1. An aircraft is weighed before it enters service: A) To establish its mass and CG. B) To establish its maximum mass. C) To establish its CG position at maximum mass. D) To establish the minimum required take-off distance at maximum all-up mass.
A) To establish its mass and CG.
2. Individual aircraft, not part of a fleet average programme, must be re-weighed: A) At intervals not exceeding 4 years. B) At intervals not exceeding 9 years. C) At intervals not exceeding 2 years. D) Re-weighing not required if no significant amendments made to aircraft.
A) At intervals not exceeding 4 years.
3. Individual aircraft, which are part of a fleet average programme, must be re- weighed: A) At intervals not exceeding 9 years B) At intervals not exceeding 4 years C) At intervals not exceeding 2 years D) Re-weighing not required if no significant amendments made to aircraft
A) At intervals not exceeding 9 years
4. If the effects of modifications on mass and CG are not, or cannot be, accurately calculated: A) The aircraft must be re-weighed. B) The aircraft must be withdrawn from service. C) The manufacturer must be notified. D) The aircraft must be operated within the previously defined parameters.
A) The aircraft must be re-weighed.
5. In the context of weighing regulations, a fleet of aircraft is: A) An operator's group of aircraft of the same model and configuration. B) A group of 4 or fewer aircraft of the same model and configuration. C) A group of 9 or fewer aircraft of the same model and configuration. D) A group of 19 or fewer aircraft of the same model and configuration.
A) An operator's group of aircraft of the same model and configuration.
6. The fleet mass is: A) The average Dry Operating Mass and average CG position for all aircraft in the fleet. B) The average Dry Operating Mass and average CG position for at least 76% of aircraft in the fleet. C) The average Dry Operating Mass and average CG position for at least 51% of aircraft in the fleet. D) The average Operating Mass and CG position for all aircraft in the fleet.
A) The average Dry Operating Mass and average CG position for all aircraft in the fleet.
7. Fleet average mass programmes require an operator to weigh a certain proportion of a fleet: A) At least every 4 years B) At least every 19 years C) At least every 9 years D) At least every 2 years
A) At least every 4 years
8. Which of the following are valid methods of, and conditions required for, aircraft weighing procedures? Mark all correct answers. A) With the hangar air conditioning units off. B) Using load cells under at least 3 jacking points. C) On a weigh bridge. D) In an enclosed hangar with doors closed. E) At a minimum of 6 jacking points F) Inside a hangar of any type (open or enclosed). G) In a hangar which is air conditioned to ISA temperature.
A) With the hangar air conditioning units off. B) Using load cells under at least 3 jacking points. C) On a weigh bridge. D) In an enclosed hangar with doors closed.
9. During weighing, what items are included? A) Only those forming part of the BEM. B) Only those forming part of the DOM. C) Only those forming part of the OM. D) Only those forming part of the AUM.
A) Only those forming part of the BEM.
10. What changes must be recorded during a re-weighing? A) Basic equipment and accumulated effects of modifications and repairs. B) Basic equipment or accumulated effects of modifications and repairs. C) Basic equipment only. D) All in-flight equipment, plus the accumulated effects of modifications and repairs.
A) Basic equipment and accumulated effects of modifications and repairs.
11. What is produced during weighing, and used to compile a weighing schedule? A) Weighing report B) CP report C) CG report D) Weighing list
A) Weighing report
12. What may be used by operators to allow for daily changes in basic equipment and crew? A) An Aircraft Prepared for Service (APS) mass and index. B) An Aircraft Prepared for Service (APS) CP report. C) An Aircraft Prepared for Service (APS) CG report. D) An Aircraft Prepared for Service (APS) weighing schedule.
A) An Aircraft Prepared for Service (APS) mass and index.
13. Which document requires the operator to ensure that the loading, mass and aircraft CG comply with limitations specified in the AFM, POH or the Operations Manual. A) IR-OPS B) Part-FCL C) ICAO Annex 4 D) Part-MED
A) IR-OPS
14. When considering the mass of a fuel load to be carried, what must be applied to the fuel volume to calculate its actual mass? A) Specific Gravity B) Standard Deviation C) Specified Factor D) Standard Gravity
A) Specific Gravity
15. In which document will standard masses for flight crew, passengers and luggage be found? A) IR-OPS B) Part-M&B C) ICAO Annex 19 D) Part-FCL
16. When a significant number of passengers and/or checked baggage appears to exceed the standard mass allowances, what action must be taken by an operator? A) Determine the actual masses by weighing OR apply an adequate mass increment. B) Multiply standard masses by a reduction factor AND remove fuel or baggage C) Remove those passengers exceeding the standard mass allowance by 1.2 or more. D) Determine the actual masses by weighing AND apply an adequate mass increment.
A) Determine the actual masses by weighing OR apply an adequate mass increment.
