Test 120 exam questions on Mass and Balance for ATPL

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1 - 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: 56200 kg 42000 kg 42545 kg 41455 kg

2 - What are the standard masses used for crew? 88 kgs for flight crew, 76 kgs cabin crew, not including baggage 85 kgs for flight crew, 75 kgs cabin crew, not including hand baggage 88 kgs for flight crew, 76 kgs cabin crew, including baggage. 85 kgs for flight crew, 75 kgs cabin crew, including hand baggage

3 - Given are the following information at take-off____________________________________________________________ STATION....................MASS (kg)....ARM (cm)....MOMENT (kgcm)____________________________________________________________ Basic Empty Condition...12045.........+30......+361350Crew..................................145........-160.......-23200Freight ( 1)..........................570.......+200......+114000Freight ( 2)..........................410..........-40.......-16400Fuel.................................6045...........-8.......-48360Given 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. 25 cm aft of datum 24.3 cm aft of datum 23.7 cm aft of datum 22 cm aft of datum

4 - 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 Always parallel to the aircraft's vertical axis. Parallel to the gravity vector. Governed by the distribution of the mass within the aircraft. At right angles to the flight path.

5 - Traffic load is the difference between: The operating mass and the basic empty mass. The take-off mass and the basic empty mass. The take-off mass and the basic empty mass plus trip fuel. The take-off mass and the operating mass.

6 - If nose wheel moves aft during gear retraction, how will this movement affect the location of the centre of gravity (CG) on the aircraft? It will cause the CG to move aft. The CG location will change, but the direction cannot be told from the information given. It will cause the CG to move forward. It will not affect the CG location.

7 - . The Traffic Load is defined as: The total mass of passengers, baggage, cargo and usable fuel The total mass of flight crew, passengers, baggage, cargo and usable fuel The total mass of passengers, baggage and cargo, including any non revenue load The total mass of crew and passengers excluding any baggage or cargo

8 - Given that:- Maximum structural take-off mass: 146 000 kg- Maximum structural landing mass: 93 900 kg- Maximum zero fuel mass: 86 300 kg- Trip fuel: 27 000 kg- Taxi fuel: 1 000 kg- Contingency fuel: 1350 kg- Alternate fuel: 2650 kg- Final reserve fuel: 3000 kgThe actual TOM can never be higher than: 120 900 kg. 146 000 kg. 121 300 kg. 120 300 kg.

9 - 'Standard Mass' as used in the computation of passenger load establish the mass of a child as 35 kg only if they are over 2 years old and occupy a seat. 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 for children over 2 years occupying a seat and 10 kg for infants (less than 2 years) not occupying a seat.

10 - . The operating mass of an aeroplane is: The empty mass plus crew, crew baggage and catering. The empty mass plus the take-off fuel mass. The empty mass plus the trip fuel mass. The dry operating mass plus the take-off fuel mass.

11 - 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 traffic load for this aeroplane is 11980 kg. 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.

12 - Given:Maximum structural take-off mass: 7400 kg Maximum structural landing mass: 7400 kg Zero Fuel Mass: 5990 kgTaxi Fuel: 15 kg Contingency Fuel: 110 kg Alternate Fuel: 275 kg Final Reserve Fuel: 250 kg Trip Fuel: 760 kgThe expected Landing Mass at destination will be: 7385 kg 7400 kg 6625 kg 7135 kg

13 - The distance from the datum to the Centre of Gravity of a mass is known as The moment arm or balance arm. The index. The moment. The force.

14 - 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 mThe aircraft mass is 2 200 kg and its centre of gravity is at 25% MACTo move the centre of gravity to 40%, which mass has to be transferred from the forward to the aft cargo hold? 110 kg 104 kg 165 kg 183 kg

15 - The responsibility for determination of the mass of 'operating items' and 'crew members' included within the Dry Operating Mass lies with The authority of the state of registration. The commander. The person compiling the weighing schedule. The operator.

