Vayudoot Aviation

1.
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

4 cm right

4 cm left

11 cm right

11 cm left

2.
The responsibility for determination of the mass of 'operating items' and 'crew members' included within the Dry Operating Mass lies with

the person compiling the weighing schedule

the authority of the state of registration

the operator

the commander

3.
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

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

Location of the undercarriage.

4.
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, 2, 3

1, 3, 5

4, 2, 6

2, 5, 6

5.
The Dry Operating Mass of a helicopter is the total mass of a helicopter

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

excluding the crew but including specific equipments for the mission and not including the usable fuel

6.
If the centre of gravity of an aeroplane moves forward during flight the elevator control will

become lighter making the aeroplane more easy to manouevre in pitch

become heavier making the aeroplane more difficult to manouevre in pitch

become lighter making the aeroplane more difficult to manouevre in pitch

become heavier making the aeroplane more easy to manouevre in pitch

7.
Considering only structural limitations, on long distance flights (at the aeroplane's maximum range), the traffic load is normally limited by

The maximum take-off mass

The maximum landing mass

The maximum zero fuel mass.

The maximum zero fuel mass plus the take-off mass

8.
The maximum intensity floor loading for an aeroplane is given in the Flight Manual as 650 kg per square metre. What is the maximum mass of a package which can be safely supported on a pallet with dimensions of 80 cm by 80 cm?

41.6 kg

101.6 kg

416.0 kg

1015.6 kg

9.
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

4.21 m

4.15 m

4.09 m

10.
The Dry Operating Mass of an aeroplane includes

Unusable fuel and reserve fuel

Passengers baggage and cargo

Fuel and passengers baggage and cargo

Crew and crew baggage, catering, removable passenger service equipment, potable water and lavatory chemicals.

11.
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

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

the operator is obliged to use the actual masses of each passenger

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

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

12.
An additional baggage container is loaded into the aft cargo compartment but is not entered into the load and trim sheet. The aeroplane will be heavier than expected and calculated take-off safety speeds

will give reduced safety margins.

will not be achieved

will be greater than required.

are unaffected but V1 will be increased

13.
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 elastic deformation whilst the load was applied, but no permanent distortion

a permanent deformation of the structure

rupture of one or more structural components

no distortion, permanent or temporary of the structure

14.
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

zero fuel mass

Dry operating mass

take-off mass

landing mass

15.
What determines the longitudinal stability of an aeroplane ?

The relationship of thrust and lift to weight and drag.

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

The dihedral, angle of sweepback and the keel effect.

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

16.
An aeroplane is weighed and the following recordings are made:nose wheel assembly scale 5330 kg left main wheel assembly scale 12370 kg right main wheel assembly scale 12480 kg If the 'operational items' amount to a mass of 1780 kg with a crew mass of 545 kg, the empty mass, as entered in the weight schedule, is

30180 kg

31960 kg

32505 kg

28400 kg

17.
Which of the following is unlikely to have any effect on the position of the centre of gravity on an aeroplane in flight ?

Normal consumption of fuel for a swept wing aeroplane

Lowering the landing gear

Changing the tailplane (horizontal stabiliser) incidence angle

Movement of cabin attendants going about their normal duties

18.
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

at or near the focal point of the aeroplane axis system

at or near the forward limit of the centre of gravity

at or near the natural balance point of the empty aeroplane.

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

19.
The empty mass of an aeroplane is recorded in

the loading manifest. It differs from the zero fuel mass by the value of the 'traffic load'.

the weighing schedule and is amended to take account of changes due to modifications of the aeroplane

the weighing schedule. If changes occur, due to modifications, the aeroplane must be reweighed always.

the loading manifest. It differs from Dry Operating Mass by the value of the 'useful load'.

20.
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

76 kg

88 kg (male) 74 kg (female).

84 kg

84 kg (male) 76 kg (female).

21.
Which of the following alternatives corresponds to zero fuel mass?

Take-off mass minus fuel to destination and alternate

The mass of an aeroplane with no usable fuel.

