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PAYLOAD AND CG

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PAYLOAD AND CG
PAYLOAD AND CG
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#1. In a modern airplane equipped with an ECAM (Electronic centralized aircraft monitor), when a failure occurs in a circuit, the centralized flight management system:1- releases an aural warning2- lights up the appropriate push-buttons on the overhead panel3- displays the relevant circuit on the system display4- processes the failure automaticallyThe combination regrouping all the correct statements is:

#2. The centre of gravity of a body is that point

#3. The centre of gravity of an aeroplane is that point through which the total mass of the aeroplane is said to act. The weight acts in a direction

#4. When an aeroplane is stationary on the ground, its total weight will act vertically

#5. The weight of an aeroplane, which is in level non accelerated flight, is said to act

#6. The centre of gravity of an aeroplane

#7. The centre of gravity is the

#8. What determines the longitudinal stability of an aeroplane ?

#9. When the centre of gravity is at the forward limit, an aeroplane will be:

#10. If the centre of gravity of an aeroplane moves forward during flight the elevator control will :

#11. An aeroplane is loaded with its centre of gravity towards the rear limit. This will result in :

#12. During take-off you notice that, for a given elevator input, the aeroplane rotates much more rapidly than expected. This is an indication that :

#13. If the centre of gravity is near the forward limit the aeroplane will:

#14. An aeroplane is said to be 'neutrally stable'. This is likely to:

#15. The stalling speed of an aeroplane will be highest when it is loaded with a:

#16. With the centre of gravity on the forward limit which of the following is to be expected?

#17. At a given mass the CG position is at 15% MAC. If the leading edge of MAC is at a position 625.6 inches aft of the datum and the MAC is given as 134.5 inches determine the position of the CG in relation to to the datum.

#18. The maximum floor loading for a cargo compartment in an aeroplane is given as 750 kg per square metre. A package with a mass of 600 kg. is to be loaded. Assuming the pallet base is entirely in contact with the floor, which of the following is the minimum size pallet that can be used ?

#19. The maximum intensity floor loading for an aeroplane is given in the Flight Manual as 650 kg per square metre. What is the maximum mass of a package which can be safely supported on a pallet with dimensions of 80 cm by 80 cm?

#20. The floor limit of an aircraft cargo hold is 5 000 N/m2.It is planned to load-up a cubic container measuring 0,4 m of side.It's maximum gross mass must not exceed:(assume g=10m/s2)

#21. The floor of the main cargo hold is limited to 4 000 N/m2.It is planned to load a cubic container each side of which measures 0.5m.Its maximum gross mass must not exceed:(assume g=10m/s2)

#22. The maximum certificated taxi (or ramp) mass is that mass to which an aeroplane may be loaded prior to engine start. It is :

#23. The maximum mass to which an aeroplane may be loaded, prior to engine start, is :

#24. The maximum taxi (ramp) mass is governed by :

#25. Considering only structural limitations, on very short legs with minimum take-off fuel, the traffic load is normally limited by:

#26. Considering only structural limitations, on long distance flights (at the aeroplane's maximum range), the traffic load is normally limited by:

#27. The maximum zero fuel mass is a mass limitation for the:

#28. Which of the following statements is correct?

#29. The maximum certificated take - off mass is :

#30. For a particular aeroplane, the structural maximum mass without any fuel on board, other than unusable quantities, is :

#31. An aeroplane, which is scheduled to fly an oceanic sector, is due to depart from a high altitude airport in the tropics at 1400 local time. The airport has an exceptionally long runway. Which of the following is most likely to be the limiting factor(s) in determining the take - off mass ?

#32. Based on actual conditions, an aeroplane has the following performance take-off mass limitations:Flaps : 0° 10° 15°Runway: 4100 4400 4600Climb: 4700 4500 4200Masses are in kgStructural limits: take-off/landing/zero fuel: 4 300 kgThe maximum take-off mass is :

#33. Assuming gross mass, altitude and airspeed remain unchanged, movement of the centre of gravity from the forward to the aft limit will cause

#34. If nose wheel moves aft during gear retraction, how will this movement affect the location of the centre of gravity (cg) on the aeroplane?

#35. Which of the following statements is correct?

#36. Which of the following statements is correct?

#37. Which of the following is most likely to affect the range of centre of gravity positions on an aeroplane?