16 - The maximum zero-fuel mass: 1- is a regulatory limitation2- is calculated for a maximum load factor of +3.5 g3- is based on the maximum permissible bending moment at the wing root4- 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: 1, 3, 5 2, 3, 4 2, 3, 5 1, 2, 3

17 - 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=10m/s 2) 1000 kg 100 kg 5000 kg 500 kg

18 - 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 massWhich statement is correct: The operating mass is the mass of the aircraft without take-off fuel. The dry operating mass includes take-off fuel. The dry operating mass includes fixed equipment needed to carry out a specific flight. The operating mass includes the traffic load.

19 - 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/s 2) 80 kg 320 kg 32 kg 800 kg

20 - 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? 64 000 kg 53 000 kg 99 000 kg 71 000 kg

21 - 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 14 kg per passenger. 13 kg per passenger. 11 kg per passenger. 15 kg per passenger.

22 - 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:

16.9 %. 27.5 %. 35.5 %. 30.4 %.

23 - The term 'Maximum Zero Fuel Mass' consist of: The maximum permissible mass of an aeroplane with no usable fuel. The maximum mass for some aeroplanes including the fuel load and the traffic load The maximum mass authorized for a certain aeroplane not including the fuel load and operational items The maximum mass authorized for a certain aeroplane not including traffic load and fuel load.

24 - 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 (1 1) having already been calculated, the centre of gravity in % MAC (Mean Aerodynamic Chord) at take-off is located at:

26.0 % 28.0 % 32.5 % 33.5 %

25 - . Traffic load is the difference between: The operating mass and the basic empty mass. The take-off mass and the basic empty mass. The take-off mass and the basic empty mass plus trip fuel. The take-off mass and the operating mass.

26 - The Dry Operating Mass includes: Crew and crew baggage, catering, removable passenger service equipment, potable water and lavatory chemicals. Passengers baggage and cargo. Fuel and passengers baggage and cargo. Unusable fuel and reserve fuel.

27 - To calculate a allowable take-off mass, the factors to be taken into account include: The sum of the maximum landing mass and the fuel on board at take-off. The sum of the maximum zero fuel mass and the trip fuel. The sum of the maximum landing mass and the trip fuel. The maximum take-off mass minus the trip fuel.

28 - In mass and balance calculations which of the following describes the datum? It is the most forward position of the centre of gravity. It is the most aft position of the centre of gravity. It is the point on the aircraft designated by the manufacturers from which all centre of gravity measurements and calculations are made. It is the distance from the centre of gravity to the point through which the weight of the component acts.

29 - Basic Empty Mass is: Dry Operating Mass minus fuel load. Dry Operating Mass minus traffic load. A component of Dry Operating Mass. The actual take-off mass minus traffic load.

30 - 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 InchesOne pilot: 160 lbsFront seat passenger: 200 lbs Centre seat passengers: 290 lbs One passenger rear seat: 110 lbs Baggage in zone 1: 100 lbsBaggage 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.

4120 4390 4720 4372

31 - When preparing to carry out the weighing procedure on an aircraft, which of the following is not required? Drain all chemical toilet fluid tanks. Drain all usable fuel. Removable passenger services equipment to be off-loaded. Drain all engine tank oil.

32 - 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? 40 cm 41.6 cm 4 m 25 cm

33 - 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:

Forward limit 7.4% MAC aft limit 27.0% MAC Forward limit 8.0% MAC aft limit 26.8% MAC Forward limit 8.6% MAC aft limit 27.0% MAC Forward limit 8.0% MAC aft limit 27.2% MAC

34 - 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: 23000 kg 20700 kg 19460 kg. 18400 kg

35 - If individual masses are used, the mass of an aircraft must be determined prior to initial entry into service and thereafter Only if major modifications have taken place. At regular annual intervals. At intervals of 9 years. At intervals of 4 years if no modifications have taken place.

36 - 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 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 21080 kg 20870 kg 21220 kg

37 - The Dry Operating Mass is the total mass of the aircraft ready for a specific type of operation but excluding Usable fuel and traffic load. Usable fuel, potable water and lavatory chemicals. Potable water and lavatory chemicals. Usable fuel and crew.

