Vayudoot Aviation

1.
When an aeroplane is stationary on the ground, its total weight will act vertically

through its centre of gravity

through its centre of pressure

through a point defined as the datum point

through the main wheels of its undercarriage assembly

2.
The standard mass for a child is

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

35 kg for holiday charters and 38 kg for all other flights.

35 kg for all flights

38 kg for all flights

3.
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

13 950 kg

18 170 kg

25 800 kg

17 840 kg

4.
When the centre of gravity is at the forward limit, an aeroplane will be

extremely unstable and 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 stable and will require excessive elevator control to change pitch

5.
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

11 kg per passenger

14 kg per passenger

15 kg per passenger

13 kg per passenger

6.
Given are:- Maximum structural take-off mass: 72 000 kg- Maximum structural landing mass: 56 000 kg- Maximum zero fuel mass: 48 000 kg- Taxi fuel: 800 kg- Trip fuel: 18 000 kg- Contingency fuel: 900 kg- Alternate fuel: 700 kg- Final reserve fuel: 2 000 kgDetermine the actual take-off mass

69 600 kg

72 000 kg

70 400 kg

74 000 kg

7.
Mass for individual passengers (to be carried on an aeroplane) may be determined from a verbal statement by or on behalf of the passengers if the number of

passengers carried is less than 20

passenger seats available is less than 20.

passengers carried is less than 6.

passenger seats available is less than 6.

8.
On an aeroplane without central fuel tank, the maximum Zero Fuel Mass is related to

Variable equipment for the flight.

Wing loaded trip fuel

The bending moment at the wing root

Maximum Structural Take-Off Mass

9.
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

unusable fuel and full operating fluids

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

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

all the oil and fuel.

10.
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?

101.6 kg

41.6 kg

416.0 kg

1015.6 kg

11.
If the centre of gravity is near the forward limit the aeroplane will

require less power for a given airspeed

tend to over rotate during take-off.

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

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

12.
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

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

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

printed in the loading manual and includes unusable fuel.

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

13.
When considering the effects of increased mass on an aeroplane, which of the following is true?

Stalling speeds will be higher

Flight endurance will be increased

Gradient of climb for a given power setting will be higher.

Stalling speeds will be lower

14.
A flight benefits from a strong tail wind which was not forecast. On arrival at destination a straight in approach and immediate landing clearance is given. The landing mass will be higher than planned and

the landing distance will be unaffected

the approach path will be steeper

the landing distance required will be longer

the approach path will be steeper and threshold speed higher

15.
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

20 420 kg

21 070 kg

21 170 kg

17 810 kg

16.
An aeroplane, which is scheduled to fly an oceanic sector, is due to depart from a high altitude airport in the tropics at 1400 local time. The airport has an exceptionally long runway. Which of the following is most likely to be the limiting factor(s) in determining the take - off mass ?

maximum certificated take - off mass

maximum zero fuel mass

en route obstacle clearance requirements

altitude and temperature of the departure airfield

17.
An aeroplane has its centre of gravity located 7 metres from the datum line and it has a mass of 49000 N. The moment about the datum is

1.43 Nm.

34 300 Nm.

343 000 Nm.

7000 Nm.

18.
Which of the following statements is correct?

The station (STA) is always the location of the centre of gravity in relation to a reference point, normally the leading edge of the wing at MAC

The centre of gravity is given in percent of MAC calculated from the leading edge of the wing, where MAC always = the wing chord halfway between the centre line of the fuselage and the wing tip

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 located behind the aft limit the aeroplane longitudinal stability increases

19.
The Maximum Zero Fuel Mass is a structural limiting mass. It is made up of the aeroplane Dry Operational mass plus

unuseable and crew standard mass

traffic load and crew standard mass.

traffic load, unuseable fuel and crew standard mass

traffic load and unuseable fuel

20.
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 convergence point

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 length of the mean aerodynamic chord and the leading edge

21.
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

121450 kg

19650 kg

39105 kg

141100 kg

22.
Given an aeroplane with: Maximum Structural Landing Mass: 125000 kgMaximum Zero Fuel Mass: 108500 kg Maximum Structural Take-off Mass: 155000 kgDry Operating Mass: 82000 kgScheduled trip fuel is 17000 kg and the reserve fuel is 5000 kg.Assuming performance limitations are not restricting, the maximum permitted take-off mass and maximum traffic load are respectively

125500 kg and 21500 kg

125500 kg and 26500 kg

130500 kg and 31500 kg

130500 kg and 26500 kg

23.
An aeroplane is weighed prior to entry into service. Who is responsible for deriving the Dry Operational Mass from the weighed mass by the addition of the 'operational items' ?

The aeroplane manufacturer or supplier.

