Test 120 exam questions on Mass and Balance for ATPL

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

2 - When considering the effects of increased mass on an aeroplane, which of the following is true? Flight endurance will be increased. Stalling speeds will be higher. Gradient of climb for a given power setting will be higher. Stalling speeds will be lower.

3 - 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

4 - 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)

6675 2496,3 2548,8 2311,8

5 - From the loading manual for the transport aeroplane, the aft cargo compartment has a maximum total load of:

9232 kg 1568 kg 4187 kg 3062 kg

6 - 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.

7 - With respect to aeroplane loading in the planning phase, which of the following statements is always correct ?LM = Landing Mass TOM = Take-off MassMTOM = Maximum Take-off Mass ZFM = Zero Fuel MassMZFM = Maximum Zero Fuel Mass DOM = Dry Operating Mass MTOM = ZFM + maximum full tank fuel mass LM = TOM - Trip Fuel Reserve Fuel = TOM - Trip Fuel MZFM = Traffic load + DOM

8 - Given:Standard Empty Mass 1764 lbs Optional Equipment 35 lbs Pilot + Passenger 300 lbs Cargo 350 lbsRamp Fuel ( Block Fuel) 60 Gal Trip Fuel 35 GalTaxi Fuel 1.7 GalFinal Reserve Fuel 18 Gal Fuel density 6 lbs/GalDetermine the expected landing mass. 2589 lbs 2557 lbs 2472 lbs 2599 lbs

9 - 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

10 - 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

11 - 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

12 - Comparing a forward CG position with an aft one, the forward cg position will cause a Decrease in the landing speed. Decrease in range. Tendency to yaw to the right on take-off. Decrease of the stalling speed.

13 - 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

14 - . 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

15 - 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]

16 - 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

17 - 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

18 - The flight preparation of a turbojet aeroplane provides the following data: Take-off runway limitation: 185 000 kgLanding runway limitation: 180 000 kgPlanned fuel consumption: 11 500 kgFuel 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 kgThe maximum cargo load that the captain may decide to load on board is: 54 000 kg 61 500 kg 55 500 kg 55 000 kg

19 - 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

20 - Aeroplane Dry Operating mass 85000 kg Performance limited take-off mass 127000 kg Performance limited landing mass 98500 kg Maximum zero fuel mass 89800 kgFuel requirements for flight - Trip fuel 29300 kgContingency and final reserve fuel 3600 kg Alternate fuel 2800 kg.The maximum traffic load that can be carried on this flight is: 6300 kg 7100 kg 12700 kg 4800 kg[see Annex]

21 - 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.

22 - 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.

23 - 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

24 - The empty mass of an aircraft is recorded in The loading manifest. It differs from Dry Operating Mass by the value of the 'useful load'. The weighing schedule. If changes occur, due to modifications, the aircraft must be re-weighed always. The loading manifest. It differs from the zero fuel mass by the value of the 'traffic load'. The weighing schedule and is amended to take account of changes due to modifications of the aircraft.

25 - 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

26 - . 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.

27 - What determines the longitudinal stability of an aeroplane ? The effectiveness of the horizontal stabilizer, rudder and rudder trim tab. The location of the centre of gravity with respect to the neutral point. The dihedral, angle of sweepback and the keel effect. The relationship of thrust and lift to weight and drag.

28 - The term 'useful load' as applied to an aircraft includes Traffic load plus usable fuel. The revenue-earning portion of traffic load plus useable fuel. The revenue-earning portion of traffic load only. Traffic load only.

29 - 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.

30 - 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

31 - 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.

32 - Which is true of the aircraft basic empty mass? It is a component of dry operating mass. It is the actual take-off mass, less traffic load. It is dry operating mass minus traffic load. It is dry operating mass minus fuel load.

33 - 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.

34 - 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

35 - 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.

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

37 - . 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

38 - 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

39 - 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

40 - . The reference about which centre of gravity moments are taken is the Datum. Chord line Centre of mass Centre of pressure

41 - 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: 1 550 kg 2 200 kg 1 600 kg 2 150 kg

42 - 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.

43 - 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]

44 - . 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.

45 - Assuming gross mass, altitude and airspeed remain unchanged, movement of the centre of gravity from the forward to the aft limit will cause: Increased cruise range Reduced maximum cruise range Lower optimum cruising speed Higher stall speed

46 - 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

47 - An aeroplane, which is scheduled to fly an oceanic sector, is due to depart from a high altitude airport in the tropics at 1400 local time. The airport has an exceptionally long runway. Which of the following is most likely to be the limiting factor(s) in determining the take - off mass ? Maximum zero fuel mass. Altitude and temperature of the departure airfield. En route obstacle clearance requirements. Maximum certificated take - off mass.

48 - 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.

49 - 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

50 - . 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

51 - 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 %.

52 - 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

53 - The BEM of an aircraft is 30000 kg.Given the following data calculate the DOM: Catering = 300 kgCrew = 600 kgTrip Fuel = 1200 kg Unusable Fuel = 30 kg Traffic Load = 2500 kg 30930 kg 30900 kg 29100 kg 34630 kg

54 - 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

55 - 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.

56 - 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.

57 - 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

58 - 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

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: 79000 kg 65200 kg. 93000 kg 78000 kg

60 - 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 %

61 - The maximum mass to which an aeroplane may be loaded, prior to engine start, is: Maximum certificated taxi (ramp) mass Maximum regulated take - off mass Maximum certificated take - off mass Maximum regulated taxi (ramp) mass

62 - 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

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

64 - 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 %

65 - 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

66 - Which of the following corresponds to zero fuel mass? Operating mass plus luggage of passengers and cargo. Operating mass plus passengers and cargo. The take-off mass of an aeroplane minus all usable fuel. Take-off mass minus fuel to destination and alternate.

