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Exam simulation Mass and Balance - ATPL - Airline Transport Pilot license

Exam simulation ATPL Mass and Balance 120 questions on 120 minutes

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1 - 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
2 - 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
3 - A pallet having a freight platform which measures 200 cm x 250 cm has a total mass of 300 kg. The pallet is carried on two ground supports each measuring 20 cm x 200 cm. Using the loading manual for the transport aeroplane, calculate how much mass may be added to, or must be off loaded from, the pallet in order for the load intensity to match the maximum permitted distribution load intensity for lower deck forward cargo compartment.
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4 - The empty mass of an aircraft is recorded in
5 - The maximum certificated take-off mass is:
6 - Longitudinal CG location can be expressed:
7 - The reference about which centre of gravity moments are taken is the
8 - Which of the following is most likely to affect the range of centre of gravity positions on an aeroplane?
9 - 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
10 - 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
11 - Length of the mean aerodynamic chord = 1 m Moment arm of the forward cargo: -0,50 m Moment arm of the aft cargo: + 2,50 m. The aircraft mass is 2 200 kg and its centre of gravity is at 25% MAC. To move the centre of gravity to 40%, which mass has to be transferred from the forward to the aft cargo hold?
12 - Given: Total mass: 7500 kg. Centre of gravity (cg) location station: 80.5. Aft CG limit station: 79.5. How 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?
13 - The BEM of an aircraft is 30000 kg. Given the following data calculate the DOM: Catering = 300 kg. Crew = 600 kg. Trip Fuel = 1200 kg. Unusable Fuel = 30 kg. Traffic Load = 2500 kg
14 - The centre of gravity of a body is that point
15 - The weight of an aircraft, which is in level non accelerated flight, is said to act
16 - The take-off mass of an aeroplane is 141000 kg. Total fuel on board is 63000 kg including 14000 kg reserve fuel and 1000 kg of unusable fuel. The traffic load is 12800 kg. The zero fuel mass is:
17 - When an aircraft is stationary on the ground, its total weight will act vertically
18 - Refer to CAP 696 Fig. 4.11:At the maximum landing mass the range of safe CG positions, as determined from the appropriate graph in the loading manual, is:
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19 - Mass for individual passengers (to be carried on an aircraft) may be determined from a verbal statement by or on behalf of the passengers if the number of
20 - When preparing to carry out the weighing procedure on an aircraft, which of the following is not required?
21 - The centre of gravity of an aircraft is that point through which the total mass of the aircraft is said to act. The weight acts in a direction
22 - Just prior to departure, you accept 10 passengers additional on board who will be seated in 'compartment OC' and you have 750 kg unloaded from cargo compartment 5. The take-off centre of gravity in MAC % (Mean Aerodynamic Chord) will be located at:
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23 - The centre of gravity of an aircraft
24 - If an aeroplane is at a higher mass than anticipated, for a given airspeed the angle of attack will
25 - For a particular aeroplane, the structural maximum mass without any fuel on board, other than unusable quantities, is:
26 - Given: Standard Empty Mass 1764 lbs. Optional Equipment 35 lbs. Pilot + Passenger 300 lbs. Cargo 350 lbs. Ramp Fuel ( Block Fuel) 60 Gal. Trip Fuel 35 Gal. Taxi Fuel 1.7 Gal. Final Reserve Fuel 18 Gal. Fuel density 6 lbs/Gal. Determine the expected landing mass.
27 - At the flight preparation stage, the following parameters in particular are available for determining the mass of the aircraft: 1- Dry operating mass 2- Operating mass. Which statement is correct:
28 - Which of the following corresponds to zero fuel mass?