The commander of the aeroplane

The Operator

The appropriate Aviation Authority

24.
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

a landing further along the runway than normal

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

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

a high threshold speed and a shorter stop distance

25.
The empty mass of an aeroplane is recorded in

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 the zero fuel mass by the value of the 'traffic load'.

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

26.
Given:Dry Operating Mass= 29 800 kgMaximum Take-Off Mass= 52 400 kgMaximum Zero-Fuel Mass= 43 100 kgMaximum Landing Mass= 46 700 kgTrip fuel= 4 000 kgFuel quantity at brakes release= 8 000 kgThe maximum traffic load is

13 300 kg

14 600 kg

9 300 kg

12 900 kg

27.
Standard masses may be used for the computation of mass values for baggage if the aeroplane

has 20 or more seats

has 6 or more seats

has 30 or more seats

is carrying 30 or more passengers

28.
If nose wheel moves aft during gear retraction, how will this movement affect the location of the centre of gravity (cg) on the aeroplane?

It will cause the cg to move aft.

It will not affect the cg location

The cg location will change, but the direction cannot be told the information given.

It will cause the cg to move forward

29.
Given the following information, calculate the loaded centre of gravity (cg).______________________________________________________________ _____STATION MASS (kg) ARM (cm) MOMENT (kgcm)____________________________________________________________ _______Basic Empty Condition 12045 +30 +361350Crew 145 -160 -23200Freight 1 5455 +200 +1091000Freight 2 410 -40 -16400Fuel 6045 -8 -48360Oil 124 +40 +4960

56.35 cm aft datum

53.35 cm aft datum

60.16 cm aft datum

56.53 cm aft datum.

30.
The centre of gravity of an aeroplane is that point through which the total mass of the aeroplane is said to act. The weight acts in a direction

governed by the distribution of the mass within the aeroplane

always parallel to the aeroplane's vertical axis

at right angles to the flight path

parallel to the gravity vector.

31.
The maximum certificated taxi (or ramp) mass is that mass to which an aeroplane may be loaded prior to engine start. It is

a value which varies with airfield temperature and altitude. Corrections are listed in the Flight Manual

a value which varies only with airfield altitude. Standard corrections are listed in the Flight Manual

a fixed value which is listed in the Flight Manual

a value which is only affected by the outside air temperature. Corrections are calculated from data given in the Flight Manual

32.
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 crew and crew baggage.

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

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 all usable fuel.

33.
Calculate the centre of gravity in % MAC (mean aerodynamic chord) with following data:Distance datum - centre of gravity: 12.53 mDistance datum - leading edge: 9.63 mLength of MAC: 8 m

63.4 % MAC

36.3 % MAC

47.0 % MAC

23.1 % MAC

34.
The actual 'Take-off Mass' is equivalent to

Dry Operating Mass plus take-off fuel and the traffic load

Actual Landing Mass plus the take-off fuel

Dry Operating Mass plus the take-off fuel

Actual Zero Fuel Mass plus the traffic load

35.
An aeroplane may be weighed

in a quiet parking area clear of the normal manoeuvring area.

in an area of the airfield set aside for maintenance

at a specified 'weighing location' on the airfield.

in an enclosed, non-air conditioned, hangar

36.
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?

62.5 kg

65.8 kg

68.9 kg

73.5 kg

37.
During take-off you notice that, for a given elevator input, the aeroplane rotates much more rapidly than expected. This is an indication that

the centre of gravity may be towards the aft limit.

the aeroplane is overloaded

the centre of gravity is too far forward

the centre of pressure is aft of the centre of gravity

38.
An aeroplane must be re-weighed at certain intervals. Where an operator uses 'fleet masses' and provided that changes have been correctly documented, this interval is

9 years for each aeroplane

4 years for each aeroplane

whenever the Certificate of Airworthiness is renewed.

whenever a major modification is carried out.

39.
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

71 300 kg and 25 300 kg

73 000 kg and 27 000 kg

73 000 kg and 24 700 kg

71 300 kg and 23 000 kg

40.
The centre of gravity location of the aeroplane is normally computed along the

lateral axis

vertical axis

horizontal axis

longitudinal axis

41.
The maximum mass to which an aeroplane may be loaded, prior to engine start, is

maximum regulated taxi (ramp) mass

maximum certificated taxi (ramp) mass

maximum certificated take - off mass

maximum regulated take - off mass

42.
The maximum quantity of fuel that can be loaded into an aeroplane's tanks is given as 3800 US Gallons. If the fuel density (specific gravity) is given as 0.79 the mass of fuel which may be loaded is

13647 kg.

18206 kg

14383 kg.

11364 kg

43.
The empty mass of an aeroplane, as given in the weighing schedule, is 61300 kg. The operational items (including crew) is given as a mass of 2300 kg. If the takeoff mass is 132000 kg (including a useable fuel quantity of 43800 kg) the useful load is

70700 kg

26900 kg.