38 - . Allowed traffic load is the difference between: Allowed take off mass and basic empty mass. Allowed take off mass and basic empty mass plus trip fuel. Operating mass and basic empty mass. Allowed take off mass and operating mass.

39 - Where is the centre of gravity of the aeroplane in the diagram?

26.57 cm forward of datum. 32.29 cm aft of datum. 26.57 cm aft of datum. 32.29 cm forward of datum.

40 - 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: 79000 kg 65200 kg. 93000 kg 78000 kg

41 - 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 kg Taxi Fuel: 250 kgContingency & final reserve fuel: 1 450 kg Alternate Fuel: 1 350 kgThe maximum traffic load that can be carried is: 21 070 kg 21 170 kg 20 420 kg 17 810 kg

42 - 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. Whenever a major modification is carried out. Whenever the Certificate of Airworthiness is renewed. 4 years for each aeroplane.

43 - . The mass of an item multiplied by it's distance from the datum is it's Moment Force Moment arm Centre of gravity

44 - 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 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. All the oil and fuel. Unusable fuel and full operating fluids.

45 - 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:

835.5 inches is 6752 kg 835.5 inches is 3062 kg 421.5 inches is 2059 lbs 421.5 inches is 4541 kg

46 - Which of the following is most likely to affect the range of centre of gravity positions on an aeroplane? Location of the undercarriage. The need to maintain a low value of stalling speed. Elevator and tailplane (horizontal stabiliser) effectiveness in all flight conditions. The need to minimise drag forces and so improve efficiency.

47 - The centre of gravity of a body is that point Where the sum of the moments from the external forces acting on the body is equal to zero Through which the sum of the forces of all masses of the body is considered to act Which is always used as datum when computing moments Where the sum of the external forces is equal to zero

48 - From the data contained in the attached appendix, the maximum allowable take - off mass and traffic load is respectively: 61600 kg and 12150 kg 60425 kg and 10975 kg 66770 kg and 17320 kg 68038 kg and 18588 kg[see Annex]

49 - 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/s^ 2)The moment for that mass used in the loading manifest is: 50000 Nm 80000 Nm 130000 Nm 30000 Nm

50 - The maximum zero fuel mass is a mass limitation for the: Strength of the fuselage Strength of the wing root Total load of the fuel imposed upon the wing Allowable load exerted upon the wing considering a margin for fuel tanking

51 - 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 a shorter stop distance. A landing short resultant from the increased angle of approach due to the very high aeroplane mass. A high threshold speed and possible undercarriage or other structural failure.

52 - maximum take-off mass is: 4 200 kg 4 100 kg 4 700 kg 4 300 kg

53 - 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? 30.0 kg 900 kg 196 kg 300 kg

54 - 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 may use the standard masses for the load and balance calculation without correction The operator may use the standard masses for the balance but must correct these for the load calculation The operator should use the individual masses of the passengers or alter the standard mass The operator is obliged to use the actual masses of each passenger

55 - 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 200000kgForward Hold Cargo 6500kg Aft hold Cargo 4000kg Distance between holds 10m Current CG: 30%MACMAC 4.6m 6000kg 2904kg 1467kg 2760kg

56 - Given:The take-off mass of an aircraft is 8470 kgTotal fuel on board is 1600 kg including 450 kg reserve fuel and 29 kg of unusable fuel The traffic load is 770 kgWhat is the Zero Fuel Mass? 6899 kg 6420 kg 6129 kg 6870 kg

57 - When establishing the mass breakdown of an aeroplane, the empty mass is defined as the sum of the: Basic mass plus variable equipment mass Empty mass dry plus variable equipment mass Basic mass plus special equipment mass Standard empty mass plus specific equipment mass plus trapped fluids plus unusable fuel mass

58 - 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 84 kg 88 kg (male) 74 kg (female). 84 kg (male) 76 kg (female).

59 - 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 landing distance required will be longer. The approach path will be steeper and threshold speed higher. The approach path will be steeper.

60 - The centre of gravity of an aircraft Is in a fixed position and is unaffected by aircraft loading. May only be moved if permitted by the regulating authority and endorsed in the aircraft's certificate of airworthiness. Must be maintained in a fixed position by careful distribution of the load. Can be allowed to move between defined limits.

