EASA Questions Mass And Balance Centre Of Gravity

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Question 1 - 5 of 20 (10 points each question)

1) If an aeroplane is at a higher mass than anticipated, for a given airspeed the angle of attack will Report

be greater, drag will increase and endurance will decrease.

be decreased, drag will decrease and endurance will increase.

remain constant, drag will decrease and endurance will decrease.

2) When considering the effects of increased mass on an aeroplane, which of the following is true? Report

Flight endurance will be increased.

Stalling speeds will be higher.

Stalling speeds will be lower.

3) 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 Report

19650 kg

121450 kg

141100 kg

4) (For this question use annex 031-9660 A or Loading Manual MRJT 1 Paragraph 3.1) The medium range jet transport aeroplane is to operate a flight carrying the maximum possible fuel load. Using the following data as appropriate, determine the mass of fuel on board at start of take off. Departure airfield performance limited take-off mass: 60 400 kg Landing airfield -not performance limited. Dry Operating Mass: 34930 kg Fuel required for flight - Taxi fuel: 715 kg Trip fuel: 8600 kg Contingency and final reserve fuel: 1700 kg Alternate fuel 1500 kg Additional reserve 400 kg Traffic load for flight 11000 kg Report

15 815 kg

14 470 kg

16 080 kg

5) 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 kg Performance limited landing mass 54200 kg Dry Operating Mass 34930 kg Taxi fuel 250 kg Trip fuel 9250 kg Contingency and holding fuel 850 kg Alternate fuel 700 kg The maximum permissible traffic load is Report

12840 kg

13090 kg.

16470 kg

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

flight crew (male) 88 kg. (female) 75 kg., cabin crew 75 kg. each. These include an allowance for hand baggage.

flight crew (male) 88 kg. (female) 75 kg., cabin crew 75 kg. each. These do not include an allowance for hand baggage.

flight crew 85 kg., cabin crew 75 kg. each. These are inclusive of a hand baggage allowance.

7) The following data applies to a planned flight. Dry Operating Mass 34900 kg Performance limited Take-Off Mass 66300 kg Performance limited Landing Mass 55200 kg Maximum Zero Fuel Mass 53070 kg Fuel required at ramp:- Taxy fuel 400 kg trip fuel 8600 kg contingency fuel 430 kg alternate fuel 970 kg holding fuel 900 kg Traffic load 16600 kg Fuel 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 : Report

15200 kg

10730 kg

12700 kg

8) 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 Report

11 kg per passenger.

15 kg per passenger.

13 kg per passenger.

9) The standard mass for a child is Report

38 kg for all flights.

30 kg for holiday charters and 35 kg for all other flights.

35 kg for all flights.

10) 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 Report

76 kg

84 kg (male) 76 kg (female).

84 kg

11) (For this question use annexes 031-9631A or Loading Manual MRJT 1 Figure 4.9) From the Loading Manual for the transport aeroplane, the maximum load that can be carried in that section of the aft cargo compartment which has a balance arm centroid at : Report

421.5 inches is 4541 kg.

421.5 inches is 2059 Lbs.

835.5 inches is 3062 kg.

12) For a particular aeroplane, the structural maximum mass without any fuel on board, other than unusable quantities, is : Report

a variable value which may limit the payload carried.

a fixed value which will limit the amount of fuel carried.

a fixed value which is stated in the Aeroplane Operating Manual.

13) (For this question use annex 031-9598 A or Loading Manual MRJT 1 Figure 4.11) The aeroplane has a Take Off Mass of 58 000 kg. At this mass the range of safe CG positions, as determined from the appropriate graph in the loading manual, is: Report

Forward limit 8.5% MAC aft limit 26.1% MAC

Forward limit 8.0% MAC aft limit 26.5% MAC

Forward limit 8.2% MAC aft limit 26.2% MAC

14) 'Standard Mass' as used in the computation of passenger load establish the mass of a child as Report

35 kg for children over 2 years occupying a seat and 10 kg for infants (less than 2 years) occupying a seat.

35 kg irrespective of age provided they occupy a seat.

35 kg only if they are over 2 years old and occupy a seat.

15) 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: Report

65200 kg.

79000 kg

78000 kg

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

unuseable and crew standard mass.

traffic load and crew standard mass.

traffic load and unuseable fuel.

17) (For this question use annex 031-9644 A or Loading Manual MRJT 1 Figure 4.14) 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: Report

6300 kg

12700 kg

4800 kg

18) (For this question use annex 031-9643 A or Loading Manual MRJT 1 Figure 4.14) The following data relates to a planned flight of an aeroplane - Dry Operational mass 60520 kg Performance limited take-off mass 92750 kg Performance limited landing mass 72250 kg Maximum Zero Fuel mass 67530 kg Fuel on board at take-off - Trip fuel 12500 kg Contingency and final reserve fuel 2300 kg Alternate fuel 1700 kg Using this data, as appropriate, calculate the maximum traffic load that can be carried. Report

7730 kg

11730 kg

7010 kg

19) 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: Report

18400 kg

20700 kg

23000 kg

20) (For this question use annex 031-9640 A or Loading Manual MRJT 1 Figure 4.14) A revenue flight is planned for the transport aeroplane. Take-off mass is not airfield limited. The following data applies: Dry Operating Mass 34930 kg Performance limited landing mass 55000 kg Fuel on board at ramp- Taxi fuel 350 kg Trip fuel 9730 kg Contingency and final reserve fuel 1200 kg Alternate fuel 1600 kg Passengers on board 130 Standard mass for each passenger 84 kg Baggage per passenger 14 kg Traffic load Maximum possible Use the loading manual provided and the above data. Determine the maximum cargo load that may be carried without exceeding the limiting aeroplane landing mass. Report

5400 kg

4530 kg.

3185 kg.

EASA Questions Mass And Balance Centre Of Gravity

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