Vayudoot Aviation

1.
A revenue flight is to be made by a jet transport. The following are the aeroplane's structural limits:-Maximum Ramp Mass: 69 900 kg-Maximum Take Off Mass: 69 300 kg-Maximum Landing Mass: 58 900 kg-Maximum Zero Fuel Mass: 52 740 kgThe performance limited take off mass is 67 450kg and the performance limited landing mass is 55 470 kg.Dry Operating Mass: 34 900 kgTrip Fuel: 6 200 kgTaxi Fuel: 250 kgContingency & final reserve fuel: 1 300 kgAlternate Fuel: 1 100 kg The maximum traffic load that can be carried is

25 800 kg

18 170 kg

13 950 kg

17 840 kg

2.
Given the following :- Maximum structural take-off mass 48 000 kg- Maximum structural landing mass: 44 000 kg- Maximum zero fuel mass: 36 000 kg-Taxi fuel: 600 kg-Contingency fuel: 900 kg-Alternate fuel: 800 kg-Final reserve fuel: 1 100 kg-Trip fuel: 9 000 kgDetermine the actual take-off mass

48 000 kg

47 800 kg

48 400 kg

53 000 kg

3.
The Zero Fuel Mass and the Dry Operating Mass

are the same value

differ by the sum of the mass of usable fuel plus traffic load mass

differ by the mass of usable fuel

differ by the value of the traffic load mass.

4.
Which one of the following is correct?

Arm = Force X Moment

Arm = Moment / Force

Moment = Force / Arm

Arm = Force / Moment

5.
Which of the following statements is correct?

The Maximum Landing Mass of an aeroplane is restricted by structural limitations, performance limitations and the strength of the runway.

The Basic Empty Mass is equal to the mass of the aeroplane excluding traffic load and useable fuel but including the crew.

The Maximum Take-off Mass is equal to the maximum mass when leaving the ramp.

The Maximum Zero Fuel Mass ensures that the centre of gravity remains within limits after the uplift of fuel.

6.
Assuming gross mass, altitude and airspeed remain unchanged, movement of the centre of gravity from the forward to the aft limit will cause

reduced maximum cruise range

higher stall speed

lower optimum cruising speed

increased cruise range

7.
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

13 kg per passenger

14 kg per passenger

11 kg per passenger

15 kg per passenger

8.
Which of the following is most likely to affect the range of centre of gravity positions on an aeroplane?

The need to maintain a low value of stalling speed.

The need to minimise drag forces and so improve efficiency

Location of the undercarriage.

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

9.
The datum used for balance calculations is

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

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

chosen on the longitudinal axis of the aircraft and necessarily situated between the leading edge and trailing edge of the wing

10.
What determines the longitudinal stability of an aeroplane ?

The effectiveness of the horizontal stabilizer, rudder and rudder trim tab.

The location of the centre of gravity with respect to the neutral point

The relationship of thrust and lift to weight and drag.

The dihedral, angle of sweepback and the keel effect.

11.
An aeroplane is performance limited to a landing mass of 54230 kg. The Dry Operating Mass is 35000 kg and the zero fuel mass is 52080 kg. If the take-off mass is 64280 kg the useful load is

10080 kg

17080 kg

12200 kg.

29280 kg.

12.
By adding to the basic empty mass the following fixed necessary equipment for a specific flight (catering, safety and rescue equipment, fly away kit, crew), we get

Dry operating mass

landing mass

take-off mass

zero fuel mass

13.
With reference to mass and balance calculations (on an aeroplane) a datum point is used. This datum point is

a point near the centre of the aeroplane. It moves longitudinally as masses are added forward and aft of its location

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

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

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.

14.
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,

a permanent deformation of the structure

no distortion, permanent or temporary of the structure

rupture of one or more structural components

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

15.
When preparing to carry out the weighing procedure on an aeroplane, which of the following is not required?

drain all chemical toilet fluid tanks

drain all useable fuel

drain all engine tank oil

removable passenger services equipment to be off-loaded

16.
The determination of the centre of gravity in relation to the mean aerodynamic chord

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 trailing edge

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 position of the aerodynamic convergence point

17.
The centre of gravity location of the aeroplane is normally computed along the

horizontal axis

vertical axis

longitudinal axis

lateral axis

18.
The Dry Operating Mass of an aircraft is 2 000 kg.The maximum take-off mass, landing and zero fuel mass are identical at 3500 kg. The block fuel mass is 550kg, and the taxi fuel mass is 50 kg. The available mass of payload is