17. When calculating the DOM the operator may use which standard masses for flight and cabin crew including their hand baggage?(Mark 2 correct answers) A) Flight Crew: 85 kg B) Cabin Crew: 75 kg C) Flight Crew: 88 kg D) Cabin Crew: 78 kg E) Flight Crew: 95 kg
A) Flight Crew: 85 kg B) Cabin Crew: 75 kg
18. What are the standard masses for adult passengers on charter aircraft, on aircraft having 20 - 29 passenger seats?(Mark 2 correct answers) A) Female: 69 kg B) Male: 83 kg C) Male: 84 kg D) Female: 84 kg E) Female: 80 kg F) Male: 92 kg
A) Female: 69 kg B) Male: 83 kg
19. What is the standard mass for checked baggage within Europe for all aircraft having 20 or more passengers seats? A) 13 kg B) 11 kg C) 15 kg D) 17 kg
A) 13 kg
20. What is the standard mass for checked baggage for a flight on an aircraft having 20 or more passengers seats, originating in London, UK and terminating in Casablanca, Morocco? A) 13 kg B) 15 kg C) 17 kg D) 11 kg
21. IR-OPS states that __________ must determine that the mass of all operating items and crew members (and their effect on aircraft CG), are included in the aircraft’s DOM by weighing or using standard masses. A) an operator B) the aircraft commander C) the flight crew D) the ground handlers
A) an operator
22. How is the CG Moment Arm calculated for the Basic Empty Mass? A) CG Moment Arm = Total Moment ÷ Total Mass B) CG Moment Arm = Total Moment x Total Mass C) CG Moment Arm = Total Mass ÷ Total Moment D) CG Moment Arm = Total Mass x Total Moment
A) CG Moment Arm = Total Moment ÷ Total Mass
23. Referring to CAP 696 Section 2 SEP1, what is the full range of distance between the forward and aft CG limits at BEM? [Referenz erforderlich: die in der Frage genannte CAP-696-Abbildung bzw. Seite separat verwenden. Grafiken sind nicht in dieser CSV enthalten.] A) 10 in B) 87.7 in C) 6.4 in D) 77.7 in
A) 10 in
24. Referring to the table below, what is the CG for the Zero Fuel Mass? [Abbildung/Tabelle erforderlich: siehe Original-PDF, Seite 5. Grafik nicht in dieser CSV enthalten.]
87.29
25. Referring to the table below, what is the CG for the Ramp Mass? [Abbildung/Tabelle erforderlich: siehe Original-PDF, Seite 5. Grafik nicht in dieser CSV enthalten.]
86.28
26. Referring to the table below, what is the CG for the Take-Off Mass? [Abbildung/Tabelle erforderlich: siehe Original-PDF, Seite 5. Grafik nicht in dieser CSV enthalten.]
86.31
27. Referring to the table below, what is the CG for the Landing Mass? [Abbildung/Tabelle erforderlich: siehe Original-PDF, Seite 6. Grafik nicht in dieser CSV enthalten.]
86.79
28. For the SEP1 in CAP 696 the CG forward and aft limits at a mass of 3500 lb are respectively: [Referenz erforderlich: die in der Frage genannte CAP-696-Abbildung bzw. Seite separat verwenden. Grafiken sind nicht in dieser CSV enthalten.] A) 78.65 in to 87.7 in B) 82.5 in to 94.6 in C) 74.0 in to 87.7 in D) 80.4 in to 87.7 in
A) 78.65 in to 87.7 in
29. Complete figure 2.4 in CAP 696 to determine the take-off mass and CG for the SEP1 aeroplane (BEM 2415 lb and CG 77.7 in) with one pilot mass 165 lb, with 2 passengers mass 200 lb and 220 lb in seats 3 and 4 and a crate mass 150 lb in area B. Block fuel 30 US Gall. [Referenz erforderlich: die in der Frage genannte CAP-696-Abbildung bzw. Seite separat verwenden. Grafiken sind nicht in dieser CSV enthalten.] A) 3317 lb and 85.9 in B) 3330 lb and 86.1 in C) 3167 lb and 83.1 in D) 3317 lb and 86.5 in
A) 3317 lb and 85.9 in
30. For the MEP1 in CAP 696 the CG forward and aft limits at a mass of 3600 lb are respectively: [Referenz erforderlich: die in der Frage genannte CAP-696-Abbildung bzw. Seite separat verwenden. Grafiken sind nicht in dieser CSV enthalten.] A) 83.15 in to 94.6 in. B) 79.8 in to 87.7 in. C) 82.0 in to 94.6 in. D) 90.5 in to 94.6 in.
A) 83.15 in to 94.6 in.
31. The formula for calculating minimum loading area is __________ mass / floor load limit. A) crate B) moment C) datum D) single unit
A) crate
32. CG Arm is calculated as follows: A) Moment / Mass B) Mass / Moment C) Moment x Mass D) CG x Mass
A) Moment / Mass
33. What is the Operating Mass? A) Operating Mass = DOM + Take-off Fuel B) Operating Mass = DOM + Ramp Fuel C) Operating Mass = DOM + Trip Fuel - Alternate Fuel D) Operating Mass = DOM - Take-off Fuel
A) Operating Mass = DOM + Take-off Fuel
34. What is the Traffic Load? A) Allowed Traffic Load = ATOM - OM B) Allowed Traffic Load = ATOM - DOM C) Allowed Traffic Load = ATOM - LM D) Allowed Traffic Load = ATOM - ZFM
A) Allowed Traffic Load = ATOM - OM
35. Which masses can be entered into section 2 of the load sheet?(Mark 4 correct answers) A) Non-revenue load B) Baggage C) Cargo (including mail) D) Passengers E) Potable Water F) In-flight catering supplies G) Crew H) Fuel I) Animals (including domestic pets)
A) Non-revenue load B) Baggage C) Cargo (including mail) D) Passengers
36. How is underload defined? A) The maximum amount of extra traffic load that can be accepted without exceeding any of the mass limitations. B) The maximum amount of extra variable load that can be accepted without exceeding any of the mass limitations. C) The minimum amount of extra traffic load that can be accepted without exceeding any of the mass limitations. D) The maximum amount of extra load that can be accepted without exceeding any of the CG limitations.
A) The maximum amount of extra traffic load that can be accepted without exceeding any of the mass limitations.
37. What is the Underload? A) Underload = Allowed Traffic Load - Actual Traffic Load B) Underload = Allowed Variable Load - Fuel C) Underload = Allowed All-up Mass + Fuel D) Underload = Allowed All-up Mass - Actual Traffic Load
A) Underload = Allowed Traffic Load - Actual Traffic Load
38. At which masses must the CG position be within the CG envelope, including any LMC? A) ZFM and TOM B) MTOM and ZFM C) AUM and MRM D) PLTOM and PLLM
A) ZFM and TOM
39. What is the Dry Operating Index (DOI)? A) An index for the position of the centre of gravity at Dry Operating Mass. B) An index for the aft and forward CG limits at Dry Operating Mass. C) An index for the average CG at Dry Operating Mass. D) An index for the %MAC at Dry Operating Mass.