29 - The empty mass of an aeroplane is given as 44800 kg. Operational items (including crew standard mass of 1060 kg) are 2300 kg. If the maximum zero fuel mass is given as 65500 kg, the maximum traffic load which could be carried is:
30 - In order to provide an adequate 'buffet boundary' at the commencement of the cruise a speed of 1.3 Vs is used. At a mass of 120000 kg this is a CAS of 180 KT. If the mass of the aeroplane is increased to 135000 kg the value of 1.3 Vs will be:
31 - In relation to an aircraft, the term ' Basic Empty Mass' includes the mass of the aircraft structure complete with its powerplants, systems, furnishings and other items of equipment considered to be an integral part of the particular aircraft configuration. Its value is
32 - The Zero Fuel Mass and the Dry Operating Mass
33 - The maximum quantity of fuel that can be loaded into an aircraft'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:
34 - The datum used for balance calculations is:
35 - Given: Maximum structural take-off mass= 146 900 kg Maximum structural landing mass= 93 800 kg Maximum zero fuel mass= 86 400 kg. Trip fuel= 27 500 kg. Block fuel= 35 500 kg. Engine starting and taxi fuel = 1 000 kg. The maximum take-off mass is equal to:
36 - 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
37 - In calculations with respect to the position of the centre of gravity a reference is made to a datum. The datum is
38 - The centre of gravity location of the aeroplane is normally computed along the:
39 - An aeroplane is loaded with its centre of gravity towards the rear limit. This will result in:
40 - 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:
41 - A mass of 500 kg is loaded at a station which is located 10 metres behind the present Centre of Gravity and 16 metres behind the datum. (Assume: g = 10 m/s²). The moment for that mass used in the loading manifest is:
42 - Comparing a forward CG position with an aft one, the forward cg position will cause a
43 - An aeroplane is weighed and the following recordings are made: nose wheel assembly scale 5330 kgleft main wheel assembly scale 12370 kg right main wheel assembly scale 12480 kgIf 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
44 - An aeroplane is said to be 'neutrally stable'. This is likely to:
45 - What effect has a centre of gravity close to the most forward limit?
46 - 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
47 - Conversion of fuel volume to mass
48 - Overloading has the following effects on performance:
49 - When has the centre of gravity to be computed?
50 - The total mass of an aeroplane is 145000 kg and the centre of gravity limits are between 4.7 m and 6.9 m aft of the datum. The loaded centre of gravity position is 4.4 m aft. How much mass must be transferred from the front to the rear hold in order to bring the out of limit centre of gravity position to the foremost limit:
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51 - 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?
52 - Given: The take-off mass of an aircraft is 8470 kg. Total fuel on board is 1600 kg including 450 kg reserve fuel and 29 kg of unusable fuel The traffic load is 770 kg. What is the Zero Fuel Mass?
53 - The mass of an item multiplied by its distance from the datum is its
54 - The floor of the main cargo hold is limited to 4000 N/m². It is planned to load a cubic container each side of which measures 0.5 m. Its maximum gross mass must not exceed: (assume g = 10 m/s²)
55 - The Dry Operating Mass is the total mass of the aircraft ready for a specific type of operation but excluding
56 - In mass and balance calculations which of the following describes the datum?
57 - Which is true of the aircraft basic empty mass?
58 - For the purpose of aeroplane mass and balance calculations, the datum point is defined as:
59 - Given the following data calculate the CG as a %MAC when 12000N of last minute cargo is added to a hold 10m from the datum: AUM 460000N. LEMac 14m from datum. MAC 4.6m. Current CG 15.4m from datum
60 - If individual masses are used, the mass of an aircraft must be determined prior to initial entry into service and thereafter
61 - Traffic Load is the:
62 - The maximum zero-fuel mass: 1- is a regulatory limitation 2- is calculated for a maximum load factor of +3.5 g 3- is based on the maximum permissible bending moment at the wing root 4- is defined on the assumption that fuel is consumed from the outer wings tank first 5- is defined on the assumption that fuel is consumed from the centre wing tank first The combination of correct statements is:
63 - The mass displacement caused by landing gear extension:
64 - 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?
