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EN ATPL Mass and Balance Questions in English
Practise Mass and Balance
The maximum quantity of fuel that can be loaded into an aircraft's tanks is given as 2200 l. If the fuel density (specific gravity) is given as 0.79 the mass of fuel which may be loaded is:
Aviation fuel F 34 has a density of 0.78 kg/l. What mass should be entered if 170 l are refuelled?
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:
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 kg. Knowing 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 kg. The maximum cargo load that the captain may decide to load on board is:
An aircraft has a Dry Operating Mass of 3000 kg. Its maximum take-off, landing and zero-fuel masses are all 5200 kg. Ramp fuel is 650 kg and taxi fuel is 50 kg. What is the maximum traffic load?
Using the CAA CAP 696 definition of useful load (take-off mass minus dry operating mass), calculate the useful load of an aeroplane with Dry Operating Mass 35000 kg, Zero Fuel Mass 52080 kg and Take-off Mass 64280 kg. Its performance-limited landing mass is 54230 kg.
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 kg. The actual TOM can never be higher than:
Using the CAA CAP 696 definition of useful load (take-off mass minus dry operating mass), calculate the useful load of an aeroplane with Take-off Mass 302550 kg and Dry Operating Mass 161450 kg. Fuel at take-off is 121450 kg, including 19450 kg of contingency and alternate fuel.
The total mass of an aircraft 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?
With respect to multi-engine piston powered aeroplane, determine the ramp mass (lbs) in the following conditions: Basic empty mass: 3 210 lbs Basic arm: 88.5 Inches. One pilot: 160 lbs. Front seat passenger: 200 lbs. Centre seat passengers: 290 lbs. One passenger rear seat: 110 lbs. Baggage in zone 1: 100 lbs. Baggage in zone 4: 50 lbs. Block fuel: 100 US Gal. Trip fuel: 55 US Gal. Fuel for start up and taxi (included in block fuel): 3 US Gal. Fuel density: 6 lbs/US Gal.