A) An index for the position of the centre of gravity at Dry Operating Mass.
40. How is the fuel index determined? A) Using a ‘fuel index correction table’. B) %MAC = Fuel Mass x SG x Fuel Index. C) Using fuel index scales. D) Fuel Index = Fuel Mass x SG x Fuel Index Correction Factor.
A) Using a ‘fuel index correction table’.
41. At which flap setting(s) can the stabiliser trim (stab trim) setting for take-off be extracted directly from the trim sheet? A) 5° B) 1° C) 2° D) 15° E) 30°
A) 5°
42. Operational Mass Limits are determined by the operator and allow for CG shift caused by which factors?(Mark 4 correct answers) A) Crew and passenger movement in the cabin during flight. B) Last minute changes. C) Flap retraction and extension. D) Fuel burn. E) Movement of live cargo (animals) in hold. F) Landing gear extension and retraction. G) Usage of toilets. H) Unexpected movement of cargo. I) Consumption of food and water.
A) Crew and passenger movement in the cabin during flight. B) Last minute changes. C) Flap retraction and extension. D) Fuel burn.
43. The trim sheet displays:-Forward CGs (smaller %MACs) to the __________. A) left B) right C) top D) bottom
A) left
44. The trim sheet displays:-Aft CGs (larger %MACs) to the __________. A) right B) left C) top D) bottom
A) right
45. What is the stabiliser trim setting for flaps 15 if the CG is 14%. A) 3.7 units B) 4.3 units C) 4.4 units D) 5.6 units
A) 3.7 units
46. What is the stabiliser trim setting for flaps 5 if the CG is 14%. A) 4.4 units. B) 5.6 units C) 4.3 units D) 3.7 units.
A) 4.4 units.
47. For the B737 as loaded in Figure 4.13 of CAP 696 what is the new landing mass and %MAC if an extra 500 kg of cargo is off loaded from compartment 1? [Referenz erforderlich: die in der Frage genannte CAP-696-Abbildung bzw. Seite separat verwenden. Grafiken sind nicht in dieser CSV enthalten.] A) 53 170 kg and 22.2% B) 54 400 kg and 20.1% C) 54 400 kg and 22.2% D) 53 170 kg and 20.2%
A) 53 170 kg and 22.2%
48. For the B737 as loaded in Figure 4.13 of CAP 696 what is the new landing mass and %MAC if an extra 500 kg of cargo is loaded into compartment 1? [Referenz erforderlich: die in der Frage genannte CAP-696-Abbildung bzw. Seite separat verwenden. Grafiken sind nicht in dieser CSV enthalten.] A) 54 170 kg and 18.0% B) 55 400 kg and 20.1% C) 55 400 kg and 17.8% D) 54 170 kg and 17.8%
A) 54 170 kg and 18.0%
49. For the B737 as loaded in Figure 4.13 of CAP 696 what is the new landing mass and %MAC if an extra 500 kg of cargo is loaded into compartment 4? [Referenz erforderlich: die in der Frage genannte CAP-696-Abbildung bzw. Seite separat verwenden. Grafiken sind nicht in dieser CSV enthalten.] A) 54 170 kg and 21.75% B) 55 400 kg and 20.1% C) 55 400 kg and 21.75% D) 54 170 kg and 20.1%
A) 54 170 kg and 21.75%
50. What is the Operating Mass? A) Operating Mass = DOM + Take-off Fuel B) Operating Mass = DOM + Ramp Fuel C) Operating Mass = DOM + Trip Fuel - Alternate Fuel D) Operating Mass = DOM - Take-off Fuel
51. What is the Traffic Load? A) Allowed Traffic Load = ATOM - OM B) Allowed Traffic Load = ATOM - DOM C) Allowed Traffic Load = ATOM - LM D) Allowed Traffic Load = ATOM - ZFM
52. Which masses can be entered into section 2 of the load sheet?(Mark 4 correct answers) A) Non-revenue load B) Cargo (including mail) C) Passengers D) Baggage E) Potable Water F) In-flight catering supplies G) Crew H) Fuel I) Animals (including domestic pets)
A) Non-revenue load B) Cargo (including mail) C) Passengers D) Baggage
53. How is underload defined? A) The maximum amount of extra traffic load that can be accepted without exceeding any of the mass limitations. B) The maximum amount of extra variable load that can be accepted without exceeding any of the mass limitations. C) The minimum amount of extra traffic load that can be accepted without exceeding any of the mass limitations. D) The maximum amount of extra load that can be accepted without exceeding any of the CG limitations.
54. What is the Underload? A) Underload = Allowed Traffic Load - Actual Traffic Load B) Underload = Allowed Variable Load - Fuel C) Underload = Allowed All-up Mass + Fuel D) Underload = Allowed All-up Mass - Actual Traffic Load
55. At which masses must the CG position be within the CG envelope, including any LMC? A) ZFM and TOM B) MTOM and ZFM C) AUM and MRM D) PLTOM and PLLM
56. What is the Dry Operating Index (DOI)? A) An index for the position of the centre of gravity at Dry Operating Mass. B) An index for the aft and forward CG limits at Dry Operating Mass. C) An index for the average CG at Dry Operating Mass. D) An index for the %MAC at Dry Operating Mass.
57. How is the fuel index determined? A) Fuel Index = Fuel Mass x SG x Fuel Index Correction Factor. B) %MAC = Fuel Mass x SG x Fuel Index. C) Using fuel index scales. D) Using a ‘fuel index correction table’.
A) Fuel Index = Fuel Mass x SG x Fuel Index Correction Factor.