#38. In cruise, an extreme aft longitudinal center of gravity:

#39. In cruise flight, an aft centre of gravity location will:

#40. The mass displacement caused by landing gear extension:

#41. At the flight preparation stage, the following parameters in particular are available for determining the mass of the aircraft:1- Dry operating mass2- Operating massWhich statement is correct:

#42. The Dry Operating Mass of an aeroplane includes :

#43. While making mass and balance calculation for a particular aeroplane, the term 'Empty Mass' applies to the sum of airframe, engine(s), fixed ballast plus

#44. Which is true of the aeroplane empty mass?

#45. In relation to an aeroplane, the term ' Basic Empty Mass' includes the mass of the aeroplane structure complete with its powerplants, systems, furnishings and other items of equipment considered to be an integral part of the particular aeroplane configuration. Its value is

#46. An aeroplane is weighed and the following recordings are made:nose wheel assembly scale 5330 kg left main wheel assembly scale 12370 kg right main wheel assembly scale 12480 kg If the 'operational items' amount to a mass of 1780 kg with a crew mass of 545 kg, the empty mass, as entered in the weight schedule, is

#47. The empty mass of an aeroplane is recorded in

#48. When establishing the mass breakdown of an aeroplane, the empty mass is defined as the sum of the:

#49. The Basic Mass of a helicopter is the mass of the helicopter without crew, :

#50. In relation to an aeroplane the Dry Operating Mass is the total mass of the aeroplane ready for a specific type of operation but excluding

#51. The Take-off Mass of an aeroplane is 66700 kg which includes a traffic load of 14200 kg and a usable fuel load of 10500 kg. If the standard mass for the crew is 545 kg the Dry Operating Mass is

#52. For the purpose of completing the Mass and Balance documentation, the Dry Operating Mass is defined as:

#53. Dry Operating Mass is the mass of the aeroplane less

#54. The total mass of the aeroplane including crew, crew baggage, plus catering and removable passenger equipment, plus potable water and lavatory chemicals but excluding usable fuel and traffic load, is referred to as:

#55. The basic empty mass of an aircraft is 30 000 kg. The masses of the following items are :- catering: 300 kg- safety and rescue material: nil- fly away kit: nil- crew (inclusive crew baggage): 365kg- fuel at take-off: 3 000 kg- unusable fuel: 120 kgpassengers, baggage, cargo: 8 000 kgThe Dry Operating Mass is :

#56. The Dry Operating Mass of a helicopter is the total mass of a helicopter :

#57. By adding to the basic empty mass the following fixed necessary equipment for a specific flight (catering, safety and rescue equipment, fly away kit, crew), we get:

#58. The zero fuel mass of an aeroplane is always:

#59. The term 'Maximum Zero Fuel Mass' consist of :

#60. The actual 'Zero Fuel Mass' is equal to the:

#61. The maximum zero-fuel mass:1- is a regulatory limitation2- is calculated for a maximum load factor of +3.5 g3- is due to the maximum permissible bending moment at the wing root4- imposes fuel dumping from the outer wings tank first5- imposes fuel dumping from the inner wings tank first6- can be increased by stiffening the wingThe combination of correct statements is:

#62. Which of the following alternatives corresponds to zero fuel mass?

#63. On an aeroplane without central fuel tank, the maximum Zero Fuel Mass is related to:

#64. The Maximum Zero Fuel Mass is the mass of the aeroplane with no usable fuel on board. It is a limitation which is:

#65. The Zero Fuel Mass and the Dry Operating Mass

#66. The Maximum Zero Fuel Mass is a structural limiting mass. It is made up of the aeroplane Dry Operational mass plus

#67. The take-off mass of an aeroplane is 141000 kg. Total fuel on board is 63000 kg including 14000 kg reserve fuel and 1000 kg of unusable fuel. The traffic load is 12800 kg. The zero fuel mass is:

#68. Mass for individual passengers (to be carried on an aeroplane) may be determined from a verbal statement by or on behalf of the passengers if the number of

#69. 'Standard Mass' as used in the computation of passenger load establish the mass of a child as

#70. On an aeroplane with a seating capacity of more than 30, it is decided to use standard mass values for computing the total mass of passengers. If the flight is not a holiday charter, the mass value which may be used for an adult is

#71. The standard mass for a child is

#72. On an aeroplane with 20 or more seats engaged on an inter-continental flight, the 'standard mass' which may be used for passenger baggage is