950 kg

1 450 kg

1 000 kg

1 500 kg

19.
At a given mass the CG position is at 15% MAC. If the leading edge of MAC is at a position 625.6 inches aft of the datum and the MAC is given as 134.5 inches determine the position of the CG in relation to to the datum

645.78 inches aft of datum

228.34 inches aft of datum

20.18 inches aft of datum

605.43 inches aft of datum

20.
The following results were obtained after weighing a helicopter :- mass at front point: 300 kg- mass at right rear point : 1 100 kg- mass at left rear point : 950 kgIt is given that the front point is located 0.30 m left of the longitudinal axis and the rear points are symmetricaly located 1.20 m from this axis.The helicopter's lateral CG-position relative to the longitudinal axis is

11 cm left

4 cm left

11 cm right

4 cm right

21.
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 kgKnowing 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 kgThe maximum cargo load that the captain may decide to load on board is

61 500 kg

54 000 kg

55 500 kg

55 000 kg

22.
The maximum taxi (ramp) mass is governed by

bearing strength of the taxiway pavement

taxi distance to take - off point

structural considerations

tyre speed and temperature limitations

23.
Which of the following is unlikely to have any effect on the position of the centre of gravity on an aeroplane in flight ?

Changing the tailplane (horizontal stabiliser) incidence angle

Movement of cabin attendants going about their normal duties

Lowering the landing gear

Normal consumption of fuel for a swept wing aeroplane

24.
Given:Aeroplane mass = 36 000 kgCentre of gravity (cg) is located at station 17 mWhat is the effect on cg location if you move 20 passengers (total mass = 1 600 kg) from station 16 to station 23?

It moves aft by 0.31 m.

It moves forward by 0.157 m.

It moves aft by 0.157 m.

It moves aft by 3.22 m.

25.
A revenue flight is to be made by a jet transport. The following are the aeroplane's structural limits:-Maximum Ramp Mass: 69 900 kg-Maximum Take Off Mass: 69 300 kg-Maximum Landing Mass: 58 900 kg-Maximum Zero Fuel Mass: 52 740 kgTake Off and Landing mass are not performance limited.Dry Operating Mass: 34 930 kgTrip Fuel: 11 500 kgTaxi Fuel: 250 kgContingency & final reserve fuel: 1 450 kgAlternate Fuel: 1 350 kg The maximum traffic load that can be carried is

17 810 kg

21 170 kg

20 420 kg

21 070 kg

26.
An aeroplane's weighing schedule indicates that the empty mass is 57320 kg. The nominal Dry Operating Mass is 60120 kg and the Maximum Zero Fuel Mass is given as 72100 kg. Which of the following is a correct statement in relation to this aeroplane?

operational items have a mass of 2800 kg and the maximum traffic load for this aeroplane is 14780 kg

operational items have a mass of 2800 kg and the maximum useful load is 11980 kg.

operational items have a mass of 2800 kg and the maximum traffic load for this aeroplane is 11980 kg.

operational items have a mass of 2800 kg and the maximum useful load is 14780 kg.

27.
Which of the following statements is correct?

The lowest stalling speed is obtained if the actual centre of gravity is located in the middle between the aft and forward limit of centre of gravity

A tail heavy aeroplane is less stable and stalls at a lower speed than a nose heavy aeroplane

If the actual centre of gravity is close to the forward limit of the centre of gravity the aeroplane may be unstable, making it necessary to increase elevator forces

If the actual centre of gravity is located behind the aft limit of centre of gravity it is possible that the aeroplane will be unstable, making it necessary to increase elevator forces

28.
A jet transport has the following structural limits:-Maximum Ramp Mass: 63 060 kg-Maximum Take Off Mass: 62 800 kg-Maximum Landing Mass: 54 900 kg- Maximum Zero Fuel Mass: 51 300 kgThe aeroplane's fuel is loaded accordance with the following requirements:-Taxi fuel: 400 kg-Trip fuel: 8400 kg-Contingency & final reserve fuel: 1800 kg-Alternate fuel: 1100 kgIf the Dry Operating Mass is 34930 kg, determine the maximum traffic load that can be carried on the flight if departure and landing airfields are not performance limited

16 430 kg

17 070 kg

16 570 kg

16 370 kg

29.
The total mass of an aeroplane 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?

30.0 kg

300 kg

196 kg

900 kg

30.
Given:Total mass: 7500 kgCentre of gravity (cg) location station: 80.5 Aft cg limit station: 79.5How much cargo must be shifted from the aft cargo compartment at station 150 to the forward cargo compartment at station 30 in order to move the cg location to the aft limit?