58. At which flap setting(s) can the stabiliser trim (stab trim) setting for take-off be extracted directly from the trim sheet? A) 5° B) 1° C) 2° D) 15° E) 30°
59. Operational Mass Limits are determined by the operator and allow for CG shift caused by which factors?(Mark 4 correct answers) A) Crew and passenger movement in the cabin during flight. B) Last minute changes. C) Flap retraction and extension. D) Fuel burn. E) Unexpected movement of cargo. F) Movement of live cargo (animals) in hold. G) Landing gear extension and retraction. H) Consumption of food and water. I) Usage of toilets.
60. The trim sheet displays:-Forward CGs (smaller %MACs) to the __________. A) left B) right C) top D) bottom
61. The trim sheet displays:-Aft CGs (larger %MACs) to the __________. A) right B) left C) top D) bottom
62. What is the stabiliser trim setting for flaps 15 if the CG is 14%. A) 3.7 units B) 4.3 units C) 4.4 units D) 5.6 units
63. What is the stabiliser trim setting for flaps 5 if the CG is 14%. A) 4.4 units. B) 5.6 units C) 4.3 units D) 3.7 units.
64. For the B737 as loaded in Figure 4.13 of CAP 696 what is the new landing mass and %MAC if an extra 500 kg of cargo is off loaded from compartment 1? [Referenz erforderlich: die in der Frage genannte CAP-696-Abbildung bzw. Seite separat verwenden. Grafiken sind nicht in dieser CSV enthalten.] A) 53 170 kg and 22.2% B) 54 400 kg and 20.1% C) 54 400 kg and 22.2% D) 53 170 kg and 20.2%
65. For the B737 as loaded in Figure 4.13 of CAP 696 what is the new landing mass and %MAC if an extra 500 kg of cargo is loaded into compartment 1? [Referenz erforderlich: die in der Frage genannte CAP-696-Abbildung bzw. Seite separat verwenden. Grafiken sind nicht in dieser CSV enthalten.] A) 54 170 kg and 18.0% B) 55 400 kg and 20.1% C) 55 400 kg and 17.8% D) 54 170 kg and 17.8%
66. For the B737 as loaded in Figure 4.13 of CAP 696 what is the new landing mass and %MAC if an extra 500 kg of cargo is loaded into compartment 4? [Referenz erforderlich: die in der Frage genannte CAP-696-Abbildung bzw. Seite separat verwenden. Grafiken sind nicht in dieser CSV enthalten.] A) 54 170 kg and 21.75% B) 55 400 kg and 20.1% C) 55 400 kg and 21.75% D) 54 170 kg and 20.1%
67. What is a critical problem associated with failure of the Fuel Management Computer System (FMCS)? A) An unbalanced aircraft, which may be outside CG limits. B) A nose heavy aircraft which is uncontrollable in pitch, resulting in a fatal dive. C) A tail heavy aircraft which is uncontrollable in pitch, resulting in an aerodynamic stall. D) A laterally unbalanced aircraft, resulting in an uncontrolable roll and yaw motion.
A) An unbalanced aircraft, which may be outside CG limits.
68. What happens to CG, as fuel is consumed? A) CG moves aft/ or forward. B) CG remains constant. C) CG moves forward. D) CG moves aft.
A) CG moves aft/ or forward.
69. What is the primary purpose of the Fuel Management Computer System (FMCS) on modern aircaft? A) The FMCS ensures fuel distribution is properly managed and maintains the aircraft within operational CG limits. B) The FMCS ensures fuel mass does not exceed structural limitations throughout the flight. C) The FMCS ensures fuel consumption is properly managed during flight so that maximum landing mass is not exceeded. D) The FMCS ensures fuel consumption is properly managed and maintains the aircraft at the optimum CG at all stages of flight.
A) The FMCS ensures fuel distribution is properly managed and maintains the aircraft within operational CG limits.
70. If an aeroplane is at a higher mass than anticipated, for a given airspeed the angle of attack will A) be greater, drag will increase and endurance will decrease. B) be decreased, drag will decrease and endurance will increase. C) remain constant, drag will decrease and endurance will decrease. D) remain constant, drag will increase and endurance will increase.
A) be greater, drag will increase and endurance will decrease.
71. For a given configuration, the stall speed of an aeroplane will be highest when loaded: A) to the maximum allowable mass with the most forward CG. B) to a low total mass with the most forward CG. C) to a low total mass with the most aft CG. D) to the maximum allowable mass with the most aft CG.
A) to the maximum allowable mass with the most forward CG.
72. Comparing a forward CG position with an aft one, the forward cg position will cause a A) decrease in range. B) decrease in the landing speed. C) decrease of the stalling speed. D) tendency to yaw to the right on take-off.
A) decrease in range.
73. The effect of the centre of gravity (CG) being close to the forward limit is: A) a reduced rate of climb capability. B) an improved rate of climb capability. C) reduced specific fuel consumption. D) decreased induced drag.
A) a reduced rate of climb capability.
74. 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 is: A) 6899 kg B) 6870 kg C) 6420 kg D) 6129 kg
A) 6899 kg
75. 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: A) 1196 kg B) 1916 kg C) 1437 kg D) 2302 kg
A) 1196 kg
76. 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 wing tank first 5- is defined on the assumption that fuel is consumed from the centre wing tank first. The combination of correct statements is: A) 1, 3, 5 B) 1, 2, 3 C) 2, 3, 5 D) 2, 3, 4
A) 1, 3, 5
77. On an aeroplane without central fuel tank, the maximum Zero Fuel Mass is related to: A) the bending moment at the wing root. B) Maximum Structural Take-Off Mass. C) wing loaded trip fuel. D) variable equipment for the flight.
A) the bending moment at the wing root.
78. Considering only structural limitations, on long distance flights (at the aeroplane's maximum range), the traffic load is normally limited by: A) The Maximum Take-off Mass. B) The Maximum Zero Fuel Mass. C) The Maximum Zero Fuel Mass plus the Take-off Mass. D) The Maximum Landing Mass.
A) The Maximum Take-off Mass.
