EASA Questions Mass And Balance Loading

Question : 1 - 20

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

1) Considering only structural limitations, on long distance flights (at the aeroplane's maximum range), the traffic load is normally limited by: Report

The maximum zero fuel mass.

The maximum take-off mass.

The maximum landing mass.

2) (For this question use annexes 031-6564A and 031-6564B or Loading Manual SEP1 Figure 2.4) With respect to a single-engine piston powered aeroplane, determine the zero fuel moment (lbs.In./100) in the following conditions: Basic Empty Mass: 2415 lbs. Arm at Basic Empty Mass: 77,9 In. Cargo Zone A: 350 lbs. Baggage Zone B: 35 lbs. Pilot and front seat passenger : 300 lbs (total) Report

2548,8

6675

2496,3

3) In calculations with respect to the position of the centre of gravity a reference is made to a datum. The datum is Report

an arbitrary reference chosen by the pilot which can be located anywhere on the aeroplane.

calculated from the data derived from the weighing procedure carried out on the aeroplane after any major modification.

a reference plane which is chosen by the aeroplane manufacturer. Its position is given in the aeroplane Flight or Loading Manual.

4) The datum is a reference from which all moment (balance) arms are measured. Its precise position is given in the control and loading manual and it is located Report

at or near the forward limit of the centre of gravity.

at or near the focal point of the aeroplane axis system.

at a convenient point which may not physically be on the aeroplane.

5) The datum used for balance calculations is: Report

chosen on the longitudinal axis of the aircraft, and always at the fire-wall level

chosen on the longitudinal axis of the aeroplane, but not necessarily between the nose and the tail of the aircraft

chosen on the longitudinal axis of the aeroplane, and necessarily situated between the nose and the tail of the aircraft

6) The operator of an aircraft equipped with 50 seats uses standard masses for passengers and baggage. During the preparation of a scheduled flight a group of passengers present themselves at the check-in desk, it is apparent that even the lightest of these exceeds the value of the declared standard mass. Report

the operator should use the individual masses of the passengers or alter the standard masss

the operator may use the standard masses for the load and balance calculation without correction

the operator may use the standard masses for the balance but must correct these for the load calculation

7) Moment (balance) arms are measured from a specific point to the body station at which the mass is located. That point is known as Report

the focal point.

the datum.

the centre of gravity of the aeroplane.

8) An aeroplane with a two wheel nose gear and four main wheels rests on the ground with a single nose wheel load of 500 kg and a single main wheel load of 6000 kg. The distance between the nose wheels and the main wheels is 10 meter. How far is the centre of gravity in front of the main wheels? Report

4 meter.

41.6 cm.

40 cm.

9) If 390 Ibs of cargo are moved from compartment B (aft) to compartment A (forward), what is the station number of the new centre of gravity (cg). Given : Gross mass 116.500 Ibs Present cg station 435.0 Compartment A station 285.5 Compartment B station 792.5 Report

463.7

433.3

436.7

10) With reference to mass and balance calculations (on an aeroplane) a datum point is used. This datum point is : Report

a point from which all balance arms are measured. The location of this point varies with the distribution of loads on the aeroplane.

a fixed point from which all balance arms are measured. It may be located anywhere on the aeroplane's longitudinal axis or on the extensions to that axis.

the point through which the sum of the mass values (of the aeroplane and its contents) is assumed to act vertically.

