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CPL Test Series
Question Bank
Questions for PAYLOAD AND CG (1488-1678)
Answer the following questions
Test Mode
Training Mode
1.
Which of the following statements is correct?
A tail heavy aeroplane is less stable and stalls at a lower speed than a nose heavy aeroplane
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
If the actual centre of gravity is located behind the aft limit the aeroplane longitudinal stability increases
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
2.
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
parallel to the gravity vector.
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
3.
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)
80 kg
32 kg
320 kg
800 kg
4.
When establishing the mass breakdown of an aeroplane, the empty mass is defined as the sum of the
basic mass plus variable equipment mass
standard empty mass plus specific equipment mass plus trapped fluids plus unusable fuel mass
empty mass dry plus variable equipment mass
basic mass plus special equipment mass
5.
In cruise, an extreme aft longitudinal center of gravity
moves away the cyclic stick from its forward stop and decreases the stresses in the head rotors
brings the cyclic stick closer to its forward stop and increases the stress in the rotor head
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 decreases the stress in the rotor head
6.
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 aeroplane in relation to the leading edge
the mean aerodynamic chord in relation to the datum
the mean aerodynamic chord in relation to the leading edge
the mean aerodynamic chord in relation to the trailing edge
7.
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 useful load 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 14780 kg
operational items have a mass of 2800 kg and the maximum traffic load for this aeroplane is 11980 kg.
8.
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
85,50%
18,14%
75,60%
10,50%
9.
To calculate a usable take-off mass, the factors to be taken into account include
Maximum landing mass augmented by the fuel burn
Maximum zero fuel mass augmented by the fuel burn
Maximum landing mass augmented by fuel on board at take-off
Maximum take-off mass decreased by the fuel burn.
10.
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
11.
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 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.
The total mass of the aeroplane ready for a specific type of operation excluding crew and crew baggage.
12.
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
60%
41%
10%
16%
13.
Which of the following alternatives corresponds to zero fuel mass?
Operating mass plus passengers and cargo.
Take-off mass minus fuel to destination and alternate
Operating mass plus load of passengers and cargo.
The mass of an aeroplane with no usable fuel.
14.
Given an aeroplane with:Maximum Structural Landing Mass: 68000 kgMaximum Zero Fuel Mass: 70200 kgMaximum Structural Take-off Mass: 78200 kgDry Operating Mass : 48000 kgScheduled trip fuel is 7000 kg and the reserve fuel is 2800 kg,Assuming performance limitations are not restricting, the maximum permitted take-off mass and maximum traffic load are respectively
77200 kg and 19400 kg
75000 kg and 20000 kg
77200 kg and 22200 kg
75000 kg and 17200 kg
15.
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
1 450 kg
950 kg
1 500 kg
1 000 kg
16.
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
zero fuel mass
take-off mass
17.
The Take-off Mass of an aeroplane is 66700 kg which includes a traffic load of 14200 kg and a usable fuel load of 10500 kg. If the standard mass for the crew is 545 kg the Dry Operating Mass is
42545 kg
56200 kg
42000 kg
41455 kg
18.
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 kgThe traffic load available for this flight is
55 000 kg
55 800 kg
25 800 kg
25 000 kg
19.
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
must be reduced to 81700 kg in order to avoid a high speed approach
is 83200 kg which is in excess of the regulated landing mass and could result in overrunning the runway
is 87300 kg which is acceptable in this case because this is a diversion and not a normal scheduled landing.
20.
When an aeroplane is stationary on the ground, its total weight will act vertically
through the main wheels of its undercarriage assembly
through its centre of gravity
through a point defined as the datum point
through its centre of pressure
21.
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.
22.
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 focal point.
the datum.
the axis
the centre of gravity of the aeroplane
23.
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,
rupture of one or more structural components
a elastic deformation whilst the load was applied, but no permanent distortion
no distortion, permanent or temporary of the structure
a permanent deformation of the structure
24.
Given:Total mass 2900 kgCentre of gravity (cg) location station: 115.0Aft cg limit station: 116.0The maximum mass that can be added at station 130.0 is
207 kg
317 kg.
14 kg
140 kg.
25.
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
29280 kg.
17080 kg
12200 kg.
10080 kg
26.