79. Given: Dry Operating Mass = 38 000 kg Maximum Structural Take-off Mass = 72 000 kg Maximum Landing Mass = 65 000 kgMaximum Zero Fuel Mass = 61 000 kg Trip Fuel = 8 000 kg Take-off Fuel = 10 300 kg The maximum allowed take-off mass and traffic load are respectively : A) 71 300 kg and 23 000 kg B) 71 300 kg and 25 300 kg C) 73 000 kg and 24 700 kg D) 73 000 kg and 27 000 kg
A) 71 300 kg and 23 000 kg
80. The centre of gravity of a body is that point A) through which the sum of the forces of all masses of the body is considered to act B) where the sum of the moments from the external forces acting on the body is equal to zero C) where the sum of the external forces is equal to zero D) which is always used as datum when computing moments
A) through which the sum of the forces of all masses of the body is considered to act
81. Which one of the following is correct? A) Arm = Moment / Force B) Arm = Force / Moment C) Moment = Force / Arm D) Arm = Force X Moment
A) Arm = Moment / Force
82. The datum is a reference from which all moment (balance) arms are measured. Its precise position is given in the control and loading manual and it is located A) at a convenient point which may not physically be on the aircraft. B) at or near the forward limit of the centre of gravity. C) at or near the focal point of the aircraft axis system. D) at or near the natural balance point of the empty aircraft.
A) at a convenient point which may not physically be on the aircraft.
83. Moment (balance) arms are measured from a specific point to the body station at which the mass is located. That point is known as A) the datum. B) the focal point. C) the axis. D) the centre of gravity of the aircraft.
A) the datum.
84. An aircraft has its centre of gravity located 7 metres from the datum line and it has a weight of 49000 N. The moment about the datum is: A) 343 000 Nm. B) 1.43 Nm. C) 7000 Nm. D) 343 000 N/m.
A) 343 000 Nm.
85. Longitudinal CG location is normally expressed: A) as a percentage of the MAC from its leading edge. B) as a percentage of the MAC from its trailing edge. C) with respect to the neutral point. D) with respect to the centre of pressure.
A) as a percentage of the MAC from its leading edge.
86. An aeroplane has a mean aerodynamic chord (MAC) of 134.5 inches. The leading edge of this chord is at a distance of 625.6 inches aft of the datum. Define the location of the centre of gravity of the aeroplane in terms of percentage MAC if the mass of the aeroplane is acting vertically through a balance arm located 650 inches aft of the datum.
18.1%
87. If individual masses are used, the mass of an aircraft must be determined prior to initial entry into service and thereafter A) at intervals of 4 years if no modifications have taken place. B) at regular annual intervals. C) only if major modifications have taken place. D) at intervals of 9 years.
A) at intervals of 4 years if no modifications have taken place.
88. An aircraft may be weighed A) in an enclosed, non-air conditioned, hangar. B) in a quiet parking area clear of the normal manoeuvring area. C) in an area of the airfield set aside for maintenance. D) at a specified 'weighing location' on the airfield.
A) in an enclosed, non-air conditioned, hangar.
89. To measure the mass and CG-position of an aircraft, it should be weighed with a minimum of: A) 3 points of support B) 2 points of support C) 1 point of support D) 4 point of support
A) 3 points of support
90. A location in the aircraft which is identified by a number designating its distance from the datum is known as: A) Station. B) Moment. C) MAC. D) Index.
A) Station.
91. The responsibility for determination of the mass of 'operating items' and 'crew members' included within the Dry Operating Mass lies with A) the operator. B) the commander. C) the authority of the state of registration. D) the person compiling the weighing schedule.
A) the operator.
92. In mass and balance calculations the "index" is: A) is a figure without unit of measurement which represents a moment. B) a location in the aeroplane identified by a number. C) an imaginary vertical plane or line from which all measurements are taken. D) the range of moments the centre of gravity (cg) can have without making the aeroplane unsafe to fly.
A) is a figure without unit of measurement which represents a moment.
93. Given : Basic Empty Mass: 1799 lbs Optional Equipment: 35 lbs Pilot + Front seat passenger: 300 lbs Cargo Mass: 350 lbs Ramp Fuel = Block Fuel: 60 Gal. Trip Fuel: 35 Gal.Fuel density: 6 lbs/Gal.Determine the Zero Fuel Mass. A) 2484 lbs B) 2589 lbs C) 2659 lbs D) 2414 lbs
A) 2484 lbs
94. The floor of the main cargo hold is limited to 4 000 N/m2. It is planned to load a cubic container each side of which measures 0.5m. Its maximum gross mass must not exceed: (assume g=10m/s2) A) 100 kg B) 1000 kg C) 500 kg D) 5000 kg
A) 100 kg
95. Which equation represents a conversion of 1 US gallon AVGAS into lbs?
1 USG = 6 lbs
96. The Maximum Zero Fuel Mass (MZFM): 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 under the assumption that fuel is consumed from the outer wing tanks first. 5. Is defined under the assumption that fuel is consumed from the inner wing tanks first. Which combination of statements is correct?
1, 3, 5
97. Using the standard mass figure from CAP 696 Page 5. You are about to depart for a commercial flight, with an aircraft having a flight crew of 7 members and 115 passengers. As part of your pre-flight calculations and given the following information, you need to calculate the Traffic Load in accordance with the standard passenger and baggage masses, as defined in the annex. Flight crew: 4 male & 3 female Male passengers: 70 Female passengers: 35 Children: 10 Baggage: 62 items Standard mass for a flight crew member: 85 kg Non-revenue load: 500 kg [Referenz erforderlich: die in der Frage genannte CAP-696-Abbildung bzw. Seite separat verwenden. Grafiken sind nicht in dieser CSV enthalten.]
