31-05. DETERMINATION OF CG POSITION

Всего заданий: 48

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Заданий на экзамен: 10

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Случайные 5 вопросов:
1. Without the crew, the weight and the CG position of the aircraft are 7.000 kg and 4,70 m. The mass of the pilot is 90 kg The mass of the copilot is 75 kg The mass of the flight engineer is 90 kg With this crew on board, the CG position of the aircraft will be:


2. A turbojet aeroplane has a planned Takeoff Mass of 190.000 kg. The cargo load is distributed as follows:
Cargo 1: 3.000 kg (3,50 m from reference point), Cargo 4: 7.000 kg (20,39 m from reference point)
Distance from reference point to leading edge: 14 m, Length of MAC: 4,6 m
Once the cargo loading is completed, the crew is informed that the centre of gravity at takeoff is located at 38% MAC (Mean Aerodynamic Cord) which is beyond the limits. The captain decides then to redistribute part of the cargo load between cargo 1 and cargo 4 in order to obtain a new centre of gravity location at 31% MAC. Following the transfer operation, the new load distribution is:
.

3. An aeroplane, whose specific data is shown in the annex, has a planned Takeoff Mass of 200.000 kg, with its centre of gravity (CG) located at 15,38 m rearward of the reference point, representing a CG location at 30% MAC (Mean Aerodynamic Cord). The current cargo load distribution is:
Front cargo: 6.500 kg
Rear cargo: 4.000 kg
For performance purposes, the captain decides to reset the value of the centre of gravity location to 33% MAC. The front and rear cargo compartments are located at a distance of 15 m and 25 m from the reference point respectively. After the transfer operation, the new cargo load distribution is:


4. Given:
CG limits from datum: 82,0 — 94,6 inches
Arm from datum to baggage zone 1: 22,5 inches, Arm frdm datum to baggage zone 4: 178,7 inches
Loaded CG: 96,6 inches, Total weight of loaded aircraft: 3.400 lbs
Freight equally distributed between baggage zones 1 and 4
The weight of freight to be moved between baggage zones to bring the aircraft into balance is:
.

5. The Total Mass of an aeroplane is 9.000 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?