65.8 kg

73.5 kg

68.9 kg

62.5 kg

31.
The take-off mass of an aeroplane is 117 000 kg, comprising a traffic load of 18 000 kg and fuel of 46 000 kg. What is the dry operating mass?

99 000 kg

64 000 kg

71 000 kg

53 000 kg

32.
An aeroplane is loaded with its centre of gravity towards the rear limit. This will result in

an increased risk of stalling due to a decrease in tailplane moment

an increase in longitudinal stability

a reduction in power required for a given speed.

a reduced fuel consumption as a result of reduced drag.

33.
Dry Operating Mass is the mass of the aeroplane less

traffic load, potable water and lavatory chemicals

usable fuel, potable water and lavatory chemicals

usable fuel and traffic load.

usable fuel

34.
While making mass and balance calculation for a particular aeroplane, the term 'Empty Mass' applies to the sum of airframe, engine(s), fixed ballast plus

all the consumable fuel and oil, but not including any radio or navigation equipment installed by manufacturer

unusable fuel and full operating fluids

all the oil, fuel, and hydraulic fluid but not including crew and traffic load.

all the oil and fuel.

35.
Standard masses may be used for the computation of mass values for baggage if the aeroplane

has 6 or more seats

has 20 or more seats

is carrying 30 or more passengers

has 30 or more seats

36.
If individual masses are used, the mass of an aeroplane must be determined prior to initial entry into service and thereafter

at regular annual intervals

at intervals of 9 years

at intervals of 4 years if no modifications have taken place.

only if major modifications have taken place

37.
The centre of gravity of an aeroplane is at 25% of the Mean Aerodynamic Chord.This means that the centre of gravity of the aeroplane is situated at 25% of the length of

the mean aerodynamic chord in relation to the trailing edge

the mean aerodynamic chord in relation to the datum

the aeroplane in relation to the leading edge

the mean aerodynamic chord in relation to the leading edge

38.
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

10%

41%

16%

60%

39.
'Standard Mass' as used in the computation of passenger load establish the mass of a child as

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 for children over 2 years occupying a seat and 10 kg for infants (less than 2 years) not occupying a seat

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

40.
To calculate a usable take-off mass, the factors to be taken into account include

Maximum landing mass augmented by fuel on board at take-off

Maximum landing mass augmented by the fuel burn

Maximum take-off mass decreased by the fuel burn.

Maximum zero fuel mass augmented by the fuel burn

41.
With the centre of gravity on the forward limit which of the following is to be expected?

A decrease in range

A tendency to yaw to the right on take-off.

A decrease of the stalling speed

A decrease in the landing speed.

42.
If the centre of gravity is near the forward limit the aeroplane will

require elevator trim which will result in an increase in fuel consumption

benefit from reduced drag due to the decrease in angle of attack.

tend to over rotate during take-off.

require less power for a given airspeed

43.
To measure the mass and CG-position of an aircraft, it should be weighed with a minimum of

1 point of support

4 point of support

3 points of support

2 points of support

44.
The maximum zero-fuel mass:1- is a regulatory limitation2- is calculated for a maximum load factor of +3.5 g3- is due to the maximum permissible bending moment at the wing root4- imposes fuel dumping from the outer wings tank first5- imposes fuel dumping from the inner wings tank first6- can be increased by stiffening the wingThe combination of correct statements is

1, 3, 5

2, 5, 6

1, 2, 3

4, 2, 6

45.
Traffic load is the

Dry Operating Mass minus the variable load.

Dry Operating Mass minus the disposable load

Take-off Mass minus Zero Fuel Mass.

Zero Fuel Mass minus Dry Operating Mass.

46.
Given:Dry operating mass = 38 000 kgmaximum structural take-off mass = 72 000 kgmaximum landing mass = 65 000 kgmaximum zero fuel mass = 61 000 kgFuel burn = 8 000 kgTake-off Fuel = 10 300 kgThe maximum allowed take-off mass and payload are respectively

73 000 kg and 24 700 kg

71 300 kg and 25 300 kg

73 000 kg and 27 000 kg

71 300 kg and 23 000 kg

47.
A location in the aeroplane which is identified by a number designating its distance from the datum is known as

MAC.

Moment.

Index.

Station.

