preliminary weights of the concept. A scatter diagram is constructed with available data from SAAB 340, SAAB 2000, Boeing 737-100 and Boeing 747-100 to predict the trend of change in weight of electrical systems with change in MTOW and operating empty weight[4, 5]. This trend line equation is used to predict the values for a given conceptual aircraft.

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Electrical system Weight in kg

Variation of Electrical System weight vs MTOW 1400 y = 0.003x + 295.74 R² = 0.9999

1200 1000 800

Electrical system Weight

600 400

Linear (Electrical system Weight)

200 0 0

100000

200000

300000

400000

MTOW in kg

Figure 4 Electrical System weight vs. MTOW

Electrical System weight in kg

Variation of Electrical System weight vs Operating Empty weight 1400 y = 0.0063x + 281.11 R² = 0.9997

1200 1000 800

Electrical system Weight

600 400

Linear (Electrical system Weight)

200 0 0

50000

100000

150000

200000

Operating Empty weight in kg

Figure 5 Electrical System weight vs. Operating Empty weight

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Chapter-4 Results and Discussion The sizing tool was used to predict the DC power consumption values and the electrical systems weight for some aircrafts with the inputs as passenger capacity, maximum take-off weight and operating empty weight[4, 7-9].

ATR 42-500 DC Power consumption KVA

MTOW 18,600 kg. Empty weight 11,250 kg 14 12

Design Value (KVA)

10 8

Value estimated from MTOW by tool (KVA)

6 4

Empty weight design value (KVA)

2 0

Value estimated from empty weight

Figure 6 ATR 43-500 Simulation Result – DC Power Consumption

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Electrical System Weight Estimation Weight of Electrical System in kg

600 500 400 300 200 100 0

By MTOW

ATR 42500

ATR 72500

Boeing 737-600

Airbus A320200

351.5

363.2

493

483.2

352

362.7

510

549.5

By empty weight

Figure 7 Simulation Result- Electrical System Weight Estimation

ATR 72-500

DC Power consumption KVA

MTOW 22,500 kg. Empty Weight 12,950 kg 20

Design Value (KVA)

15 10

Value estimated from MTOW by tool (KVA)

5 0

Empty weight design value (KVA)

Figure 8 ATR 72-500 Simulation Result- DC Power Consumption

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Airbus A320-200

DC Power consumption KVA

MTOW 62,500 kg. Empty Weight 42,600 kg 60 50 40

Design Value (KVA) Value estimated from MTOW by tool (KVA)

30 20 10

Empty weight design value (KVA)

0

Value estimated from empty weight

Figure 9 Airbus A320-200 Simulation Result- DC Power Consumption

Boeing 737-600

DC Power consumption KVA

MTOW 66,000 kg. Empty Weight 36,378 kg 60 50

MTOW Design Value (KVA)

40 30 20

Value estimated from MTOW by tool (KVA) Empty weight design value (KVA)

10 0

Value estimated from empty weight (KVA)

Figure 10 Boeing 737-600 Simulation Result- DC Power Consumption

From the DC power consumption analysis, it could be seen that the increase in difference between values estimated by the tool and actual values increases vastly with increase in the size of the aircraft. This can be due to the fact that the estimation is based on small aircrafts (i.e. MTOW less than around 25,000 kg). To improve the accuracy of prediction of the tool for bigger aircrafts like the Airbus A320, the library has to contain data for similar sized aircrafts. 11

Chapter-5 Conclusion and Future Work The initial objectives of this work were to define the electrical system to proposed layout, with regard to redundancy aspects, power needed over time, weight and size of the system and its components. This system would not only be scalable with power needed but also it can be represented as a physical model in CATIA, to provide the designers an idea if the components would fit in the proposed size of the aircraft. The objectives were revised to due to the limiting factors being the availability of data for the library construction. Currently, only the DC power consumption analysis data are available from manufacturers. More data like AC power consumption analysis, size, weight and power rating of individual components would have helped in the completion of the data library. With a richer collection of library for a variety of aircrafts, the accuracy of the results will be greater. As the sizing tool considers only the DC power consumption values, it does not represent a clear picture in the results. Also, the ratio of consumption of AC and DC power differs between aircrafts since the DC power consumption of the SAAB 340 is more than the bigger SAAB 2000. Also, without any available data for other aircrafts to compare against, the results of this work are yet to be validated. With the trend moving towards replacing more hydraulic and pneumatic systems with electrical systems, the electrical systems weight estimation also gains more significance. This work is in a very primitive stage, so are the methods used in the estimation. This can be used as a fundamental ground work on which a vastly improved sizing tool could be based upon.