Operating mass plus load of passengers and cargo.

Operating mass plus passengers and cargo.

22.
With reference to mass and balance calculations (on an aeroplane) a datum point is used. This datum point is

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

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

23.
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 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

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 position of the aerodynamic convergence point

24.
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

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

unusable fuel and full operating fluids

all the oil and fuel.

25.
For the purpose of completing the Mass and Balance documentation, the Operating Mass is considered to be Dry Operating Mass plus

Ramp Fuel Mass.

Ramp Fuel Mass less the fuel for APU and run-up

Take-off Fuel Mass

Trip Fuel Mass

26.
The following results were obtained after weighing a helicopter :- front point : 220 kg- right rear point : 500 kg- left rear point : 480 kgThe 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

0,04 m

1,18 m

3,36 m

3,44 m

27.
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

2 points of support

3 points of support

28.
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

29.
The actual 'Zero Fuel Mass' is equal to the

Actual Landing Mass plus trip fuel

Basic Empty Mass plus the fuel loaded

Dry Operating Mass plus the traffic load.

Operating Mass plus all the traffic load.

30.
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

53 000 kg

47 800 kg

48 000 kg

48 400 kg

31.
The Zero Fuel Mass and the Dry Operating Mass

differ by the value of the traffic load 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

32.
The following data is extracted from an aeroplane's loading manifest:Performance limited take-off mass 93500 kgExpected landing mass at destination 81700 kgMaximum certificated landing mass 86300 kgFuel on board 16500 kgDuring 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 and excess structural stress could result

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 overrunning the runway

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

33.
The Basic Mass of a helicopter is the mass of the helicopter without crew,

without specific equipment for the mission, without payload, wthout unusable fuel.

without specific equipments for the mission, without payload, with fuel on board.

without payload, with specific equipment for the mission, without the unusable fuel

without specific equipment for the mission, without payload, with the unusable fuel and standard equipment

34.
The maximum floor loading for a cargo compartment in an aeroplane is given as 750 kg per square metre. A package with a mass of 600 kg. is to be loaded. Assuming the pallet base is entirely in contact with the floor, which of the following is the minimum size pallet that can be used ?

40 cm by 300 cm

40 cm by 200 cm

30 cm by 300 cm

30 cm by 200 cm

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

has 6 or more seats

has 30 or more seats

is carrying 30 or more passengers

has 20 or more seats

36.
To calculate a usable take-off mass, the factors to be taken into account include

Maximum zero fuel mass augmented by the fuel burn

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.

37.
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

32 kg

80 kg

320 kg

38.
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

increased cruise range

lower optimum cruising speed

higher stall speed

39.
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

605.43 inches aft of datum

228.34 inches aft of datum

20.18 inches aft of datum

40.
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

15 kg per passenger

14 kg per passenger

11 kg per passenger

13 kg per passenger

41.
For the purpose of completing the Mass and Balance documentation, the Dry Operating Mass is defined as

The total mass of the aeroplane ready for a specific type of operation excluding all usable fuel.

The total mass of the aeroplane ready for a specific type of operation excluding all usable fuel and traffic load

The total mass of the aeroplane ready for a specific type of operation excluding crew and crew baggage.

The total mass of the aeroplane ready for a specific type of operation excluding all traffic load.

42.
Dry Operating Mass is the mass of the aeroplane less

usable fuel, potable water and lavatory chemicals

usable fuel

traffic load, potable water and lavatory chemicals

usable fuel and traffic load.

43.
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

21 170 kg

21 070 kg

17 810 kg

20 420 kg

44.
When the centre of gravity is at the forward limit, an aeroplane will be

extremely stable and will require excessive elevator control to change pitch

extremely stable and require small elevator control to change pitch.

extremely unstable and require small elevator control to change pitch

extremely unstable and require excessive elevator control to change pitch

45.
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

12200 kg.

17080 kg

29280 kg.

