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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 - 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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2 - 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?
3 - 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
4 - 'Standard Mass' as used in the computation of passenger load establish the mass of a child as
5 - 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
6 - For the purpose of completing the Mass and Balance documentation, the Operating Mass is considered to be Dry Operating Mass plus
7 - 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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8 - 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
9 - Longitudinal CG location can be expressed:
10 - 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:
11 - While making mass and balance calculation for a particular aircraft, the term 'Basic Empty Mass' applies to the sum of airframe, engine(s), fixed ballast plus
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 - If individual masses are used, the mass of an aircraft must be determined prior to initial entry into service and thereafter
14 - When the centre of gravity is at the forward limit, an aeroplane will be:
15 - If the centre of gravity is near the forward limit the aeroplane will:
16 - 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
17 - 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
18 - 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:
19 - What effect has a centre of gravity close to the most forward limit?
20 - When an aircraft is stationary on the ground, its total weight will act vertically
21 - 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:
22 - For a particular aeroplane, the structural maximum mass without any fuel on board, other than unusable quantities, is:
23 - Traffic Load is the:
24 - The zero fuel mass of an aeroplane is always:
25 - Considering only structural limitations, on very short legs with minimum take-off fuel, the Traffic Load is normally limited by:
26 - If an aeroplane is at a higher mass than anticipated, for a given airspeed the angle of attack will
27 - Which one of the following is correct?
28 - What are the standard masses used for crew?
29 - Which of the following is most likely to affect the range of centre of gravity positions on an aeroplane?
30 - 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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31 - 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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32 - 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
33 - The Dry Operating Mass is the total mass of the aircraft ready for a specific type of operation but excluding
34 - For the purpose of completing the Mass and Balance documentation, the Traffic Load is considered to be equal to the Take-off Mass
35 - The Basic Empty Mass is 4960 kg, the Dry Operating Mass is 5220 kg and the Zero Fuel Mass is 6040 kg. If the take-off mass is 7630 kg the useful load is
36 - The maximum quantity of fuel that can be loaded into an aircraft's tanks is given as 2200 l. If the fuel density (specific gravity) is given as 0.79 the mass of fuel which may be loaded is:
37 - 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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38 - The Maximum Taxi (Ramp) Mass is governed by:
39 - An aircraft basic empty mass is 3000 kg. The maximum take-off, landing, and zero-fuel mass are identical, at 5200 kg. Ramp fuel is 650 kg, the taxi fuel is 50 kg. The maximum traffic load is:
40 - Where is the centre of gravity of the aeroplane in the diagram?
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41 - 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
42 - 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?
43 - 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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44 - 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?
45 - 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:
46 - The empty mass of an aircraft is recorded in
47 - 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.
48 - What determines the longitudinal stability of an aeroplane?
49 - The mass displacement caused by landing gear extension:
50 - Allowed traffic load is the difference between:
51 - The actual 'Zero Fuel Mass' is equal to the:
52 - When establishing the mass breakdown of an aeroplane, the empty mass is defined as the sum of the:
53 - From the loading manual for the transport aeroplane, the aft cargo compartment has a maximum total load of:
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54 - The Dry Operating Mass includes:
55 - Regarding centre of gravity position and longitudinal stability, which of the following statements is correct?
56 - Assuming gross mass, altitude and airspeed remain unchanged, movement of the centre of gravity from the forward to the aft limit will cause:
57 - An aircraft 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'?
58 - The mass of an aircraft is 1950 kg. If 450 kg is added to a cargo hold 1.75 metres from the loaded centre of gravity (cg). The loaded cg will move:
59 - 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:
60 - For a given configuration, the stall speed of an aeroplane will be highest when loaded:
61 - 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
62 - 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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63 - When has the centre of gravity to be computed?