#73. In determining the Dry Operating Mass of an aeroplane it is common practice to use 'standard mass' values for crew. These values are

#74. The maximum quantity of fuel that can be loaded into an aeroplane's tanks is given as 3800 US Gallons. If the fuel density (specific gravity) is given as 0.79 the mass of fuel which may be loaded is

#75. Conversion of fuel volume to mass

#76. Standard masses may be used for the computation of mass values for baggage if the aeroplane

#77. The operator of an aircraft equipped with 50 seats uses standard masses for passengers and baggage. During the preparation of a scheduled flight a group of passengers present themselves at the check-in desk, it is apparent that even the lightest of these exceeds the value of the declared standard mass.

#78. The actual 'Take-off Mass' is equivalent to:

#79. Traffic load is the:

#80. The term 'useful load' as applied to an aeroplane includes

#81. An aeroplane is performance limited to a landing mass of 54230 kg. The Dry Operating Mass is 35000 kg and the zero fuel mass is 52080 kg. If the take-off mass is 64280 kg the useful load is

#82. An aeroplane's weighing schedule indicates that the empty mass is 57320 kg. The nominal Dry Operating Mass is 60120 kg and the Maximum Zero Fuel Mass is given as 72100 kg. Which of the following is a correct statement in relation to this aeroplane?

#83. The empty mass of an aeroplane, as given in the weighing schedule, is 61300 kg. The operational items (including crew) is given as a mass of 2300 kg. If the takeoff mass is 132000 kg (including a useable fuel quantity of 43800 kg) the useful load is

#84. The following data applies to an aeroplane which is about to take off: Certified maximum take-off mass 141500 kg Performance limited take-off mass 137300 kg Dry Operating Mass 58400 kg Crew and crew hand baggage mass 640 kg Crew baggage in hold 110 kgFuel on board 60700 kgFrom this data calculate the mass of the useful load.

#85. The Dry Operating Mass of an aircraft is 2 000 kg.The maximum take-off mass, landing and zero fuel mass are identical at 3500 kg. The block fuel mass is 550kg, and the taxi fuel mass is 50 kg. The available mass of payload is:

#86. Allowed traffic load is the difference between :

#87. The crew of a transport aeroplane prepares a flight using the following data:- Block fuel: 40 000 kg- Trip fuel: 29 000 kg- Taxi fuel: 800 kg- Maximum take-off mass: 170 000 kg- Maximum landing mass: 148 500 kg- Maximum zero fuel mass: 112 500 kg- Dry operating mass: 80 400 kgThe maximum traffic load for this flight is:

#88. The crew of a transport aeroplane prepares a flight using the following data:- Dry operating mass: 90 000 kg- Block fuel: 30 000 kg- Taxi fuel: 800 kg- Maximum take-off mass: 145 000 kgThe traffic load available for this flight is:

#89. An aircraft basic empty mass is 3000 kg.The maximum take-off, landing, and zerofuel mass are identical, at 5200 kg. Ramp fuel is 650 kg, the taxi fuel is 50 kg.The payload available is :

#90. The take-off mass of an aeroplane is 117 000 kg, comprising a traffic load of 18 000 kg and fuel of 46 000 kg. What is the dry operating mass?

#91. When preparing to carry out the weighing procedure on an aeroplane, which of the following is not required?

#92. An aeroplane may be weighed

#93. An aeroplane must be re-weighed at certain intervals. Where an operator uses 'fleet masses' and provided that changes have been correctly documented, this interval is

#94. If individual masses are used, the mass of an aeroplane must be determined prior to initial entry into service and thereafter

#95. An aeroplane is weighed prior to entry into service. Who is responsible for deriving the Dry Operational Mass from the weighed mass by the addition of the 'operational items' ?