29600 kg

68400 kg

44.
When preparing to carry out the weighing procedure on an aeroplane, which of the following is not required?

drain all useable fuel

drain all chemical toilet fluid tanks

removable passenger services equipment to be off-loaded

drain all engine tank oil

45.
The responsibility for determination of the mass of 'operating items' and 'crew members' included within the Dry Operating Mass lies with

the commander

the authority of the state of registration

the operator

the person compiling the weighing schedule

46.
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 IbsPresent cg station 435.0Compartment A station 285.5Compartment B station 792.5

436.7

506.3

433.3

463.7

47.
The crew of a transport aeroplane prepares a flight using the following data:- Block fuel: 40 000 kg- Trip fuel: 29 000 kg- Taxi fuel: 800 kg- Maximum take-off mass: 170 000 kg- Maximum landing mass: 148 500 kg- Maximum zero fuel mass: 112 500 kg- Dry operating mass: 80 400 kgThe maximum traffic load for this flight is

18 900 kg

32 900 kg

40 400 kg

32 100 kg

48.
An aircraft basic empty mass is 3000 kg.The maximum take-off, landing, and zerofuel mass are identical, at 5200 kg. Ramp fuel is 650 kg, the taxi fuel is 50 kg.The payload available is

2 200 kg

1 550 kg

2 150 kg

1 600 kg

49.
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

50.
Moment (balance) arms are measured from a specific point to the body station at which the mass is located. That point is known as

the centre of gravity of the aeroplane

the focal point.

the datum.

the axis

Question Bank

Questions for PAYLOAD AND CG (1488-1678)

When an aeroplane is stationary on the ground, its total weight will act vertically

The standard mass for a child is

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

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

Given are:- Maximum structural take-off mass: 72 000 kg- Maximum structural landing mass: 56 000 kg- Maximum zero fuel mass: 48 000 kg- Taxi fuel: 800 kg- Trip fuel: 18 000 kg- Contingency fuel: 900 kg- Alternate fuel: 700 kg- Final reserve fuel: 2 000 kgDetermine the actual take-off mass

Mass for individual passengers (to be carried on an aeroplane) may be determined from a verbal statement by or on behalf of the passengers if the number of

On an aeroplane without central fuel tank, the maximum Zero Fuel Mass is related to

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

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?

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

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

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

A flight benefits from a strong tail wind which was not forecast. On arrival at destination a straight in approach and immediate landing clearance is given. The landing mass will be higher than planned and

An aeroplane, which is scheduled to fly an oceanic sector, is due to depart from a high altitude airport in the tropics at 1400 local time. The airport has an exceptionally long runway. Which of the following is most likely to be the limiting factor(s) in determining the take - off mass ?

An aeroplane has its centre of gravity located 7 metres from the datum line and it has a mass of 49000 N. The moment about the datum is

Which of the following statements is correct?

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

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

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

An aeroplane is weighed prior to entry into service. Who is responsible for deriving the Dry Operational Mass from the weighed mass by the addition of the 'operational items' ?

The empty mass of an aeroplane is recorded in

Given:Dry Operating Mass= 29 800 kgMaximum Take-Off Mass= 52 400 kgMaximum Zero-Fuel Mass= 43 100 kgMaximum Landing Mass= 46 700 kgTrip fuel= 4 000 kgFuel quantity at brakes release= 8 000 kgThe maximum traffic load is

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

If nose wheel moves aft during gear retraction, how will this movement affect the location of the centre of gravity (cg) on the aeroplane?

The centre of gravity of an aeroplane is that point through which the total mass of the aeroplane is said to act. The weight acts in a direction

The maximum certificated taxi (or ramp) mass is that mass to which an aeroplane may be loaded prior to engine start. It is

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

Calculate the centre of gravity in % MAC (mean aerodynamic chord) with following data:Distance datum - centre of gravity: 12.53 mDistance datum - leading edge: 9.63 mLength of MAC: 8 m

The actual 'Take-off Mass' is equivalent to

An aeroplane may be weighed

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?

During take-off you notice that, for a given elevator input, the aeroplane rotates much more rapidly than expected. This is an indication that

An aeroplane must be re-weighed at certain intervals. Where an operator uses 'fleet masses' and provided that changes have been correctly documented, this interval is

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

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

The maximum mass to which an aeroplane may be loaded, prior to engine start, is

The maximum quantity of fuel that can be loaded into an aeroplane's tanks is given as 3800 US Gallons. If the fuel density (specific gravity) is given as 0.79 the mass of fuel which may be loaded is

The empty mass of an aeroplane, as given in the weighing schedule, is 61300 kg. The operational items (including crew) is given as a mass of 2300 kg. If the takeoff mass is 132000 kg (including a useable fuel quantity of 43800 kg) the useful load is

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

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

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 IbsPresent cg station 435.0Compartment A station 285.5Compartment B station 792.5

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

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