EASA Questions Mass And Balance Inroduction

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

1) (For this question use annex 031-4740A or Loading Manual MEP1 Figure 3.4) With respect to multi-engine piston powered aeroplane, determine the block fuel moment (lbs.In.) in the following conditions: Basic empty mass: 3 210 lbs. One pilot: 160 lbs. Front seat passenger : 200 lbs. Centre seat passengers: 290 lbs. (total) 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. Report

9 360

56 160 Answer Explanations

433 906

2) (For this question use annex 031-4742A or Loading Manual MEP1 Figure 3.4) With respect to a multi-engine piston powered aeroplane, determine the CG location at take off in the following conditions: Basic empty mass: 3 210 lbs. One pilot: 160 lbs. Front seat passenger : 200 lbs. Centre seat passengers: 290 lbs. (total) One passenger rear seat: 110 lbs. Baggage in zone 1: 100 lbs. Baggage in zone 4: 50 lbs. Zero Fuel Mass: 4210 lbs. Moment at Zero Fuel Mass: 377751 lbs.In 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. Report

91.84 inches aft of datum

91.92 inches aft of datum

91.69 inches aft of datum

3) An aircraft basic empty mass is 3000 kg. The maximum take-off, landing, and zero-fuel mass are identical, at 5200 kg. Ramp fuel is 650 kg, the taxi fuel is 50 kg. The payload available is : Report

2 150 kg

1 600 kg

1 550 kg

4) (For this question use annex 031-4741A or Loading Manual MEP1 Figure 3.4) With respect to a multi-engine piston powered aeroplane, determine the total moment (lbs.In) at landing in the following conditions: Basic empty mass: 3 210 lbs. One pilot: 160 lbs. Front seat passenger : 200 lbs. Centre seat passengers: 290 lbs. (total) 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. Total moment at take-off: 432226 lbs.In Report

433 906

377 746

401 338

5) (For this question use annex 031-11606A) Without the man on the winch, the mass and the lateral CG-position of the aircraft are 6 000 kg and 0,04 m to the right. - the mass of the man on the winch is 100 kg With the man on the winch , the lateral CG-position of the aircraft will be: Report

0,062m to the right

0,016m to the left

beyond the limits

6) Which of the following is most likely to affect the range of centre of gravity positions on an aeroplane? Report

Elevator and tailplane (horizontal stabiliser) effectiveness in all flight conditions.

Location of the undercarriage.

The need to maintain a low value of stalling speed.

7) The mass displacement caused by landing gear extension: Report

does not create a longitudinal moment

creates a pitch-down longitudinal moment

creates a longitudinal moment in the direction (pitch-up or pitch-down) determined by the type of landing gear

8) The mass and balance information gives : Basic mass : 1 200 kg ; Basic balance arm : 3.00 m Under these conditions the Basic centre of gravity is at 25% of the mean aerodynamic chord (MAC). The length of MAC is 2m. In the mass and balance section of the flight manual the following information is given : Position Arm front seats : 2.5 m rear seats : 3.5 m rear hold : 4.5 m fuel tanks : 3.0 m The pilot and one passenger embark; each weighs 80 kg. Fuel tanks contain 140 litres of petrol with a density of 0.714. The rear seats are not occupied.Taxi fuel is negligable. The position of the centre of gravity at take-off (as % MAC) is : Report

34 %

17 %

22 %

9) The basic empty mass of an aircraft is 30 000 kg. The masses of the following items are : - catering: 300 kg - safety and rescue material: nil - fly away kit: nil - crew (inclusive crew baggage): 365kg - fuel at take-off: 3 000 kg - unusable fuel: 120 kg - passengers, baggage, cargo: 8 000 kg The Dry Operating Mass is : Report

30 300 kg

38 300 kg

30 785 kg

10) The floor limit of an aircraft cargo hold is 5 000 N/m2. It is planned to load-up a cubic container measuring 0,4 m of side. It's maximum gross mass must not exceed: (assume g=10m/s2) Report

32 kg

320 kg

80 kg

11) At maximum certificated take-off mass an aeroplane departs from an airfield which is not limiting for either take-off or landing masses. During initial climb the number one engine suffers a contained disintegration. An emergency is declared and the aeroplane returns to departure airfield for an immediate landing. The most likely result of this action will be Report

a landing short resultant from the increased angle of approach due to the very high aeroplane mass.

a high threshold speed and possible undercarriage or other structural failure.

a high threshold speed and a shorter stop distance.

12) (For this question use appendix 031-11605A) Without the crew, the weight and the CG-position of the aircraft are 7 000 kg and 4,70m. - the mass of the pilot is 90 kg - the mass of the copilot is 75 kg - the mass of the flight engineer is 90 kg With this crew on board, the CG-position of the aircraft will be: Report

4,455 m

4,615 m

0,217 m

13) The following data is extracted from an aeroplane's loading manifest: Performance limited take-off mass 93500 kg Expected landing mass at destination 81700 kg Maximum certificated landing mass 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 Report

must be reduced to 81700 kg in order to avoid a high speed approach.

is 87300 kg which is acceptable in this case because this is a diversion and not a normal scheduled landing.

is 87300 kg and excess structural stress could result

14) The Dry Operating Mass of a helicopter is the total mass of a helicopter : Report

including the crew,the fuel and the specific equipments for the mission but excluding payload

including the crew, the usable fuel and the specific equipments for the mission and payload

ready for a specific operation including the crew and traffic load, not including the usable fuel

15) At a mass of 1 800 kg, a helicopter equipped with a winch has a lateral CG-position of 5 cm to the left. The CG of the load suspended from the winch is at a distance of 60 cm to the right. With a winch load of 200 kg the lateral CG-position of the helicopter will be: Report

10.5 cm to the right

10,5 cm to the right

1.5 cm to the right

16) During a violent avoidance manoeuvre, a light twin aircraft, certified to FAR 23 requirements was subjected to an instantaneous load factor of 4.2. The Flight Manual specifies that the aircraft is certified in the normal category for a load factor of -1.9 to +3.8. Considering the certification requirements and taking into account that the manufacturer of the twin did not include, during its conception, a supplementary margin in the flight envelope, it might be possible to observe; Report

rupture of one or more structural components

a permanent deformation of the structure

a elastic deformation whilst the load was applied, but no permanent distortion

17) The centre of gravity is the Report

centre of thrust along the longitudinal axis, in relation to a datum line

focus along the longitudinal axis, in relation to a datum line

point where all the aircraft mass is considered to be concentrated

18) The determination of the centre of gravity in relation to the mean aerodynamic chord: Report

consists of defining the centre of gravity longitudinally in relation to the position of the aerodynamic centre of pressure

consists of defining the centre of gravity longitudinally in relation to the length of the mean aerodynamic chord and the leading edge

consists of defining the centre of gravity longitudinally in relation to the length of the mean aerodynamic chord and the trailing edge

19) To measure the mass and CG-position of an aircraft, it should be weighed with a minimum of: Report

3 points of support

2 points of support

1 point of support

20) The following results were obtained after weighing a helicopter : - front point : 220 kg - right rear point : 500 kg - left rear point : 480 kg The helicopter's datum is 3.40 m forward of the rotor axis. The front point is located 2.00 m forward of the rotor axis and the rear points are located 0.50 m aft of the rotor axis. The longitudinal CG-position in relation to the datum is: Report

3,36 m

0,04 m

3,44 m

EASA Questions Mass And Balance Inroduction

Inroduction

Centre of Gravity

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