48.
After weighing a helicopter the following values are noted:forward point: 350 kgaft right point: 995 kgaft left point: 1 205 kgWhat is the longitudinal CG-position in relation to the datum situated 4 m in front of the rotor axis, knowing that the forward point is at 2.5 m forward of the rotor axis and the aft points are 1 m aft of the rotor axis?

4.52 m

4.15 m

4.21 m

4.09 m

49.
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)

800 kg

320 kg

32 kg

80 kg

50.
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 kgpassengers, baggage, cargo: 8 000 kgThe Dry Operating Mass is

30 665 kg

30 785 kg

30 300 kg

38 300 kg

Question Bank

Questions for PAYLOAD AND CG (1488-1678)

Given the following :- Maximum structural take-off mass 48 000 kg- Maximum structural landing mass: 44 000 kg- Maximum zero fuel mass: 36 000 kg-Taxi fuel: 600 kg-Contingency fuel: 900 kg-Alternate fuel: 800 kg-Final reserve fuel: 1 100 kg-Trip fuel: 9 000 kgDetermine the actual take-off mass

The Zero Fuel Mass and the Dry Operating Mass

Which one of the following is correct?

Which of the following statements is correct?

Assuming gross mass, altitude and airspeed remain unchanged, movement of the centre of gravity from the forward to the aft limit will cause

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

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

The datum used for balance calculations is

What determines the longitudinal stability of an aeroplane ?

An aeroplane is performance limited to a landing mass of 54230 kg. The Dry Operating Mass is 35000 kg and the zero fuel mass is 52080 kg. If the take-off mass is 64280 kg the useful load is

By adding to the basic empty mass the following fixed necessary equipment for a specific flight (catering, safety and rescue equipment, fly away kit, crew), we get

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

When preparing to carry out the weighing procedure on an aeroplane, which of the following is not required?

The determination of the centre of gravity in relation to the mean aerodynamic chord

The centre of gravity location of the aeroplane is normally computed along the

The Dry Operating Mass of an aircraft is 2 000 kg.The maximum take-off mass, landing and zero fuel mass are identical at 3500 kg. The block fuel mass is 550kg, and the taxi fuel mass is 50 kg. The available mass of payload is

At a given mass the CG position is at 15% MAC. If the leading edge of MAC is at a position 625.6 inches aft of the datum and the MAC is given as 134.5 inches determine the position of the CG in relation to to the datum

The maximum taxi (ramp) mass is governed by

Which of the following is unlikely to have any effect on the position of the centre of gravity on an aeroplane in flight ?

Given:Aeroplane mass = 36 000 kgCentre of gravity (cg) is located at station 17 mWhat is the effect on cg location if you move 20 passengers (total mass = 1 600 kg) from station 16 to station 23?

An aeroplane's weighing schedule indicates that the empty mass is 57320 kg. The nominal Dry Operating Mass is 60120 kg and the Maximum Zero Fuel Mass is given as 72100 kg. Which of the following is a correct statement in relation to this aeroplane?

Which of the following statements is correct?

Given:Total mass: 7500 kgCentre of gravity (cg) location station: 80.5 Aft cg limit station: 79.5How much cargo must be shifted from the aft cargo compartment at station 150 to the forward cargo compartment at station 30 in order to move the cg location to the aft limit?

The take-off mass of an aeroplane is 117 000 kg, comprising a traffic load of 18 000 kg and fuel of 46 000 kg. What is the dry operating mass?

An aeroplane is loaded with its centre of gravity towards the rear limit. This will result in

Dry Operating Mass is the mass of the aeroplane less

While making mass and balance calculation for a particular aeroplane, the term 'Empty Mass' applies to the sum of airframe, engine(s), fixed ballast plus

Standard masses may be used for the computation of mass values for baggage if the aeroplane

If individual masses are used, the mass of an aeroplane must be determined prior to initial entry into service and thereafter

The centre of gravity of an aeroplane is at 25% of the Mean Aerodynamic Chord.This means that the centre of gravity of the aeroplane is situated at 25% of the length of

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

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

To calculate a usable take-off mass, the factors to be taken into account include

With the centre of gravity on the forward limit which of the following is to be expected?

If the centre of gravity is near the forward limit the aeroplane will

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

Traffic load is the

Given:Dry operating mass = 38 000 kgmaximum structural take-off mass = 72 000 kgmaximum landing mass = 65 000 kgmaximum zero fuel mass = 61 000 kgFuel burn = 8 000 kgTake-off Fuel = 10 300 kgThe maximum allowed take-off mass and payload are respectively

A location in the aeroplane which is identified by a number designating its distance from the datum is known as

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)