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.
a point from which all balance arms are measured. The location of this point varies with the distribution of loads on the aeroplane
a point near the centre of the aeroplane. It moves longitudinally as masses are added forward and aft of its location
the point through which the sum of the mass values (of the aeroplane and its contents) is assumed to act vertically
27.
The stalling speed of an aeroplane will be highest when it is loaded with a
low gross mass and aft centre of gravity
high gross mass and aft centre of gravity
low gross mass and forward centre of gravity
high gross mass and forward centre of gravity
28.
An aeroplane is loaded with its centre of gravity towards the rear limit. This will result in
a reduced fuel consumption as a result of reduced drag.
an increased risk of stalling due to a decrease in tailplane moment
a reduction in power required for a given speed.
an increase in longitudinal stability
29.
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
18 170 kg
17 840 kg
13 950 kg
25 800 kg
30.
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?
53 000 kg
71 000 kg
99 000 kg
64 000 kg
31.
The centre of gravity location of the aeroplane is normally computed along the
horizontal axis
longitudinal axis
lateral axis
vertical axis
32.
The centre of gravity of an aeroplane
can be allowed to move between defined limits.
is in a fixed position and is unaffected by aeroplane loading
must be maintained in a fixed position by careful distribution of the load.
may only be moved if permitted by the regulating authority and endorsed in the aeroplane's certificate of airworthiness
33.
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?
73.5 kg
62.5 kg
68.9 kg
65.8 kg
34.
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
38 300 kg
30 300 kg
30 665 kg
30 785 kg
35.
With the centre of gravity on the forward limit which of the following is to be expected?
A tendency to yaw to the right on take-off.
A decrease in the landing speed.
A decrease of the stalling speed
A decrease in range
36.
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
39105 kg
141100 kg
121450 kg
19650 kg
37.
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.
38 kg for all flights
35 kg for all flights
38.
The Dry Operating Mass of a helicopter is the total mass of a helicopter
ready for a specific operation including the crew and traffic load, not including the usable fuel
including the crew, the usable fuel and the specific equipments for the mission and payload
excluding the crew but including specific equipments for the mission and not including the usable fuel
including the crew,the fuel and the specific equipments for the mission but excluding payload
39.
'Standard Mass' as used in the computation of passenger load establish the mass of a child as
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) occupying a seat
35 kg only if they are over 2 years old and 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
40.
The centre of gravity of a body is that point
through which the sum of the forces of all masses of the body is considered to act.
where the sum of the moments from the external forces acting on the body is equal to zero
which is always used as datum when computing moments.
where the sum of the external forces is equal to zero
41.
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
29600 kg
26900 kg.
68400 kg
70700 kg
42.
Which of the following is unlikely to have any effect on the position of the centre of gravity on an aeroplane in flight ?
Movement of cabin attendants going about their normal duties
Lowering the landing gear
Changing the tailplane (horizontal stabiliser) incidence angle
Normal consumption of fuel for a swept wing aeroplane
43.
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 approach path will be steeper and threshold speed higher
the approach path will be steeper
the landing distance will be unaffected
the landing distance required will be longer
44.
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
74 000 kg
70 400 kg
45.
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
1 600 kg
1 550 kg
2 150 kg
46.
In calculations with respect to the position of the centre of gravity a reference is made to a datum. The datum is
a reference plane which is chosen by the aeroplane manufacturer. Its position is given in the aeroplane Flight or Loading Manual.
calculated from the data derived from the weighing procedure carried out on the aeroplane after any major modification
an arbitrary reference chosen by the pilot which can be located anywhere on the aeroplane
calculated from the loading manifest
47.
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
55 500 kg
61 500 kg
55 000 kg
54 000 kg
48.
The maximum certificated take - off mass is
limited by the runway take off distance available. It is tabulated in the Flight Manual
a structural limit which may not be exceeded for any take - off.
a take - off limiting mass which is governed by the gradient of climb after reaching V2
a take - off limiting mass which is affected by the aerodrome altitude and temperature.
49.
The weight of an aeroplane, which is in level non accelerated flight, is said to act
always along the vertical axis of the aeroplane
vertically through the centre of pressure.
vertically through the centre of gravity
vertically through the datum point
50.
Dry Operating Mass is the mass of the aeroplane less
usable fuel and traffic load.
usable fuel
traffic load, potable water and lavatory chemicals
usable fuel, potable water and lavatory chemicals
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