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EN ATPL Mass and Balance Questions in English
Practise Mass and Balance
Aeroplane Dry Operating mass 85000 kg Performance limited take-off mass 127000 kg Performance limited landing mass 98500 kg Maximum zero fuel mass 89800 kg. Fuel requirements for flight - Trip fuel 29300 kg. Contingency and final reserve fuel 3600 kg. Alternate fuel 2800 kg. The maximum traffic load that can be carried on this flight is:
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 masses are not performance limited. Dry Operating Mass: 34 930 kgTrip Fuel: 11 500 kg Taxi Fuel: 250 kgContingency & final reserve fuel: 1 450 kg Alternate Fuel: 1 350 kg. The maximum traffic load that can be carried is:
Where is the centre of gravity of the aeroplane in the diagram?
Given are the following information at take-off ____________________________________________________________ STATION....................MASS (kg)....ARM (cm)....MOMENT (kgcm) ____________________________________________________________ Basic Empty Condition...12045.........+30......+361350 Crew..................................145........-160.......-23200 Freight (1)..........................570.......+200......+114000 Freight (2)..........................410..........-40.......-16400 Fuel.................................6045...........-8.......-48360 Given that the flight time is 2 h and the estimated fuel flow will be 1050 litres per h. The specific density of fuel is 0.79. The 'Freight (2)' will be dropped during flight within the scope of a rescue action. Calculate the CG position at landing.
Given: Standard Empty Mass 1764 lbs. Optional Equipment 35 lbs. Pilot + Passenger 300 lbs. Cargo 350 lbs. Ramp Fuel ( Block Fuel) 60 Gal. Trip Fuel 35 Gal. Taxi Fuel 1.7 Gal. Final Reserve Fuel 18 Gal. Fuel density 6 lbs/Gal. Determine the expected landing mass.
Length of the mean aerodynamic chord = 1 m Moment arm of the forward cargo: -0,50 m Moment arm of the aft cargo: + 2,50 m. The aircraft mass is 2 200 kg and its centre of gravity is at 25% MAC. To move the centre of gravity to 40%, which mass has to be transferred from the forward to the aft cargo hold?
Using the CAA CAP 696 definition of useful load (take-off mass minus dry operating mass), calculate the useful load for: Basic Empty Mass 4800 kg, Dry Operating Mass 5050 kg, Zero Fuel Mass 6210 kg and Take-off Mass 8010 kg.
Given: The take-off mass of an aircraft is 8470 kg. Total fuel on board is 1600 kg including 450 kg reserve fuel and 29 kg of unusable fuel The traffic load is 770 kg. What is the Zero Fuel Mass?
The maximum load per running metre of an aircraft is 350 kg / m. The width of the floor area is 2 metres. The floor strength limitation is 300 kg per square metre. Which one of the following crates (length x width x height) can be loaded directly on the floor?
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 the datum.