10 476 kg
98. Given: Fuel volume: 3800 US Gallons Fuel density: 0.79 kg/l. The fuel mass ls:
11 364 kg
99. 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:
1196 kg
100. During the pre-flight preparation, the pilot calculates a take-off fuel of 53 US gallons. Considering a fuel density of 6 lb per US gallon, this equals:
144 kg
101. The following data applies to an aircraft which is about to take-off. MSTOM 8600 kg PLTOM 8470 kg DOM 5110 kg Crew and special operating equipment 290 kg Take- off fuel 1460 kg Calculate the traffic load.
1900 kg
102. Given the following information, what is the maximum amount of Extra Fuel that can be uploaded for this Commercial Air Transport flight? MTOM 2050 lb MLM 1910 lb ZFM 1727 lb Planned T/O Fuel 32 US gal Trip Fuel 25 US gal Fuel tank capacity 54.5 US gal Specific gravity 0.72
21.8 US gal
103. Determine the Take-off Mass for the following single engine aeroplane. Given : Basic Empty Mass 1799 lb Pilot + Front seat passenger 300 lb Cargo Mass 350 lb Ramp Fuel = Block Fuel 60 Gal Trip Fuel 35 Gal Fuel density 6 lb/Gal Taxi Fuel 10 lb
2799 lb
104. A pilot is taking-off from an airport with a light aircraft which has a maximum structural take-off mass of 3250 lb and 25 lb of taxi fuel can be added. It is a hot summer day and the maximum all up mass (MAUM) ls 3100 lb. What is the maximum ramp mass in these conditions?
3100 lb
105. According to the Flight Manual, the Maximum Structural Mass of your aircraft is 3200 lb, which may be increased by 25 lb for taxiing. It is a hot day and the performance charts restrict the Maximum All Up Mass (MAUM) to 3100 lb. What is the value of the Regulated Take-Off Mass (RTOM)?
106. The Take-off Mass of an aeroplane is 66 700 kg which includes a traffic load of 14 200 kg and a usable fuel load of 10 500 kg. If the standard mass for the crew is 545 kg the Dry Operating Mass is:
4720 lb
107. The Take-off Mass (TOM) of an aircraft is 8470 kg Total fuel on board is 1 600 kg including 450 kg reserve fuel and 29 kg of unusable fuel The Traffic Load (TL) is 770 kg What is the Zero Fuel Mass (ZFM)?
6899 kg
108. Given: The Take-off Mass (TOM) of an aeroplane is 141 000 kg. Total fuel on board is 63 000 kg including 14 000 kg reserve fuel and 1 000 kg of unusable fuel. The Traffic Load (TL) is 12 800 kg. What is the Zero Fuel Mass (ZFM)?
79 000 kg
109. 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 = 10 m/s²):
80 kg
110. Given the following data, what ls the additional traffic load that the crew could accept for take-off? Dry Operating Mass: 12 445 lb Traffic Load: 241 lb Fuel loaded: 5000 lb Trip Fuel: 3000 lb Taxi Fuel: 100 lb MTOM: 18 386 lb
800 lb
111. For a particular aeroplane, the structural maximum mass without any fuel on board, other than unusable quantities, is:
A fixed value which is stated in the Aeroplane Operating Manual.
112. The Maximum Zero Fuel Mass (MZFM) is:
A structural limit listed in the Flight Manual as a fixed value.
113. Dry operating mass is the take-off mass of the aircraft less:
All usable fuel and traffic load.
114. Calculate the Basic Empty Mass and CG position of the aircraft given the following data: Reference point situated 60 inches from the Datum. Nosewheel load of 1275 kg situated -27 inches from the reference point. Left mainwheel load of 5383 kg situated +105 inches from the reference point. Right mainwheel load of 5287 kg situated +105 inches from the reference point. Ballast of 96 kg situated +112 inches from the reference point.
BEM 11945 kg. CG 150.91 inches aft of the datum.
115. The Dry Operating Mass includes:
crew and crew baggage, catering, removable passenger service equipment, potable water and lavatory chemicals.
116. The actual Zero Fuel Mass (ZFM) is equal to the:
Dry Operating Mass plus the Traffic Load.
117. By adding to the Basic Empty Mass the mass of crew, crew baggage, catering, and operational equipment for a specific flight, we get the:
Dry Operating Mass.
118. According to OPS regulations, standard masses for checked baggage may be used if the aircraft:
Has 20 or more seats.
119. The floor of the main cargo hold is limited to 4000 N/ms2 It is planned to load a cubic container each side of which measures 0.5 m. The maximum gross mass must not exceed (assume g = 10 m/s2):
It is planned to load a cubic container each side of which measures 0.5 m. ...
120. The Maximum Zero Fuel Mass (MZFM) is the mass of the aeroplane with no usable fuel on board. It is a limitation which is:
Listed in the Flight Manual as a fixed value. It is a structural limit.
121. Considering only structural limitations, on very short legs with minimum take- off fuel, the traffic load is normally limited by:
Maximum Zero Fuel Mass.
122. The Maximum Zero Fuel Mass (MZFM) is a mass limitation for the:
Strength of the wing root.
123. Which of the following statements best describes the "Regulated Landing Mass'?"
The lowest of the Performance Limited Landing Mass and Structural Limited Landing Mass.
124. The term 'Maximum Zero Fuel Mass' (MZFM) consists of:
The maximum permissible mass of an aeroplane with no usable fuel.
125. The Zero Fuel Mass (ZFM) of an aeroplane is always:
The Take-off Mass minus the Take-off Fuel Mass.
126. A baggage weighing 50 kg is tied down on the baggage zone of the aircraft and the moment is -5000 KG mm The arm of the baggage zone is:
-100 nm and is located forward of the datum.
127. Due to variations in the actual passenger distribution, cargo loading, or fuel distribution in comparison with the data used during the pre-flight preparation of the mass and balance documentation, the Operator (1) ___ which is/are (2) ___ restrictive than the certified CG limits.
(1) defines operational CG limits; (2) more.
128. The operator can determine (1) ____ to the Centre-of-Gravity limits, to be (2) _____.
(1) own limitations; (2) more restrictive.