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References [1] [2] [3] [4] [5] [6] [7] [8] [9]

I. Moir and A. Seabridge, Aircraft Systems: Longman Scientific & Technical, 1992. SAAB, "SAAB 340B Aircraft Operations Manual." SAAB, "SAAB 2000 DC Load Analysis." Boeing. (05 June). Boeing 737-600 Technical Characteristics. Available: http://www.boeing.com Boeing, "Weight Prediction Manual - Class 1," 25 September 1968. J. Roskam, Airplane Design Part 5. Kansas: Roskam Aviation and Engineering Corporation, 1985. Airbus. (05 June). Airbus A320 Dimensions and Key Data. . Available: http://www.airbus.com ATR. (05 June). ATR 42-500 Product Sheets-Operating Weight. Available: http://www.atraircraft.com ATR. ATR 72-500 Product Sheets-Operating Weight. Available: http://www.atraircraft.com

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Appendix VBA Script Sub Button5_Click() Sheet5.Cells(18, 6).ClearContents Sheet5.Cells(18, 7).ClearContents Dim design_value As Integer Dim flight_condition As Integer If Size.Cells(3, 2) > 0 And Size.Cells(4, 2) = 0 Then design_value = Round((Sheet5.Cells(99, 7) * Sheet5.Cells(7, 2).Value), 1) flight_condition = Round((Sheet5.Cells(7, 2) * (Sheet5.Cells(88, 2) + Sheet5.Cells(88, 3)) / 2), 1) Sheet5.Cells(18, 5) = "Total DC Power Consumption in KVA by Empty Weight " ElseIf Size.Cells(4, 2) > 0 And Size.Cells(3, 2) = 0 Then design_value = Sheet5.Cells(106, 7) * Sheet5.Cells(6, 2) flight_condition = Sheet5.Cells(6, 2) * ((Sheet5.Cells(89, 2) + Sheet5.Cells(89, 3)) / 2) Sheet5.Cells(18, 5) = "Total DC Power Consumption in KVA by MTOW" ElseIf Size.Cells(4, 2) = 0 And Size.Cells(3, 2) = 0 Then design_value = 0 flight_condition = 0 End If Sheet5.Cells(18, 6) = Round(design_value, 2) Sheet5.Cells(18, 7) = Round(flight_condition, 2) Dim S2000_Power_LHDC As Integer Dim S2000_Power_RHDC As Integer Dim S2000_Power_CNTRDC As Integer Dim S340_Power_LHDC As Integer Dim S340_Power_RHDC As Integer

If Size.Cells(17, 2).Value = 1 And Size.Cells(28, 2).Value = 1 Then Sheet5.Cells(9, 2).Value = "Both Engines operational " Sheet5.Cells(12, 2).Value = "Starting "

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ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 3).Value = 1 Then Sheet5.Cells(9, 2).Value = "Both Engines operational " Sheet5.Cells(12, 2).Value = "Taxiing " ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 4).Value = 1 Then Sheet5.Cells(9, 2).Value = "Both Engines operational " Sheet5.Cells(12, 2).Value = "Take-off " ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 5).Value = 1 Then Sheet5.Cells(9, 2).Value = "Both Engines operational " Sheet5.Cells(12, 2).Value = "Climb " ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 6).Value = 1 Then Sheet5.Cells(9, 2).Value = "Both Engines operational " Sheet5.Cells(12, 2).Value = "Cruise " ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 9).Value = 1 Then Sheet5.Cells(9, 2).Value = "Both Engines operational " Sheet5.Cells(12, 2).Value = "Landing " ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 2).Value = 1 Then Sheet5.Cells(9, 2).Value = "One generator operational " Sheet5.Cells(12, 2).Value = "Starting " ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 3).Value = 1 Then Sheet5.Cells(9, 2).Value = "One generator operational " Sheet5.Cells(12, 2).Value = "Taxiing " ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 4).Value = 1 Then Sheet5.Cells(9, 2).Value = "One generator operational " Sheet5.Cells(12, 2).Value = "Take-off " ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 5).Value = 1 Then Sheet5.Cells(9, 2).Value = "One generator operational " Sheet5.Cells(12, 2).Value = "Climb " ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 6).Value = 1 Then Sheet5.Cells(9, 2).Value = "One generator operational " Sheet5.Cells(12, 2).Value = "Cruise "