#96. The responsibility for determination of the mass of 'operating items' and 'crew members' included within the Dry Operating Mass lies with

#97. The empty mass of an aeroplane is given as 44800 kg. Operational items (including crew standard mass of 1060 kg) are 2300 kg. If the maximum zero fuel mass is given as 65500 kg, the maximum traffic load which could be carried is:

#98. For the purpose of completing the Mass and Balance documentation, the Operating Mass is considered to be Dry Operating Mass plus

#99. The following data applies to a planned flight.Dry Operating Mass 34900 kgPerformance limited Take-Off Mass 66300 kgPerformance limited Landing Mass 55200 kgMaximum Zero Fuel Mass 53070 kgFuel required at ramp:-Taxy fuel 400 kgtrip fuel 8600 kgcontingency fuel 430 kgalternate fuel 970 kgholding fuel 900 kgTraffic load 16600 kgFuel costs at the departure airfield are such that it is decided to load the maximum fuel quantity possible. The total fuel which may be safely loaded prior to departure is :

#100. Prior to departure the medium range twin jet aeroplane is loaded with maximum fuel of 20100 litres at a fuel density (specific gravity) of 0.78. Using the following data - Performance limited take-off mass 67200 kgPerformance limited landing mass 54200 kgDry Operating Mass 34930 kgTaxi fuel 250 kgTrip fuel 9250 kgContingency and holding fuel 850 kgAlternate fuel 700 kgThe maximum permissible traffic load is

#101. An aeroplane is to depart from an airfield at a take-off mass of 302550 kg. Fuel on board at take-off (including contingency and alternate of 19450 kg) is 121450 kg. The Dry Operating Mass is 161450 kg. The useful load will be

#102. Given:Maximum structural take-off mass= 146 900 kgMaximum structural landing mass= 93 800 kgMaximum zero fuel mass= 86 400 kgTrip fuel= 27 500 kgBlock fuel= 35 500 kgEngine starting and taxi fuel = 1 000 kgThe maximum take-off mass is equal to:

#103. Given:Dry Operating Mass= 29 800 kgMaximum Take-Off Mass= 52 400 kgMaximum Zero-Fuel Mass= 43 100 kgMaximum Landing Mass= 46 700 kgTrip fuel= 4 000 kgFuel quantity at brakes release= 8 000 kgThe maximum traffic load is:

#104. Given the following :- Maximum structural take-off mass 48 000 kg- Maximum structural landing mass: 44 000 kg- Maximum zero fuel mass: 36 000 kg-Taxi fuel: 600 kg-Contingency fuel: 900 kg-Alternate fuel: 800 kg-Final reserve fuel: 1 100 kg-Trip fuel: 9 000 kgDetermine the actual take-off mass:

#105. Given that:- Maximum structural take-off mass: 146 000 kg- Maximum structural landing mass: 93 900 kg- Maximum zero fuel mass: 86 300 kg- Trip fuel: 27 000 kg- Taxi fuel: 1 000 kg- Contingency fuel: 1350 kg- Alternate fuel: 2650 kg- Final reserve fuel: 3000 kgDetermine the actual take-off mass:

#106. Given are:- Maximum structural take-off mass: 72 000 kg- Maximum structural landing mass: 56 000 kg- Maximum zero fuel mass: 48 000 kg- Taxi fuel: 800 kg- Trip fuel: 18 000 kg- Contingency fuel: 900 kg- Alternate fuel: 700 kg- Final reserve fuel: 2 000 kgDetermine the actual take-off mass:

#107. With respect to aeroplane loading in the planning phase, which of the following statements is always correct ?LM = Landing MassTOM = Take-off MassMTOM = Maximum Take-off MassZFM = Zero Fuel MassMZFM = Maximum Zero Fuel MassDOM = Dry Operating Mass

#108. Given an aeroplane with:Maximum Structural Landing Mass: 68000 kgMaximum Zero Fuel Mass: 70200 kgMaximum Structural Take-off Mass: 78200 kgDry Operating Mass : 48000 kgScheduled trip fuel is 7000 kg and the reserve fuel is 2800 kg,Assuming performance limitations are not restricting, the maximum permitted take-off mass and maximum traffic load are respectively:

#109. Given an aeroplane with: Maximum Structural Landing Mass: 125000 kgMaximum Zero Fuel Mass: 108500 kg Maximum Structural Take-off Mass: 155000 kgDry Operating Mass: 82000 kgScheduled trip fuel is 17000 kg and the reserve fuel is 5000 kg.Assuming performance limitations are not restricting, the maximum permitted take-off mass and maximum traffic load are respectively:

#110. For the purpose of completing the Mass and Balance documentation, the Traffic Load is considered to be equal to the Take-off Mass

#111. A jet transport has the following structural limits:-Maximum Ramp Mass: 63 060 kg-Maximum Take Off Mass: 62 800 kg-Maximum Landing Mass: 54 900 kg- Maximum Zero Fuel Mass: 51 300 kgThe aeroplane's fuel is loaded accordance with the following requirements:-Taxi fuel: 400 kg-Trip fuel: 8400 kg-Contingency & final reserve fuel: 1800 kg-Alternate fuel: 1100 kgIf the Dry Operating Mass is 34930 kg, determine the maximum traffic load that can be carried on the flight if departure and landing airfields are not performance limited.