129. An aeroplane has a mean aerodynamic chord (MAC) of 134.5 inches. The leading edge of this chord is at a distance of 625.6 inches aft of the datum. Define the location of the centre of gravity of the aeroplane in terms of percentage MAC if the mass of the aeroplane is acting vertically through a balance arm located 650 inches aft of the datum.
0.181
130. To measure the mass and CG-position of an aircraft, it should be weighed with a minimum of:
3 points of support
131. Determine the length of the MAC, given: Leading edge at wing root: STA 235 Trailing edge at wing root: STA 250 Leading edge at wing tip: STA 148 Trailing edge at wing tip: STA 212 Leading edge of MAC: STA 192 Trailing edge of MAC: STA 224 Note: Body stations are distances from the aircraft nose in 10 -1 m.
320 cm
132. 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
36.3 % MAC
133. An aeroplane with one nose landing gear and two main landing gears is weighed on jacks. Determine the aircraft BEM and CG position, using the following readouts: Nose landing gear, located at 161 inches from datum reading: 2300 kg Each main landing gear, located at 775 inches from datum reading: 19300 kg
40900 kg and 740.5 inches from datum.
134. A tri-wheel aircraft has its datum 25 inches aft of the nose wheel and 180 inches forward of the main wheels. If the nose jack shows 125 lb and each main wheel jack shows 3400 lb, determine the BEM and the CG position.
6925 lb and 201.3 inches from the nose wheel of the aircraft.
135. 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.
136. The arm is the ___ distance of a load as measured from the aircraft ___ .
Horizontal; datum
137. Select the statement which best defines the Datum.
Is a fixed point from which all balance arm distances are measured.
138. In mass and balance calculations which of the following describes the datum?
It is the point on the aircraft designated by the manufacturers from which all centre of gravity measurements and calculations are made.
139. An aircraft is used for Commercial Air Transport. Since the aircraft's initial entry into service, 3 years ago, several repairs and modifications have been executed. These changes were accurately documented. The Operator uses individual aircraft masses. Does the aircraft need to be re-weighed now?
No, but it must be re-weighed within the next 12 months.
140. If all the moments are positive when calculating mass (weight) and balance, the position of the datum would be at the:
Nose, or forward of the aircraft.
141. 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:
Parallel to the gravity vector.
142. A location in the aircraft which is identified by a number designating its distance from the datum is known as:
Station.
143. Moment (balance) arms are measured from a specific point to the body station at which the mass is located. That point is known as:
The datum
144. The moment for an item is:
The mass of the item multiplied by its distance from the datum.
145. The weighing of an aircraft must be performed:
Whenever the cumulative change to the DOM exceeds plus/minus 0.5% of the MSLM.
146. A mass of 600 kg is loaded at a station which is located 12 metres behind the present centre of gravity and 18 metres behind the datum. (Assume g=10 m/s2) The moment for that mass used in the loading manifest is:
108 kNm
147. An aircraft has a total mass of 3927 kg with a CG of 4.28 m aft of the datum line. Determine the amount of additional load to be loaded at station 5.8 m aft of the datum line, to establish a new CG of 4.37 m aft of the datum line:
247 kg
148. Given : Basic Empty Mass: 1799 lbs Optional Equipment: 35 lbs Pilot + Front seat passenger: 300 lbs Cargo Mass: 350 lbs Ramp Fuel = Block Fuel: 60 Gal. Trip Fuel: 35 Gal.Fuel density: 6 lbs/Gal. Determine the Zero Fuel Mass.
2484 lbs
149. The Take-Off Mass of an aircraft is 12 500 kg and the take-off Centre of Gravity is located 4.2 m aft of datum, which is out of the forward limit. Calculate the mass that must be moved from the forward cargo hold to the rear cargo hold, in order to move the CG to the forward limit 4.5 m aft of datum. The distance between the cargo holds is 15 m.
250 kg
150. Determine the dry operating index (DOI) of the aircraft, given: BEM: 3208 kg CG at BEM: 129.7 inches aft of datum 2 crew members: 160 kg Crew seats: 47.5 inches aft of datum DOI= ( mass (kg) x CG (inches) / 5000) - 30
54.74
151. An aircraft with a two wheel nose gear and four main wheels rests on the ground with a single nose wheel load of 7250 N and a single main wheel load of 60 000 N. The distance between the nose wheels and the main wheels is 10 metres. How far is the Centre of Gravity ln front of the main wheels?
57 cm.
152. An aircraft has a total mass of 5430 kg with a CG of 5.43 m aft of the datum line. Minutes before despatch an additional load of 210 kg was loaded onto the aircraft. The aircraft's new CG is 5.56 m aft of the datum. The additional load was placed:
8.92 m aft of the datum line.
153. An aircraft has a total mass of 5430 kg with a CG of 5.43 m aft of the datum line. Minutes before despatch an additional load of 210 kg was loaded onto the aircraft. The aircraft's new CG is 5.56 m aft of the datum. The additional load was placed:
154. 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:
80 000 Nm
155. 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:
156. Given: Mass on nose wheel: 285 kg Mass on left main wheels: 1465 kg Mass on right main wheels: 1395 kg Distance between the nose and main wheels: 7 ft 8 in Calculate the aircraft's CG position.
83.7 in aft of the nose wheel.
157. In mass and balance calculations the 'index' is
A figure without unit of measurement which represents a moment.
158. What is the purpose of the trim sheet in Mass and Balance?
a graphical reasoning to determine the CG position of operational masses.
159. A turbojet aeroplane has a planned Take-off Mass of 190 000 kg. The cargo load is distributed as follows: Cargo 1: 3000 kg (3.50 m from reference point) Cargo 4: 7000 kg (20.98 m from reference point) Distance from reference point to leading edge: 14m Length of MAC: 4.6 m Once the cargo loading is completed, the crew is informed that the centre of gravity at take-off is located at 38% MAC (Mean Aerodynamic Chord) which is beyond the limits. The captain decides then to redistribute part of the cargo load between cargo 1 and cargo 4 in order to obtain a new centre of gravity location at 31% MAC. Following the transfer operation, the new load distribution is:
cargo 1: 6500 kg; cargo 4: 3500 kg.