65 - Prior to departure an aircraft is loaded with 16500 litres of fuel at a fuel density of 780 kg/m3. This is entered into the load sheet as 16500 kg and calculations are carried out accordingly. As a result of this error, the aircraft is
66 - If the centre of gravity is near the forward limit the aeroplane will:
67 - The actual 'Zero Fuel Mass' is equal to the:
68 - With respect to a single-engine piston powered aeroplane, determine the zero fuel moment (lbs. In./100) in the following conditions: Basic Empty Mass: 2415 lbs. Arm at Basic Empty Mass: 77,9 In. Cargo Zone A: 350 lbs. Baggage Zone B: 35 lbs. Pilot and front seat passenger: 300 lbs (total)
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69 - A jet aeroplane, with the geometrical characteristics shown in the appendix, has a take-off weight (W) of 460 000 N and a centre of gravity (point G on annex) located at 15.40 m from the zero reference point. At the last moment the station manager has 12 000 N of freight added in the forward compartment at 10 m from the zero reference point. The final location of the centre of gravity, calculated in percentage of mean aerodynamic chord AB (from point A), is equal to:
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70 - The Maximum Zero Fuel Mass is the mass of the aeroplane with no usable fuel on board. It is a limitation which is:
71 - To measure the mass and CG-position of an aircraft, it should be weighed with a minimum of:
72 - The floor limit of an aircraft cargo hold is 5000 N/m². It is planned to load-up a cubic container measuring 0,4 m of side. Its maximum gross mass must not exceed: (assume g = 10 m/s²)
73 - The total mass of an aircraft 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?
74 - In determining the Dry Operating Mass of an aeroplane it is common practice to use 'standard mass' values for crew. These values are
75 - Given: Total mass 2900 kg. Centre of gravity (cg) location station: 115. Aft CG limit station: 116. The maximum mass that can be added at station 130 is:
76 - 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 kg Maximum Take-off mass 89430 kg Maximum Landing mass 71520 kg Actual Zero fuel mass 62050 kg Fuel on board at ramp: Taxi fuel 600 kg Trip fuel 17830 kg. Contingency, final reserve and alternate 9030 kg. If the Dry Operating Mass is 40970 kg the traffic load that can be carried on this flight is
77 - 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 the datum.
78 - 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 kg. The actual take-off mass can never be higher than:
79 - On an aeroplane without central fuel tank, the maximum Zero Fuel Mass is related to:
80 - Calculate the centre of gravity in % MAC (mean aerodynamic chord) with following data: Distance datum - centre of gravity: 12.53 m. Distance datum - leading edge: 9.63 m Length of MAC: 8 m
81 - Traffic load is the difference between:
82 - Assuming gross mass, altitude and airspeed remain unchanged, movement of the centre of gravity from the forward to the aft limit will cause:
83 - The maximum mass to which an aeroplane may be loaded, prior to engine start, is:
84 - 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:
85 - The term 'useful load' as applied to an aircraft includes
86 - What determines the longitudinal stability of an aeroplane?
87 - Fuel loaded onto an aeroplane is 15400 kg but is erroneously entered into the load and trim sheet as 14500 kg. This error is not detected by the flight crew but they will notice that
88 - Considering only structural limitations, on long distance flights (at the aeroplane's maximum range), the traffic load is normally limited by:
89 - Given: Maximum structural take-off mass: 7400 kg Maximum structural landing mass: 7400 kg Zero Fuel Mass: 5990 kg. Taxi Fuel: 15 kg. Contingency Fuel: 110 kg. Alternate Fuel: 275 kg. Final Reserve Fuel: 250 kg. Trip Fuel: 760 kg. The expected Landing Mass at destination will be:
90 - For the purpose of completing the Mass and Balance documentation, the Operating Mass is considered to be Dry Operating Mass plus
91 - Which of the following is unlikely to have any effect on the position of the centre of gravity on an aeroplane in flight?