#112. A flight has been made from London to Valencia carrying minimum fuel and maximum traffic load. On the return flight the fuel tanks in the aeroplane are to be filled to capacity with a total fuel load of 20100 litres at a fuel density of 0.79 kg/l.The following are the aeroplane's structural limits:-Maximum Ramp Mass: 69 900 kg-Maximum Take Off Mass: 69 300 kg-Maximum Landing Mass: 58 900 kg- Maximum Zero Fuel Mass: 52 740 kgThe performance limited take off mass at Valencia is 67 330 kg.The landing mass at London is not performance limited.Dry Operating Mass: 34 930 kgTrip Fuel (Valencia to London): 5 990 kgTaxi fuel: 250 kgThe maximum traffic load that can be carried from Valencia will be:

#113. An aeroplane is to depart from an airfield where the performance limited take-off mass is 89200 kg. Certificated maximum masses are as follows:Ramp (taxi) mass 89930 kgMaximum Take-off mass 89430 kgMaximumLanding mass 71520 kgActual Zero fuel mass 62050 kgFuel on board at ramp:Taxi fuel 600 kgTrip fuel 17830 kgContingency, final reserve and alternate 9030 kgIf the Dry Operating Mass is 40970 kg the traffic load that can be carried on this flight is

#114. A revenue flight is to be made by a jet transport. The following are the aeroplane's structural limits:-Maximum Ramp Mass: 69 900 kg-Maximum Take Off Mass: 69 300 kg-Maximum Landing Mass: 58 900 kg-Maximum Zero Fuel Mass: 52 740 kgThe performance limited take off mass is 67 450kg and the performance limited landing mass is 55 470 kg.Dry Operating Mass: 34 900 kgTrip Fuel: 6 200 kgTaxi Fuel: 250 kgContingency & final reserve fuel: 1 300 kgAlternate Fuel: 1 100 kg The maximum traffic load that can be carried is:

#115. A revenue flight is to be made by a jet transport. The following are the aeroplane's structural limits:-Maximum Ramp Mass: 69 900 kg-Maximum Take Off Mass: 69 300 kg-Maximum Landing Mass: 58 900 kg-Maximum Zero Fuel Mass: 52 740 kgTake Off and Landing mass are not performance limited.Dry Operating Mass: 34 930 kgTrip Fuel: 11 500 kgTaxi Fuel: 250 kgContingency & final reserve fuel: 1 450 kgAlternate Fuel: 1 350 kg The maximum traffic load that can be carried is:

#116. A revenue flight is to be made by a jet transport. The following are the aeroplane's structural limits:-Maximum Ramp Mass: 69 900 kg-Maximum Take Off Mass: 69 300 kg-Maximum Landing Mass: 58 900 kg-Maximum Zero Fuel Mass: 52 740 kgTake Off and Landing mass are not performance limited.Dry Operating Mass: 34 900 kgTrip Fuel: 11 800 kgTaxi Fuel: 500 kgContingency & final reserve fuel: 1 600 kgAlternate Fuel: 1 900 kg The maximum traffic load that can be carried is:

#117. The flight preparation of a turbojet aeroplane provides the following data: Take-off runway limitation: 185 000 kg Landing runway limitation: 180 000 kg Planned fuel consumption: 11 500 kg Fuel already loaded on board the aircraft: 20 000 kgKnowing that: Maximum take-off mass (MTOM): 212 000 kg Maximum landing mass (MLM): 174 000 kg Maximum zero fuel mass (MZFM): 164 000 kg Dry operating mass (DOM): 110 000 kgThe maximum cargo load that the captain may decide to load on board is:

#118. To calculate a usable take-off mass, the factors to be taken into account include:

#119. Given:Dry operating mass = 38 000 kgmaximum structural take-off mass = 72 000 kgmaximum landing mass = 65 000 kgmaximum zero fuel mass = 61 000 kgFuel burn = 8 000 kgTake-off Fuel = 10 300 kgThe maximum allowed take-off mass and payload are respectively :