10080 kg

46.
In cruise, an extreme aft longitudinal center of gravity

moves away the cyclic stick from its forward stop and increases the stress in the rotor head

brings the cyclic stick closer to its forward stop and increases the stress in the rotor head

brings the cyclic stick closer to its forward stop and decreases the stress in the rotor head

moves away the cyclic stick from its forward stop and decreases the stresses in the head rotors

47.
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

30 785 kg

38 300 kg

30 300 kg

30 665 kg

48.
The total mass of the aeroplane including crew, crew baggage, plus catering and removable passenger equipment, plus potable water and lavatory chemicals but excluding usable fuel and traffic load, is referred to as

Maximum Zero Fuel Mass

Aeroplane Prepared for Service ( APS) Mass

Dry Operating Mass

Zero Fuel Mass

49.
An aeroplane is to depart from an airfield where the performance limited take-off mass is 89200 kg. Certificated maximum masses are as follows:Ramp (taxi) mass 89930 kgMaximum Take-off mass 89430 kgMaximumLanding mass 71520 kgActual Zero fuel mass 62050 kgFuel on board at ramp:Taxi fuel 600 kgTrip fuel 17830 kgContingency, final reserve and alternate 9030 kgIf the Dry Operating Mass is 40970 kg the traffic load that can be carried on this flight is

21500 kg

21220 kg

21080 kg

20870 kg

50.
In relation to an aeroplane, the term ' Basic Empty Mass' includes the mass of the aeroplane structure complete with its powerplants, systems, furnishings and other items of equipment considered to be an integral part of the particular aeroplane configuration. Its value is

inclusive of an allowance for crew, crew baggage and other operating items. It is entered in the loading manifest

printed in the loading manual and includes unusable fuel.

found in the flight manual and is inclusive of unusable fuel plus fluids contained in closed systems

found in the latest version of the weighing schedule as corrected to allow for modifications

Question Bank

Questions for PAYLOAD AND CG (1488-1678)

The responsibility for determination of the mass of 'operating items' and 'crew members' included within the Dry Operating Mass lies with

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

The Dry Operating Mass of a helicopter is the total mass of a helicopter

If the centre of gravity of an aeroplane moves forward during flight the elevator control will

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

The maximum intensity floor loading for an aeroplane is given in the Flight Manual as 650 kg per square metre. What is the maximum mass of a package which can be safely supported on a pallet with dimensions of 80 cm by 80 cm?

The Dry Operating Mass of an aeroplane includes

An additional baggage container is loaded into the aft cargo compartment but is not entered into the load and trim sheet. The aeroplane will be heavier than expected and calculated take-off safety speeds

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

What determines the longitudinal stability of an aeroplane ?

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

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

The empty mass of an aeroplane is recorded in

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

Which of the following alternatives corresponds to zero fuel mass?

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

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

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

For the purpose of completing the Mass and Balance documentation, the Operating Mass is considered to be Dry Operating Mass plus

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

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 actual 'Zero Fuel Mass' is equal to the

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

The Basic Mass of a helicopter is the mass of the helicopter without crew,

The maximum floor loading for a cargo compartment in an aeroplane is given as 750 kg per square metre. A package with a mass of 600 kg. is to be loaded. Assuming the pallet base is entirely in contact with the floor, which of the following is the minimum size pallet that can be used ?

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

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

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)

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

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

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

For the purpose of completing the Mass and Balance documentation, the Dry Operating Mass is defined as

Dry Operating Mass is the mass of the aeroplane less

When the centre of gravity is at the forward limit, an aeroplane will be

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

In cruise, an extreme aft longitudinal center of gravity

The total mass of the aeroplane including crew, crew baggage, plus catering and removable passenger equipment, plus potable water and lavatory chemicals but excluding usable fuel and traffic load, is referred to as

In relation to an aeroplane, the term ' Basic Empty Mass' includes the mass of the aeroplane structure complete with its powerplants, systems, furnishings and other items of equipment considered to be an integral part of the particular aeroplane configuration. Its value is