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WorksheetsAircraft Mass and Balance - Mass Limitations
Total questions: 20
Worksheet time: 29mins
The maximum zero fuel mass is the maximum permissible mass of the aircraft...
with no unusable fuel
including the fuel taken up for take-off
with no usable fuel
including all usable fuel unless the aircraft flight manual excludes it
The maximum structural take-off mass is
the maximum permissible total aircraft mass on completion of the refuelling operation
the maximum permissible total aircraft mass for take off subject to the limiting conditions at the departure airfield
the maximum permissible total aircraft mass for take off but excluding fuel
the maximum permissible total aircraft mass at the start of the take-off run
The regulated take-off mass:
is the lower of maximum structural take-off mass and the performance limited landing mass
is the higher of maximum structural zero fuel mass and the performance limited take-off mass
is the lower of maximum structural take-off mass and the performance limited take-off mass
is the maximum performance limited take-off mass subject to any last minute mass changes
Shortly after take-off, an aircraft has to return to its departure airfield due to a serious technical error. In order to land safely, the aircraft must dump fuel. How much fuel must be dumped?
Sufficient to reduce the mass to the zero fuel mass
The pilot calculates the amount of fuel to jettison to reduce the mass to a safe level, or below the regulated landing mass
As much as the pilot feels it is just sufficient to land safely
The fuel system automatically stops the jettison at the regulated landing mass
If the maximum structural landing mass is exceeded
the aircraft will be unable to take-off
no damage will occur providing the aircraft is within the regulated landing mass
no damage will occur providing the aircraft is within the performance limited landing mass
the aircraft's landing gear could collapse on landing
The maximum zero fuel mass is a mass limitation for the
total load of the fuel imposed upon the wing
total load of the fuel imposed upon the fuselage
strength of the wing root
strength of the fuselage
The maximum mass to which an aircraft may be loaded, prior to engine start is
maximum regulated taxi mass
maximum certificated taxi mass
maximum regulated take-off mass
maximum structural take-off mass
The maximum structural take off mass is
a limit which must not be exceeded for any take-off
a take-off limiting mass which is affected by the aerodrome altitude and temperature
a take-off limiting mass which is governed by the climb gradient
limited by the take-off distance available and tabulated in the flight manual
Which of the following statements is correct?
The maximum take-off mass is equal to the maximum mass when leaving the ramp
The basic empty mass is equal to the mass of the aircraft excluding traffic load and usable fuel but including the crew
The maximum zero fuel mass ensures that the centre of gravity remains within limits at all times
The maximum landing mass of an aircraft is restricted by structural limitations, performance limitations and the strength of the runway
Maximum taxi mass is governed by:
tyre speed and temperatuire limitations
structural considerations
taxi distance to take-off point
strength of the taxiway pavement
To calculate the allowable take-off mass, the factors to be taken into account include:
the max take-off mass minus the trip fuel
the sum of the max zero fuel mass and the trip fuel
the sum of the max landing mass and the fuel on board at take-off
the sum of the max landing mass and the trip fuel
Basic empty mass = 5400 kg
Zero fuel mass = 6300 kg
Take-off mass = 8100 kg
Dry operating mass = 5800 kg
Find useful load.
2700
2300
900
1800
Dry operating mass = 37500 kg
Max certified take-off mass = 73000 kg
Max landing mass = 66300 kg
Max zero fuel mass = 62200 kg
Fuel burn = 7500 kg
Take-off fuel = 11000 kg
The max allowed take-off mass and traffic load are respectively:
73800 kg and 28800 kg
73800 kg and 25300 kg
73000 kg and 24500 kg
73000 kg and 28000 kg
An aircraft weighing schedule indicates that the empty mass is 58830 kg. The nominal dry operating mass is 62900 kg and the maximum zero fuel mass is given as 74210 kg.
Which of the following is a correct statement in relation to this aircraft?
Operational items have a mass of 4070 kg and the max useful load is 11310 kg
Operational items have a mass of 4070 kg and the max useful load is 15380 kg
Operational items have a mass of 4070 kg and the max traffic load is 11310 kg
Operational items have a mass of 4070 kg and the max traffic load is 15380 kg
Trip fuel = 29300 kg
Contingency fuel = 1800 kg
Alternate fuel = 2800 kg
Final reserve fuel = 1800 kg
DOM = 85000 kg
PLTOM = 127000 kg
PLTM = 98500 kg
MZFM = 89800 kg
Find the traffic load.
4800 kg
6300 kg
7100 kg
12700 kg
Given:
Taxi fuel = 40 kg
Block fuel = 1980 kg
Trip fuel = 1060 kg
Zero fuel mass = 4790 kg
Find the actual take off mass.
6770 kg
6730 kg
5910 kg
4990 kg
Zero fuel mass = 6200 kg
MSLM = 7550 kg
MSTOM = 7550 kg
Taxi fuel = 20 kg
Alternate fuel = 280 kg
Contingency fuel = 100 kg
Final reserve fuel = 245 kg
Trip fuel = 770 kg
What is the expected landing mass?
7285 kg
7550 kg
6825 kg
7530 kg
PLTOM: 93500 kg
Expected landing mass at destination: 81700 kg
MSLM: 86300 kg
Fuel on board: 16500 kg
During 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:
is 87300 kg which is acceptable in this case because this is a diversion and not a normal scheduled landing
is 83200 kg which is in excess of the regulated landing mass and could result in over-running the runway
is 87300 kg and excess structural stress could result
must be reduced to 81700 kg in order to avoid a high speed approach
Given:
DOM = 79800 kg
Max TO mass = 169000 kg
Max landing mass = 148500 kg
Max zero fuel mass = 112860 kg
Block fuel = 39550 kg
Taxi fuel = 800 kg
Trip fuel = 28700 kg
The maximum traffic load for this aircraft is:
58600 kg
41050 kg
50450 kg
33060 kg
Determine the take off mass for this aircraft
BEM = 1764 lbs
Pilot mass = 165 lbs
Front seat passenger mass = 165 lbs
Optional equipment = 35 lbs
Cargo mass = 380 lbs
Trip fuel = 40 gal
Take-off fuel = 60 gal
Fuel density = 6 lb/gal
2749 lbs
2869 lbs
2719 lbs
2859 bs