#120. Prior to departure an aeroplane is loaded with 16500 litres of fuel at a fuel density of 780 kg/m³. This is entered into the load sheet as 16500 kg and calculations are carried out accordingly. As a result of this error, the aeroplane is

#121. An additional baggage container is loaded into the aft cargo compartment but is not entered into the load and trim sheet. The aeroplane will be heavier than expected and calculated take-off safety speeds

#122. Fuel loaded onto an aeroplane is 15400 kg but is erroneously entered into the load and trim sheet as 14500 kg. This error is not detected by the flight crew but they will notice that

#123. When considering the effects of increased mass on an aeroplane, which of the following is true?

#124. A flight benefits from a strong tail wind which was not forecast. On arrival at destination a straight in approach and immediate landing clearance is given. The landing mass will be higher than planned and

#125. If an aeroplane is at a higher mass than anticipated, for a given airspeed the angle of attack will

#126. In order to provide an adequate ""buffet boundary"" at the commencement of the cruise a speed of 1.3Vs is used. At a mass of 120000 kg this is a CAS of 180 knots. If the mass of the aeroplane is increased to 135000 kg the value of 1.3Vs will be

#127. The following data is extracted from an aeroplane's loading manifest:Performance limited take-off mass 93500 kgExpected landing mass at destination 81700 kgMaximum certificated landing mass 86300 kgFuel on board 16500 kgDuring the flight a diversion is made to an en-route alternate which is not 'performance limited' for landing. Fuel remaining at landing is 10300 kg. The landing mass

#128. At maximum certificated take-off mass an aeroplane departs from an airfield which is not limiting for either take-off or landing masses. During initial climb the number one engine suffers a contained disintegration. An emergency is declared and the aeroplane returns to departure airfield for an immediate landing. The most likely result of this action will be

#129. During a violent avoidance manoeuvre, a light twin aircraft, certified to FAR 23 requirements was subjected to an instantaneous load factor of 4.2. The Flight Manual specifies that the aircraft is certified in the normal category for a load factor of -1.9 to +3.8.Considering the certification requirements and taking into account that the manufacturer of the twin did not include, during its conception, a supplementary margin in the flight envelope, it might be possible to observe,

#130. The centre of gravity location of the aeroplane is normally computed along the:

#131. In mass and balance calculations which of the following describes the datum?

#132. A location in the aeroplane which is identified by a number designating its distance from the datum is known as:

#133. In calculations with respect to the position of the centre of gravity a reference is made to a datum. The datum is

#134. The datum is a reference from which all moment (balance) arms are measured. Its precise position is given in the control and loading manual and it is located

#135. Moment (balance) arms are measured from a specific point to the body station at which the mass is located. That point is known as

#136. The datum used for balance calculations is:

#137. With reference to mass and balance calculations (on an aeroplane) a datum point is used. This datum point is :

#138. The distance from the datum to the Centre of Gravity of a mass is known as

#139. An aeroplane has its centre of gravity located 7 metres from the datum line and it has a mass of 49000 N. The moment about the datum is:

#140. Which one of the following is correct?

#141. In mass and balance calculations the ""index"" is:

#142. A mass of 500 kg is loaded at a station which is located 10 metres behind the present Centre of Gravity and 16 metres behind the datum. (Assume: g=10 m/s^2)The moment for that mass used in the loading manifest is :

#143. Calculate the centre of gravity in % MAC (mean aerodynamic chord) with following data:Distance datum - centre of gravity: 12.53 mDistance datum - leading edge: 9.63 mLength of MAC: 8 m

#144. The loaded centre of gravity (cg) of an aeroplane is 713 mm aft of datum. The mean aerodynamic chord lies between station 524 mm aft and 1706 mm aft. The cg expressed as % MAC (mean aerodynamic chord) is:

#145. The centre of gravity of an aeroplane is at 25% of the Mean Aerodynamic Chord.This means that the centre of gravity of the aeroplane is situated at 25% of the length of:

#146. An aeroplane has a mean aerodynamic chord (MAC) of 134.5 inches. The leading edge of this chord is at a distance of 625.6 inches aft of the datum. Give the location of the centre of gravity of the aeroplane in terms of percentage MAC if the mass of the aeroplane is acting vertically through a balance arm located 650 inches aft of the datum.