160. An Airbus A380 is loaded with cargo including a series of sports cars. The total mass is 100 000kg. The CG is 10 m from the datum and is 25% of Mac. The Mac is 7m long. Lamborghini weighs 1,000kg Range Rover sport weighs 2,000kg The Lamborghini is 5m behind the CG, and the Range Rover is 10m behind the Lamborghini. If the Lamborghini and the Range Rover are stolen, where is the new position of the CG?
CG = 9.7m
161. 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.
162. What effect does a CG outside the aft limit have on aircraft longitudinal stability and controllability?
Decreases stability and increases controllability
163. How can you calculate the Dry Operating Index (DOI)?
DOM x CG arm / constant
164. If the CG of an aircraft is close to its forward limit, what will be achieved if fuel is transferred from the wing tanks to the aeroplane's fin or horizontal stabiliser tanks?
Efficient fuel consumption, by repositioning the CG aft.
165. When the centre of gravity is at the forward limit, an aeroplane will be:
Extremely stable and will require excessive elevator control to change pitch.
166. A load placed forward of the datum:
Has a negative arm and therefore generates a negative moment.
167. State the advantage(s) of the index method to determine moments.
It reduces the dimensions of the moments thus making it easier to calculate.
168. Which equation is correct in order to calculate the centre of gravity? The sum of the:
Moments divided by the sum of the masses.
169. An aeroplane, with its CG limits from 638 inches to 658 inches aft of the datum, should have been loaded so as to give a calculated Take-Off Mass of 64 200 kg and the CG located at 640 inches aft of the datum, with 750 kg loaded into the front cargo hold and 500 kg into the rear cargo hold. Unfortunately, the ground staff incorrectly loaded all the cargo into the forward cargo hold. If the distance between the cargo holds ls 517 inches, is the aeroplane's CG within limits?
No, it is out of the forward limit.
170. During the pre-flight, the pilot assumed that the only passenger weighing 170 lb would sit at the front-row seat (located 85 inches aft of datum). The calculations gave a Take-Off Mass of 4100 lb and a take-off CG located at 94 inches aft of datum. When the passenger arrives, he/she sits at the rear seat, located 158 inches aft of datum. The CG limits are from 86 inches to 95 inches aft of datum. Determine if the new CG within limits:
No, it is out of the rear limit.
171. An aeroplane weighing schedule indicates that: The Empty Mass is 57 320 kg. The nominal Dry Operating Mass (DOM) is 60 120 kg. The Maximum Zero Fuel Mass (MZFM) is given as 72 100 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 11 980 kg.
172. An aeroplane weighing schedule indicates that: The Empty Mass is 57 320 kg. The nominal Dry Operating Mass (DOM) is 60 120 kg. The Maximum Zero Fuel Mass (MZFM) is given as 72 100 kg. Which of the following is a correct statement in relation to this aeroplane?
173. When must the centre of gravity (CG) be computed?
Prior to every flight.
174. What are the effects of a CG forward of the forward limit?
Range, endurance and absolute ceiling will decrease.
175. What are the advantages of using the index method to determine moments? It:
Reduces the magnitude of moments, making it less time-consuming to compute.
176. Which of the following would not affect the position of the CG?
Stabilizer trim setting.
177. The captain has received a calculated load sheet with his pre-flight package. The ground handler now hands over a final load sheet. ln this scenario, which one does the captain have to use?
The final load sheet provided by the ground handler.
178. Refer to CAP 696 figure 4.12. The ZFM of an aeroplane is equal to 48 000 kg and the CG position is at 25 % MAC. Which one of the statements below is correct ? [Referenz erforderlich: die in der Frage genannte CAP-696-Abbildung bzw. Seite separat verwenden. Grafiken sind nicht in dieser CSV enthalten.]
The Index at ZFM is within limits and in an aft position.
179. The principle of the index method is:
To divide high magnitude moments by a constant and thereby simplify calculations by decreased values.
180. Assuming a baggage compartment with a structural limitation of 32 lb/sq ft, a mass of 200 kg has to be distributed over an area of:
1.28 m²
181. The basic empty mass of an aircraft is 30 000 kg The masses of the following items are: Catering 300 kg Safety and rescue material nil Fly away kit nil Crew (inclusive crew baggage) 365 kg Fuel at take-off 3000 kg Unusable fuel 120 kg Passengers, baggage, cargo 8 000 kg The Dry Operating Mass is:
30 665 kg
182. The maximum intensity floor loading for an aeroplane is given in the Flight Manual as 650 kg per square metre. What is the maximum mass of a package which can be safely supported on a pallet with dimensions of 80 cm by 80 cm?
416.0 kg
183. A container with a base area of 5 x 5 ft2 is loaded into a cargo compartment. The maximum running load of the compartment is 85 lb/feet. The maximum possible weight of the container is:
425 lb
184. Given : Actual mass 116 500 lb Original CG station 435.0 Compartment A station 285.5 Compartment B station 792.5 If 390 lb of cargo is moved from compartment B (aft) to compartment A (forward), what is the station number of the new CG?
433.3
185. 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?
A load of 400 kg in a crate with dimensions 1.2 m x 1.2 m x 1.2 m.
186. Which one of the following shipments can be loaded in a cargo compartment with a floor loading of 70 kg/m2? Shipment W: 500 kg on a pallet sized 2 m x 2 m Shipment X: 500 kg on a pallet sized 1 m x 1 m Shipment Y: 600 kg on a pallet sized 2 m x 2 m Shipment Z: 600 kg on a pallet sized 3 m x 3 m (All pallets are in direct contact with the cargo floor).
Shipment Z
187. 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 give reduced safety margins
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