67 - '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.

68 - The Maximum Taxi (Ramp) Mass is governed by: Tyre speed and temperature limitations. Structural considerations. Taxi distance to take-off point. Bearing strength of the taxiway pavement.

69 - 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.

70 - Conversion of fuel volume to mass May be done by using standard fuel density values as specified in EU - OPS 1. May be done by using standard fuel density values as specified in the Operations Manual, if the actual fuel density is not known. Must be done using fuel density values of 0.79 for JP 1 and 0.76 for JP 4 as specified in EU - OPS, IEM - OPS 1.605E. Must be done by using actual measured fuel density values.

71 - Which one of the following is correct? Arm = Force / Moment Moment = Force / Arm Arm = Moment / Force Arm = Force X Moment

72 - 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.

73 - 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.

74 - 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

75 - 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.

76 - 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.

77 - Traffic Load is the: Dry Operating Mass minus the disposable load. Zero Fuel Mass minus Dry Operating Mass. Take-off Mass minus Zero Fuel Mass. Dry Operating Mass minus the Variable Load.

78 - The Maximum Zero Fuel Mass is a structural limiting mass. It is made up of the aeroplane Dry Operational mass plus Traffic load, non-revenue load and crew standard mass. Unuseable fuel and crew standard mass. Traffic load Traffic load and potable water.

79 - 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.

80 - 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.

81 - A load placed forward of the datum Has a negative arm and therefore generates a negative mass and moment Has a positive arm and therefore generates a positive mass and moment Has a negative arm and therefore generates a negative moment Has a positive arm and therefore generates a positive moment

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

83 - 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.

84 - 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.

85 - An aeroplane is said to be 'neutrally stable'. This is likely to: Be caused by a centre of gravity which is towards the forward limit Be totally unrelated to the position of the centre of gravity Be caused by a centre of gravity which is towards the rearward limit Cause the centre of gravity to move forwards

86 - 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 1590 kg 2670 kg 820 kg 2410 kg

87 - . When has the centre of gravity to be computed? At least every four years After every 400-hrs inspection During every yearly inspection Prior to every flight

88 - 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.

89 - 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.

90 - 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 460000NLEMac 14m from datum MAC 4.6mCurrent CG 15.4m from datum 29.25% 25% 30.5% 27.5%

91 - 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: 40 cm. 33 cm. 34 cm. 30 cm.

92 - 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.

93 - 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]

94 - Contrary to the loading sheet forecasts you have:Cargo compartment 1: empty Cargo compartment 2: 1000 kgCargo compartment 3: 3000 kgCargo compartment 4: 2000 kgCargo compartment 5: 1000 kg Passengers in compartment OA: 20 Passengers in compartment OB: 20 Passengers in compartment OC: 30The take-off centre of gravity in MAC % (Mean Aerodynamic Chord), will be located at:

32.5 % 24.5 % 35.5 % 30.5 %

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

96 - A load placed aft of the datum: Has a negative arm and therefore generates a negative moment and mass Has a negative arm and therefore generates a negative moment but a positive mass Has a positive arm and therefore generates a positive moment Has a positive arm and therefore generates a positive moment but negative mass

97 - 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 %

98 - 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.

99 - 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.

100 - 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.

101 - . 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

102 - 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.

103 - 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

104 - A jet transport has the following structural limits:-Maximum Ramp Mass: 63 060 kg-Maximum Take Off Mass: 62 800 kg-Maximum Landing Mass: 54 900 kg-Maximum Zero Fuel Mass: 51 300 kgThe aeroplane's fuel is loaded accordance with the following requirements:-Taxi fuel: 400 kg-Trip fuel: 8400 kg-Contingency & final reserve fuel: 1800 kg-Alternate fuel: 1100 kgIf the Dry Operating Mass is 34930 kg, determine the maximum traffic load that can be carried on the flight if departure and landing airfields are not performance limited. 16 430 kg 17 070 kg 16 370 kg 16 570 kg

105 - In determining the Dry Operating Mass of an aeroplane it is common practice to use 'standard mass' values for crew. These values are Flight crew 85 kg., cabin crew 75 kg. each. These do not include a hand baggage allowance. Flight crew 85 kg., cabin crew 75 kg. each. These are inclusive of a hand baggage allowance. Flight crew (male) 88 kg. (female) 75 kg., cabin crew 75 kg. each. These do not include an allowance for hand baggage. Flight crew (male) 88 kg. (female) 75 kg., cabin crew 75 kg. each. These include an allowance for hand baggage.

106 - 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

107 - For a given configuration, the stall speed of an aeroplane will be highest when loaded: To the maximum allowable mass with the most forward CG To the maximum allowable mass with the most aft CG To a low total mass with the most aft CG To a low total mass with the most forward CG

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

109 - . 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.

110 - 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.

111 - 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.

112 - . 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.

113 - 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: Zero fuel mass Take-off mass Landing mass Dry operating mass

114 - 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 Found in the latest version of the weighing schedule as corrected to allow for modifications. Printed in the loading manual and includes unusable fuel. Found in the flight manual and is inclusive of unusable fuel plus fluids contained in closed systems. Inclusive of an allowance for crew, crew baggage and other operating items. It is entered in the loading manifest.

115 - 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.

116 - 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

117 - 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

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? 40 cm by 200 cm 40 cm by 300 cm 30 cm by 200 cm 30 cm by 300 cm

119 - 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

120 - 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: 14383 kg 11364 kg 13647 kg 18206 kg

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Exam simulation Mass and Balance ATPL - Airline Transport Pilot license

Exam simulation atpl 120 questions on 120 minutes