92 - The maximum quantity of fuel that can be loaded into an aircraft's tanks is given as 400 US Gallons. If the fuel density (specific gravity) is given as 0.79 the mass of fuel which may be loaded is:
93 - From the loading manual for the transport aeroplane, the aft cargo compartment has a maximum total load of:
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94 - A load placed aft of the datum:
95 - 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 kg. Knowing 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 kg. The maximum cargo load that the captain may decide to load on board is:
96 - Aviation fuel F 34 has a density of 0.78 kg/l. What mass should be entered if 170 l are refuelled?
97 - The Maximum Zero Fuel Mass is a structural limiting mass. It is made up of the aeroplane Dry Operational mass plus
98 - Allowed traffic load is the difference between:
99 - When establishing the mass breakdown of an aeroplane, the empty mass is defined as the sum of the:
100 - 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:
101 - Aeroplane Dry Operating mass 85000 kg Performance limited take-off mass 127000 kg Performance limited landing mass 98500 kg Maximum zero fuel mass 89800 kg. Fuel requirements for flight - Trip fuel 29300 kg. Contingency and final reserve fuel 3600 kg. Alternate fuel 2800 kg. The maximum traffic load that can be carried on this flight is:
102 - A location in the aircraft which is identified by a number designating its distance from the datum is known as:
103 - 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
104 - The Maximum Certificated Taxi (or Ramp) Mass is that mass to which an aeroplane may be loaded prior to engine start. It is:
105 - For the medium range transport aeroplane, from the loading manual, determine the maximum total volume of fuel which can be loaded into the main wing tanks. (Fuel density value 0.78)
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106 - 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 masses are not performance limited. Dry Operating Mass: 34 930 kgTrip Fuel: 11 500 kg Taxi Fuel: 250 kgContingency & final reserve fuel: 1 450 kg Alternate Fuel: 1 350 kg. The maximum traffic load that can be carried is:
107 - The actual 'Take-off Mass' is equivalent to:
108 - Dry Operating Mass is the mass of the aircraft less
109 - With respect to multi-engine piston powered aeroplane, determine the ramp mass (lbs) in the following conditions: Basic empty mass: 3 210 lbs Basic arm: 88.5 Inches. One pilot: 160 lbs. Front seat passenger: 200 lbs. Centre seat passengers: 290 lbs. 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.
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110 - An aircraft may be weighed
111 - The operating mass of an aeroplane is:
112 - The maximum zero fuel mass is a mass limitation for the:
113 - In mass and balance calculations the 'index' is:
114 - Given the following data how much cargo must be moved from the forward hold to the aft hold to achieve a CG at 33% MAC?AUM 200000kg. Forward Hold Cargo 6500kg. Aft hold Cargo 4000kg. Distance between holds 10m. Current CG: 30%MAC. MAC 4.6m
115 - Knowing that: Dry operating mass: 110000 kg. Basic index: 119.1. Number of passengers: 185 distributed as shown in the annex (75 kg per PAX). Cargo load + luggage: 14000 kg distributed as shown in the annex. Fuel: 42000 kg (Fuel shift -20). Stages (1) to (7) and (11) having already been calculated, the centre of gravity in % MAC (Mean Aerodynamic Chord) at take-off is located at:
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116 - During take-off you notice that, for a given elevator input, the aeroplane rotates much more rapidly than expected. This is an indication that:
117 - The centre of gravity is the
118 - The maximum floor loading for a cargo compartment in an aircraft 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?
119 - With respect to aeroplane loading in the planning phase, which of the following statements is always correct? LM = Landing Mass. TOM = Take-off Mass. MTOM = Maximum Take-off Mass. ZFM = Zero Fuel Mass. MZFM = Maximum Zero Fuel Mass. DOM = Dry Operating Mass
120 - Contrary to the loading sheet forecasts you have: Cargo compartment 1: empty. Cargo compartment 2: 1000 kg. Cargo compartment 3: 3000 kg. Cargo compartment 4: 2000 kg. Cargo compartment 5: 1000 kg. Passengers in compartment OA: 20. Passengers in compartment OB: 20. Passengers in compartment OC: 30. The take-off centre of gravity in MAC % (Mean Aerodynamic Chord), will be located at:
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