64 - Given are the following information at take-off ____________________________________________________________ STATION....................MASS (kg)....ARM (cm)....MOMENT (kgcm) ____________________________________________________________ Basic Empty Condition...12045.........+30......+361350 Crew..................................145........-160.......-23200 Freight (1)..........................570.......+200......+114000 Freight (2)..........................410..........-40.......-16400 Fuel.................................6045...........-8.......-48360 Given that the flight time is 2 h and the estimated fuel flow will be 1050 litres per h. The specific density of fuel is 0.79. The 'Freight (2)' will be dropped during flight within the scope of a rescue action. Calculate the CG position at landing.
65 - The Maximum Zero Fuel Mass is a structural limiting mass. It is made up of the aeroplane Dry Operational mass plus
66 - During take-off you notice that, for a given elevator input, the aeroplane rotates much more rapidly than expected. This is an indication that:
67 - 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:
68 - On an aeroplane without central fuel tank, the maximum Zero Fuel Mass is related to:
69 - The Maximum Zero Fuel Mass is the mass of the aeroplane with no usable fuel on board. It is a limitation which is:
70 - The Basic Empty Mass is 4800 kg, the Dry Operating Mass is 5050 kg and the Zero Fuel Mass is 6210 kg. If the take-off mass is 8010 kg the useful load is:
71 - In calculations with respect to the position of the centre of gravity a reference is made to a datum. The datum is
72 - 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:
73 - A load placed forward of the datum
74 - 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:
75 - Moment (balance) arms are measured from a specific point to the body station at which the mass is located. That point is known as
76 - 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:
77 - The maximum mass to which an aeroplane may be loaded, prior to engine start, is:
78 - An aeroplane is loaded with its centre of gravity towards the rear limit. This will result in:
79 - The mass of an item multiplied by its distance from the datum is its
80 - 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?
81 - Which of the following is unlikely to have any effect on the position of the centre of gravity on an aeroplane in flight?
82 - To calculate a allowable take-off mass, the factors to be taken into account include:
83 - 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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84 - For the purpose of aeroplane mass and balance calculations, the datum point is defined as:
85 - The responsibility for determination of the mass of 'operating items' and 'crew members' included within the Dry Operating Mass lies with
86 - Conversion of fuel volume to mass
87 - 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.
88 - The reference about which centre of gravity moments are taken is the
89 - To measure the mass and CG-position of an aircraft, it should be weighed with a minimum of:
90 - An aeroplane is said to be 'neutrally stable'. This is likely to:
91 - When considering the effects of increased mass on an aeroplane, which of the following is true?
92 - Comparing a forward CG position with an aft one, the forward cg position will cause a
93 - Aviation fuel F 34 has a density of 0.78 kg/l. What mass should be entered if 170 l are refuelled?
94 - The standard mass for a child is
95 - 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
96 - 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?
97 - 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
98 - 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)
99 - For the purpose of completing the Mass and Balance documentation, the Dry Operating Mass is defined as:
100 - The maximum load per running metre of an aircraft is 350 kg / m. The width of the floor area is 2 metres. The floor strength limitation is 300 kg per square metre. Which one of the following crates (length x width x height) can be loaded directly on the floor?
101 - In mass and balance calculations which of the following describes the datum?
102 - An aeroplane with a two wheel nose gear and four main wheels rests on the ground with a single nose wheel load of 500 kg and a single main wheel load of 6000 kg. The distance between the nose wheels and the main wheels is 10 m. How far is the centre of gravity in front of the main wheels?
103 - 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
104 - 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:
105 - 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
106 - From the Loading Manual for the transport aeroplane, the maximum load that can be carried in that section of the aft cargo compartment which has a balance arm centroid at:
question meb2.webp
107 - The actual 'Take-off Mass' is equivalent to:
108 - In determining the Dry Operating Mass of an aeroplane it is common practice to use 'standard mass' values for crew. These values are
109 - The maximum zero fuel mass is a mass limitation for the:
110 - Dry Operating Mass is the mass of the aircraft less
111 - 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
112 - Traffic load is the difference between:
113 - 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.
114 - 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 kg The traffic load available for this flight is:
115 - In mass and balance calculations the 'index' is:
116 - 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:
117 - 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:
118 - The term 'useful load' as applied to an aircraft includes
119 - 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?
120 - In cruise flight, a centre of gravity moving aft will:
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