61 - Loads must be adequately secured in order to: Avoid unplanned centre of gravity (CG) movement and aircraft damage. Prevent excessive g-loading during the landing flare. Avoid any centre of gravity (CG) movement during flight. Allow steep turns.

62 - 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: Increased to 191 KT, drag will increase and air distance per kg of fuel will decrease. Increased to 202 KT but, since the same angle of attack is used, drag and range will remain the same. Increased to 191 KT, drag will decrease and air distance per kg of fuel will increase. Unaffected as Vs always occurs at the same angle of attack.

63 - 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 Lighter than anticipated and the calculated safety speeds will be too low Lighter than anticipated and the calculated safety speeds will be too high Heavier than anticipated and the calculated safety speeds will be too low. Heavier than anticipated and the calculated safety speeds will be too high

64 - 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.

28.5 kg must be off loaded. 28.5 kg may be added. 285.5 kg may be added. 158.3 kg must be off loaded.

65 - . The centre of gravity is the Centre of thrust along the longitudinal axis, in relation to a datum line Point where all the aircraft mass is considered to be concentrated Neutral point along the longitudinal axis, in relation to a datum line Focus along the longitudinal axis, in relation to a datum line

66 - A aeroplane has a landing mass of 53 000kg. The range of safe CG positions, as determined from the appropriate graph in the loading manual, is: Forward limit 7.8% MAC aft limit 27.0% MAC Forward limit 8.7% MAC aft limit 26.8% MAC Forward limit 7.3% MAC aft limit 26.8% MAC Forward limit 8.2% MAC aft limit 27.0% MAC[see Annex]

67 - 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: 1738 kg 1798 kg 2098 kg 2785 kg

68 - Considering only structural limitations, on very short legs with minimum take-off fuel, the Traffic Load is normally limited by: Maximum Zero Fuel Mass. Actual Landing Mass. Maximum Take-off Mass. Maximum Landing Mass.

69 - For the purpose of completing the Mass and Balance documentation, the Operating Mass is considered to be Dry Operating Mass plus Ramp (Block) Fuel Mass. Trip Fuel Mass. Take-off Fuel Mass. Ramp Fuel Mass less the fuel for APU and run-up.

70 - 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 %

71 - Dry Operating Mass is the mass of the aircraft less Usable fuel and traffic load. Usable fuel, potable water and lavatory chemicals. Traffic load, potable water and lavatory chemicals. Usable fuel.

72 - The datum used for balance calculations is: Chosen on the longitudinal axis of the aeroplane, and necessarily situated between the nose and the tail of the aircraft Chosen on the longitudinal axis of the aeroplane, but not necessarily between the nose and the tail of the aircraft Chosen on the longitudinal axis of the aircraft, and always at the fire-wall level Chosen on the longitudinal axis of the aircraft and necessarily situated between the leading edge and trailing edge of the wing

73 - To measure the mass and CG-position of an aircraft, it should be weighed with a minimum of: 3 points of support 4 point of support 1 point of support 2 points of support

74 - 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 mean aerodynamic chord in relation to the datum The mean aerodynamic chord in relation to the trailing edge The aeroplane in relation to the leading edge The mean aerodynamic chord in relation to the leading edge

75 - 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. 10080 kg. 12200 kg. 17080 kg

76 - 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. 62.5 kg. 73.5 kg. 68.9 kg.

77 - 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' ? The Operator. The commander of the aircraft. The aircraft manufacturer or supplier. The appropriate Aviation Authority.

78 - The centre of gravity is the Centre of thrust along the longitudinal axis, in relation to a datum line Point where all the aircraft mass is considered to be concentrated Neutral point along the longitudinal axis, in relation to a datum line Focus along the longitudinal axis, in relation to a datum line

79 - The weight of an aircraft, which is in level non accelerated flight, is said to act Vertically through the centre of pressure. Vertically through the centre of gravity. Always along the vertical axis of the aircraft. Vertically through the datum point.