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ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 9).Value = 1 Then Sheet5.Cells(9, 2).Value = "One generator operational " Sheet5.Cells(12, 2).Value = "Landing " ElseIf Size.Cells(17, 6).Value = 1 And Size.Cells(28, 2).Value = 1 Then Sheet5.Cells(9, 2).Value = "Battery backup" Sheet5.Cells(12, 2).Value = "Starting " ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 3).Value = 1 Then Sheet5.Cells(9, 2).Value = "Battery backup" Sheet5.Cells(12, 2).Value = "Taxiing " ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 4).Value = 1 Then Sheet5.Cells(9, 2).Value = "Battery backup" Sheet5.Cells(12, 2).Value = "Take-off " ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 5).Value = 1 Then Sheet5.Cells(9, 2).Value = "Battery backup" Sheet5.Cells(12, 2).Value = "Climb " ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 6).Value = 1 Then Sheet5.Cells(9, 2).Value = "Battery backup" Sheet5.Cells(12, 2).Value = "Cruise" ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 9).Value = 1 Then Sheet5.Cells(9, 2).Value = "Battery backup" Sheet5.Cells(12, 2).Value = "Landing" End If ''''''''''''''''LH DC 'normal engine operation 'APU START If Size.Cells(17, 2).Value = 1 And Size.Cells(28, 2).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(259, 8) S340_Power_LHDC = Sheet3.Cells(204, 8) S340_Power_RHDC = 0

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'TAXI ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 3).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(259, 9) S340_Power_LHDC = Sheet3.Cells(205, 9) 'TAKEOFF ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 4).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(259, 13) S340_Power_LHDC = Sheet3.Cells(205, 13) 'CLIMB ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 5).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(259, 16) S340_Power_LHDC = Sheet3.Cells(204, 16) 'CRUISE ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 6).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(259, 20) S340_Power_LHDC = Sheet3.Cells(205, 21) 'LANDING ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 9).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(259, 24) 'S2000_Power_LHDC = Sheet1.Cells(260, 24) S340_Power_LHDC = Sheet3.Cells(205, 26) ''''''' one generator operational 'APU START ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 2).Value = 1 Then S2000_Power_LHDC = 0 'TAXI ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 3).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(258, 11) S2000_Power_RHDC = 0 S340_Power_LHDC = Sheet3.Cells(198, 11)

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S340_Power_RHDC = 0 'S2000_Power_LHDC = Sheet1.Cells(259, 11) S2000_Power_LHDC = 0 S2000_Power_RHDC = 0 SS340_Power_LHDC = 0 S340_Power_RHDC = 0 'TAKE OFF ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 4).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(258, 14) S2000_Power_RHDC = 0 S340_Power_LHDC = Sheet3.Cells(198, 14) S340_Power_RHDC = 0 'CLIMB ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 5).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(258, 18) S2000_Power_RHDC = 0 'S2000_Power_LHDC = Sheet1.Cells(259, 18) S340_Power_LHDC = Sheet3.Cells(198, 18) S340_Power_RHDC = 0 'CRUISE ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 6).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(258, 22) S2000_Power_RHDC = 0 'S2000_Power_LHDC = Sheet1.Cells(259, 22) S340_Power_LHDC = Sheet3.Cells(198, 23) S340_Power_RHDC = 0 'LANDING ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 9).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(258, 25) S2000_Power_RHDC = 0

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'S2000_Power_LHDC = Sheet1.Cells(260, 25) S340_Power_LHDC = Sheet3.Cells(198, 27) S340_Power_RHDC = 0 'battery operational 'APU START ElseIf Size.Cells(17, 6).Value = 1 And Size.Cells(28, 2).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(256, 7) S340_Power_LHDC = Sheet3.Cells(194, 7) 'TAXI ElseIf Size.Cells(17, 6).Value = 1 And Size.Cells(28, 3).Value = 1 Then S2000_Power_LHDC = 0 S340_Power_LHDC = 0 'TAKE OFF ElseIf Size.Cells(17, 6).Value = 1 And Size.Cells(28, 4).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(256, 15) S340_Power_LHDC = Sheet3.Cells(194, 15) 'CLIMB ElseIf Size.Cells(17, 6).Value = 1 And Size.Cells(28, 5).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(256, 19) S340_Power_LHDC = Sheet3.Cells(194, 20) 'CRUISE ElseIf Size.Cells(17, 6).Value = 1 And Size.Cells(28, 6).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(256, 23) S340_Power_LHDC = Sheet3.Cells(194, 25) 'LANDING ElseIf Size.Cells(17, 6).Value = 1 And Size.Cells(28, 9).Value = 1 Then S2000_Power_LHDC = Sheet1.Cells(256, 26) S340_Power_LHDC = Sheet3.Cells(194, 28) End If