11) (For this question use annexes 031- 11205A and 031-11205B) A turbojet aeroplane is parked with the following data: Corrected dry operating mass: 110 100 kg Basic corrected index: 118.6 Initial cargo distribution: cargo 1: 4 000 kg ; cargo 2: 2 000 kg ; cargo 3: 2 000 kg; other cargo compartments are empty Take-off mass: 200 000 kg; centre of gravity (C.G.) location: 32 % For perfomance reasons, the captain decides to redistribute part of the cargo loading between cargo compartments, in order to take off with a new C.G. location of 34 %. He asks for a transfer of: Report

1 000 kg from cargo 1 to cargo 4

500 kg from cargo 1 to cargo 3

1 000 kg from cargo 3 to cargo 1

12) With respect to aeroplane loading in the planning phase, which of the following statements is always correct ? LM = Landing Mass TOM = Take-off Mass MTOM = Maximum Take-off Mass ZFM = Zero Fuel Mass MZFM = Maximum Zero Fuel Mass DOM = Dry Operating Mass Report

Reserve Fuel = TOM - Trip Fuel

LM = TOM - Trip Fuel

MTOM = ZFM + maximum possible fuel mass

13) Determine the Take-off Mass for the following single engine aeroplane. Given : Standard Empty Mass : 1764 lbs Optional Equipment : 35 lbs Pilot + Front seat passenger : 300 lbs Cargo Mass : 350 lbs Ramp Fuel = Block Fuel : 60 Gal. Trip Fuel : 35 Gal. Fuel density : 6 lbs/Gal. Report

2764 lbs

2809 lbs

2799 lbs

14) An aeroplane has a mean aerodynamic chord (MAC) of 134.5 inches. The leading edge of this chord is at a distance of 625.6 inches aft of the datum. Give the location of the centre of gravity of the aeroplane in terms of percentage MAC if the mass of the aeroplane is acting vertically through a balance arm located 650 inches aft of the datum. Report

18,14%

75,6%

85,5%

15) Determine the Zero Fuel Mass for the following single engine aeroplane. Given : Standard Empty Mass : 1764 lbs Optional Equipment : 35 lbs Pilot + Front seat passenger : 300 lbs Cargo Mass : 350 lbs Ramp Fuel = Block Fuel : 60 Gal. Trip Fuel : 35 Gal. Fuel density : 6 lbs/Gal. Report

2449 lbs

2589 lbs

2659 lbs

16) (For this question use appendix 031-11589A) Without the man on the winch, the mass and the lateral CG position of the helicopter are 6 000 kg and 0.055 m to the right. - the mass of the wet man on the winch is 180 kg With the man on the winch, the mass and lateral CG-position of the helicopter are : Report

beyond the limit

6 180 kg and 0.059m to the right

6 180 kg and 0.075m to the right

17) 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: Report

61 500 kg

54 000 kg

55 000 kg

18) (For this question use annex 031-11219A) An aeroplane, whose specific data is shown in the annex, has a planned take-off mass of 200 000 kg, with its centre of gravity (C.G.) is located at 15.38 m rearward of the reference point, representing a C.G. location at 30 % MAC (Mean Aerodynamic Cord). For performance purposes, the captain decides to reset the value of the centre of gravity location to 35 % MAC. The front and rear cargo compartments are located at a distance of 15 m and 25 m from the reference point respectively, the cargo load mass which needs to be transferred from the front to the rear cargo compartment is: Report

5 600 kg

3 600 kg

4 600 kg

19) (For this question use annex 031-11251A , 031-11251B and 031-11251C) Knowing that: . Dry operating mass: 110 000 kg . Basic index: 119.1 . Number of passengers: 185 distributed as shown in the annex (75 kg per PAX) . Cargo load + luggage: 14 000 kg distributed as shown in the annex. . Fuel: 42 000 kg Stages (1) to (7) and (11) having already been calculated, the centre of gravity in % MAC (Mean Aerodynamic Cord) for zero fuel mass is located at: Report

29.3 %

28.3 %

30.5 %

20) The crew of a transport aeroplane prepares a flight using the following data: - Dry operating mass: 90 000 kg - Block fuel: 30 000 kg - Taxi fuel: 800 kg - Maximum take-off mass: 145 000 kg The traffic load available for this flight is: Report

55 000 kg

55 800 kg

25 800 kg

EASA Questions Mass And Balance Loading

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Centre of Gravity

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