80 - . Basic Empty Mass is: Dry Operating Mass minus fuel load. Dry Operating Mass minus traffic load. A component of Dry Operating Mass. The actual take-off mass minus traffic load.

81 - 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 aircraft manufacturer. Its position is given in the aircraft Flight or Loading Manual. Calculated from the data derived from the weighing procedure carried out on the aircraft after any major modification. An arbitrary reference chosen by the pilot which can be located anywhere on the aircraft. Calculated from the loading manifest.

82 - Considering only structural limitations, on long distance flights (at the aeroplane's maximum range), the traffic load is normally limited by: The maximum zero fuel mass. The maximum take-off mass. The maximum landing mass. The maximum zero fuel mass plus the take-off mass.

83 - 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 centre of pressure is aft of the centre of gravity. The centre of gravity is too far forward. The aeroplane is overloaded.

84 - . The moment for an item is The mass of the item divided by it's distance from the datum The mass of the item multiplied by it's distance from the datum The square of the distance the item is from the datum divided by it's mass The distance the item is from the datum divided by it's mass

85 - Which of the following is unlikely to have any effect on the position of the centre of gravity on an aeroplane in flight ? Changing the tailplane (horizontal stabiliser) incidence angle. Normal consumption of fuel for a swept wing aeroplane. Movement of cabin attendants going about their normal duties. Lowering the landing gear.

86 - If the centre of gravity is near the forward limit the aeroplane will: Benefit from reduced drag due to the decrease in angle of attack. Require less power for a given airspeed. Require elevator trim which will result in an increase in fuel consumption. Tend to over rotate during take-off.

87 - 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.

88 - . Overloading has the following effects on performance: Reduced take off and landing distance, increased VNE and increased fuel consumption Increased take off and landing distance, increased rate of climb and increased fuel consumption Reduced take off and landing distance, increased VNE and reduced rate of climb Increased take off and landing distance, reduced rate of climb and increased fuel consumption

89 - Which of the following statements is correct? If the actual centre of gravity is located behind the aft limit of centre of gravity it is possible that the aeroplane will be unstable, making it necessary to increase elevator forces A tail heavy aeroplane is less stable and stalls at a lower speed than a nose heavy aeroplane The lowest stalling speed is obtained if the actual centre of gravity is located in the middle between the aft and forward limit of centre of gravity If the actual centre of gravity is close to the forward limit of the centre of gravity the aeroplane may be unstable, making it necessary to increase elevator forces

90 - 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: 3210 kg 2960 kg 1160 kg 1800 kg

91 - On an aeroplane without central fuel tank, the maximum Zero Fuel Mass is related to: The bending moment at the wing root. Variable equipment for the flight. Wing loaded trip fuel. Maximum Structural Take-Off Mass.

92 - When the centre of gravity is at the forward limit, an aeroplane will be: Extremely stable and require small elevator control to change pitch. Extremely stable and will require excessive 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.

93 - Given:Total mass 2900 kgCentre of gravity (cg) location station: 115 Aft cg limit station: 116The maximum mass that can be added at station 130 is: 140 kg. 317 kg. 14 kg. 207 kg.

94 - . What effect has a centre of gravity close to the most forward limit? A better rate of climb capability. A reduction in the specific fuel consumption. A reduced rate of climb capability. A decreased induced drag.

95 - A location in the aircraft which is identified by a number designating its distance from the datum is known as: Station. Index. MA Moment.

96 - Longitudinal CG location can be expressed: As a percentage of the MAC from its trailing edge. As a percentage of the MAC from its leading edge. With respect to the centre of pressure. With respect to the neutral point.

97 - For a particular aeroplane, the structural maximum mass without any fuel on board, other than unusable quantities, is: A variable value which is governed by the payload carried. A fixed value which is stated in the Aeroplane Operating Manual. A fixed value which will limit the amount of fuel carried. A variable value which may limit the payload carried.

98 - The centre of gravity location of the aeroplane is normally computed along the: Longitudinal axis. Horizontal axis. Lateral axis. Vertical axis.