#147. The determination of the centre of gravity in relation to the mean aerodynamic chord:

#148. If 390 Ibs of cargo are moved from compartment B (aft) to compartment A (forward), what is the station number of the new centre of gravity (cg).Given : Gross mass 116.500 IbsPresent cg station 435.0Compartment A station 285.5Compartment B station 792.5

#149. Given the following information, calculate the loaded centre of gravity (cg).______________________________________________________________ _____STATION MASS (kg) ARM (cm) MOMENT (kgcm)____________________________________________________________ _______Basic Empty Condition 12045 +30 +361350Crew 145 -160 -23200Freight 1 5455 +200 +1091000Freight 2 410 -40 -16400Fuel 6045 -8 -48360Oil 124 +40 +4960

#150. An aeroplane with a two wheel nose gear and four main wheels rests on the ground with a single nose wheel load of 500 kg and a single main wheel load of 6000 kg. The distance between the nose wheels and the main wheels is 10 meter.How far is the centre of gravity in front of the main wheels?

#151. To measure the mass and CG-position of an aircraft, it should be weighed with a minimum of:

#152. The following results were obtained after weighing a helicopter :- mass at front point: 300 kg- mass at right rear point : 1 100 kg- mass at left rear point : 950 kgIt is given that the front point is located 0.30 m left of the longitudinal axis and the rear points are symmetricaly located 1.20 m from this axis.The helicopter's lateral CG-position relative to the longitudinal axis is:

#153. After weighing a helicopter the following values are noted:forward point: 350 kgaft right point: 995 kgaft left point: 1 205 kgWhat is the longitudinal CG-position in relation to the datum situated 4 m in front of the rotor axis, knowing that the forward point is at 2.5 m forward of the rotor axis and the aft points are 1 m aft of the rotor axis?

#154. The following results were obtained after weighing a helicopter :- front point : 220 kg- right rear point : 500 kg- left rear point : 480 kgThe helicopter's datum is 3.40 m forward of the rotor axis. The front point is located 2.00 m forward of the rotor axis and the rear points are located 0.50 m aft of the rotor axis.The longitudinal CG-position in relation to the datum is:

#155. Given:Total mass 2900 kgCentre of gravity (cg) location station: 115.0Aft cg limit station: 116.0The maximum mass that can be added at station 130.0 is:

#156. Given:Total mass: 7500 kgCentre of gravity (cg) location station: 80.5 Aft cg limit station: 79.5How much cargo must be shifted from the aft cargo compartment at station 150 to the forward cargo compartment at station 30 in order to move the cg location to the aft limit?

#157. The total mass of an aeroplane is 9000 kg. The centre of gravity (cg) position is at 2.0 m from the datum line. The aft limit for cg is at 2.1 m from the datum line.What mass of cargo must be shifted from the front cargo hold (at 0.8 m from the datum) to the aft hold (at 3.8 m), to move the cg to the aft limit?

#158. Given:Aeroplane mass = 36 000 kgCentre of gravity (cg) is located at station 17 mWhat is the effect on cg location if you move 20 passengers (total mass = 1 600 kg) from station 16 to station 23?

#159. The mass of an aeroplane is 1950 kg. If 450 kg is added to a cargo hold 1.75 metres from the loaded centre of gravity (cg). The loaded cg will move:

#160. Given are the following information at takeoff_______________________________________________________________ ____STATION MASS (kg) ARM (cm) MOMENT (kgcm)____________________________________________________________ _______Basic Empty Condition 12045 +30 +361350Crew 145 -160 -23200Freight 1 5455 +200 +1091000 Freight 2 410 -40 -16400Fuel 6045 -8 - 48360Oil 124 +40 +4960Given that the flight time is 2 hours and the estimated fuel flow will be 1050 litres per hour and the average oil consumption will be 2.25 litres per hour. The specific density of fuel is 0.79 and the specific density of oil is 0.96.Calculate the landing centre of gravity

#161. Given that the total mass of an aeroplane is 112 000 kg with a centre of gravity position at 22.62m aft of the datum. The centre of gravity limits are between 18m and 22m. How much mass must be removed from the rear hold (30 m aft of the datum) to move the centre of gravity to the middle of the limits:

#162. Which of the following is unlikely to have any effect on the position of the centre of gravity on an aeroplane in flight ?

Finish
PAYLOAD AND CG
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