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'RH DC 'normal engine operational 'APU START If Size.Cells(17, 2).Value = 1 And Size.Cells(28, 2).Value = 1 Then S2000_Power_RHDC = Sheet1.Cells(260, 8) S340_Power_LHDC = Sheet3.Cells(204, 8) S340_Power_RHDC = 0 'TAXI ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 3).Value = 1 Then S2000_Power_RHDC = Sheet1.Cells(260, 9) 'S2000_Power_RHDC = Sheet1.Cells(261, 9) S340_Power_RHDC = Sheet3.Cells(206, 9) 'TAKEOFF ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 4).Value = 1 Then S2000_Power_RHDC = Sheet1.Cells(260, 13) S340_Power_RHDC = Sheet3.Cells(206, 13) 'CLIMB ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 5).Value = 1 Then S2000_Power_RHDC = Sheet1.Cells(260, 16) S340_Power_RHDC = Sheet3.Cells(206, 16) 'CRUISE ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 6).Value = 1 Then S2000_Power_RHDC = Sheet1.Cells(260, 20) 'S2000_Power_RHDC = Sheet1.Cells(261, 20) S340_Power_RHDC = Sheet3.Cells(206, 21) 'LANDING ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 9).Value = 1 Then S2000_Power_RHDC = Sheet1.Cells(260, 24) 'S2000_Power_RHDC = Sheet1.Cells(261, 24) S340_Power_RHDC = Sheet3.Cells(206, 26)

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End If 'CTR DC '''''' battery supply 'APU START If Size.Cells(17, 6).Value = 1 And Size.Cells(28, 2).Value = 1 Then S2000_Power_CNTRDC = 0 'TAXI ElseIf Size.Cells(17, 6).Value = 1 And Size.Cells(28, 3).Value = 1 Then S2000_Power_CNTRDC = 0 'TAKE OFF ElseIf Size.Cells(17, 6).Value = 1 And Size.Cells(28, 4).Value = 1 Then S2000_Power_CNTRDC = 0 'CLIMB ElseIf Size.Cells(17, 6).Value = 1 And Size.Cells(28, 5).Value = 1 Then S2000_Power_CNTRDC = 0 'S2000_Power_CNTRDC = Sheet1.Cells(262, 16) 'CRUISE ElseIf Size.Cells(17, 6).Value = 1 And Size.Cells(28, 6).Value = 1 Then S2000_Power_CNTRDC = 0 'LANDING ElseIf Size.Cells(17, 6).Value = 1 And Size.Cells(28, 9).Value = 1 Then S2000_Power_CNTRDC = 0 'normal engine operation 'APU START ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 2).Value = 1 Then S2000_Power_CNTRDC = Sheet1.Cells(261, 8) 'TAXI ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 3).Value = 1 Then S2000_Power_CNTRDC = Sheet1.Cells(261, 9)

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'TAKE OFF ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 4).Value = 1 Then S2000_Power_CNTRDC = Sheet1.Cells(261, 13) 'CLIMB ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 5).Value = 1 Then S2000_Power_CNTRDC = Sheet1.Cells(261, 16) 'S2000_Power_CNTRDC = Sheet1.Cells(262, 16) 'CRUISE ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 6).Value = 1 Then S2000_Power_CNTRDC = Sheet1.Cells(261, 20) 'LANDING ElseIf Size.Cells(17, 2).Value = 1 And Size.Cells(28, 9).Value = 1 Then S2000_Power_CNTRDC = Sheet1.Cells(261, 24) 'one engine operational 'APU START ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 2).Value = 1 Then S2000_Power_CNTRDC = 0 'TAXI ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 3).Value = 1 Then S2000_Power_CNTRDC = 0 'TAKE OFF ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 4).Value = 1 Then S2000_Power_CNTRDC = 0 'CLIMB ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 5).Value = 1 Then S2000_Power_CNTRDC = 0 'CRUISE ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 6).Value = 1 Then S2000_Power_CNTRDC = 0

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'LANDING ElseIf Size.Cells(17, 3).Value = 1 And Size.Cells(28, 9).Value = 1 Then S2000_Power_CNTRDC = 0 End If Sheet1.Cells(306, 2).Value = S2000_Power_LHDC Sheet1.Cells(307, 2).Value = S2000_Power_RHDC Sheet5.Cells(78, 3).Value = S2000_Power_CNTRDC Sheet3.Cells(225, 2).Value = S340_Power_LHDC Sheet3.Cells(226, 2).Value = S340_Power_RHDC Sheet1.Cells(3, 8).Value = S2000_Power_CNTRDC End Sub

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