99 - 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 m Length of MAC: 8 m 63.4 % MAC 36.3 % MAC 23.1 % MAC 47.0 % MAC

100 - The actual 'Take-off Mass' is equivalent to: Actual Zero Fuel Mass plus the traffic load Dry Operating Mass plus the take-off fuel Dry Operating Mass plus take-off fuel and the traffic load Actual Landing Mass plus the take-off fuel

101 - 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 not be achieved. Will be greater than required. Will give reduced safety margins. Are unaffected but V1 will be increased.

102 - 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 28400 kg 31960 kg 30180 kg 32505 kg

103 - 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:

3 500 kg 35 000 kg 7 500 kg 62 500 kg

104 - In cruise flight, a centre of gravity moving aft will: Decrease longitudinal static stability Not change the manoeuvrability Have no effect on longitudinal static stability Increase longitudinal static stability

105 - 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 Passengers carried is less than 6. Passenger seats available is less than 20. Passenger seats available is less than 10. Passengers carried is less than 20.

106 - The aeroplane has a Take Off Mass of 58 000 kg. At this mass the range of safe CG positions, as determined from the appropriate graph in the loading manual, is: Forward limit 8.2% MAC aft limit 26.2% MAC Forward limit 9.5% MAC aft limit 26.1% MAC Forward limit 8.0% MAC aft limit 26.5% MAC Forward limit 8.5% MAC aft limit 26.1% MAC[see Annex]

107 - An aeroplane is carrying a traffic load of 10320 kgComplete the necessary sections of the attached appendix and determine which of the answers given below represents the maximum increase in the traffic load 7000 kg 8268 kg 1830 kg 655 kg[see Annex]

108 - 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:

29.5 % 27.8 % 27.2 % 30.5 %

109 - 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 V1 will be reached sooner than expected V1 will be increased. Speed at un-stick will be higher than expected The aeroplane will rotate much earlier than expected.

110 - At a given mass the CG position is at 15% MAC. If the leading edge of MAC is at a position625.6 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. 605.43 inches aft of datum 20.18 inches aft of datum If the leading edge of MAC is at a position625.6 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. 605.43 inches aft of datum 20.18 inches aft of datum 228.34 inches aft of datum 645.78 inches aft of datum

111 - If an aeroplane is at a higher mass than anticipated, for a given airspeed the angle of attack will Be decreased, drag will decrease and endurance will increase. Remain constant, drag will decrease and endurance will decrease. Be greater, drag will increase and endurance will decrease. Remain constant, drag will increase and endurance will increase.

112 - What mass has to be entered in the loading chart for aviation fuel F 34 if 170 l may be refuelled? (Fuel density = 0.78 kg/l) 133 kg 218 kg 170 kg 133 daN

113 - The Zero Fuel Mass and the Dry Operating Mass Differ by the sum of the mass of usable fuel plus traffic load mass. Are the same value. Differ by the mass of usable fuel. Differ by the value of the traffic load mass.

114 - The mass of an item multiplied by it's distance from the datum is it's Moment Force Moment arm Centre of gravity

115 - 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 19650 kg 141100 kg 39105 kg 121450 kg

116 - The maximum certificated take - off mass is: 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. 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.

117 - The standard mass for a child is 35 kg for holiday charters and 38 kg for all other flights. 35 kg for all flights. 30 kg for holiday charters and 35 kg for all other flights. 38 kg for all flights.

118 - An aeroplane is loaded with its centre of gravity towards the rear limit. This will result in: A reduction in power required for a given speed An increased risk of stalling due to a decrease in tailplane moment An increase in longitudinal stability A reduced fuel consumption as a result of reduced drag

119 - 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: 55 000 kg 25 000 kg 55 800 kg 25 800 kg

120 - For the purpose of completing the Mass and Balance documentation, the Traffic Load is considered to be equal to the Take-off Mass Plus the Operating Mass. Plus the Trip Fuel Mass. Less the Operating Mass. Less the Trip Fuel Mass.

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Exam simulation Mass and Balance ATPL - Airline Transport Pilot license

Exam simulation atpl 120 questions on 120 minutes