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#1. Where is the C of G of the aircraft below?
#2. Where is the C of G of the aircraft below?
#3. Calculate the take-off and landing C of G positions for an aircraft which has MTOM = 3400 Kg. MLM = 3100 Kg. BEM = 2000 Kg. C of G at BEM = +2.25 m. Take-off fuel = 500 Kg. Fuel arm = +3.5 m. Take-off oil = 20 Kg. Oil arm = -9 m. Crew = 200 Kg. Crew arm = -3.75 m. Passengers = 360 Kg. Passengers arm = + 4 m. Baggage = 250 Kg. Baggage arm = +10 m. Fuel burned during flight = 300 Kg. Oil burned flight = -5 Kg. Allowable C of G range = +2.5 m. to +3.5 m.
#4. What are the total mass and C of G position of the aircraft in the diagram if the load on the nosewheel is 750 Newtons, and those on the main wheels are 5950 N and 5950 Newtons. Use g = 9.81 Kg/N.
#5. Calculate the C of G position of the aircraft below?
#6. Where is the C of G of the aircraft in the diagram?
#7. How far is the C of G from the main wheels of an aircraft of an aircraft with two nose wheels and two main wheels if the load on each nose wheel is 725 Kg and that on each main wheel is 6000 Kg and the nose wheels are 10 metres in front of the main wheels?
#8. What are the total mass and C of G position of the aircraft in the diagram if the load on the nose wheel is 750 Newtons, and those on the main wheels are 5950 N and 5950 Newtons. Use g = 9.81 Kg/N.
#9. The SEP 1 described in Section II of CAP 696 is loaded with a 460 Ib box of base area 2 ft 9 inches wide and 2 ft 9 inches long, located centrally across baggage zones B and C. The total mass of the aircraft before loading the box was 3120 Ib and the C of G position was +84 inches. Which of the following statements are true of the situation after the box has been loaded? The MTOM is greater than the total mass. (ii) The C of G position is within limits. (iii) The floor loading is within limits.
#10. What is the C of G position of an MEP 1 aircraft if its TOM = 4250 Ib and its take-off moment is +399000 Ib inches?
#11. Using the data for MEP 1 in Section III of the CAP 696 loading manual and the following information identify which of the following statements are true? Pilot and front passenger 400 Ib. Passenger (centre seats) 340 Ib. Baggage zone 3 180 Ib. Baggage zone 1 90 Ib. Fuel load at start 85 USG. Taxi fuel 4 USG. Trip fuel 65 USG.
#12. What are the total mass and C of G position of the aircraft in the diagram if the load on the nosewheel is 550 Newtons, and those on the main wheels are 8850 N and 8890 Newtons. Use g = 9.81 Kg/N.
#13. Where is the C of G datum of the MRJT 1 aircraft described in the CAP 696 loading manual?
#14. Where is the C of G of the aircraft illustrated below?
#15. What is the total moment of the unusable fuel is carried in the center and wing tanks of the MRJT 1 as described in the CAP 696 loading manual?
#16. What is the fuel index of 14080 Kg. of fuel in the MRJT 1 aircraft described in the CAP 696 loading manual, if the fuel index of 16080 Kg is -17.1, and the fuel index of 2000 kg is -3.3?
#17. Where is the C of G of the aircraft illustrated below?
#18. What is the fuel index of 9080 Kg of fuel in the MRJT 1 aircraft described in the CAP 696 loading manual, if the fuel index of 11080 Kg is -4.5, and the fuel index of 2000 kg is -3.3?
#19. Using the conversions factors in the CAP 696 loading manual, estimate the mass of 350 Imperial gallons of JET A1 if its specific gravity is 0.80?
#20. How will landing gear retraction affect the C of G position of a large aircraft?
#21. Where is the C of G of the aircraft illustrated below?
#22. Where is the C of G datum for the SEP 1 aeroplane in Section II of the CAP 696?
#23. To what is the C of G position of an aircraft most commonly referenced?
#24. Which of the following factors is the most important is determining the allowable limits of movement of the C of G of an aeroplane?
#25. Where is the C of G of the aircraft illustrated below?
#26. using the data for the single engine piston/propeller aircraft in Section II of the loading manual to SEP 1 aircraft provided in the CAP 696 and below, complete the loading manifest below and calculate the C of G position at the times of take-off and landing? Front seat occupants 380 Ib, 3rd & 4th seat passenger 2 x 170 Ib, 60 Ib of passenger baggage in zone B, 120 Ib of passenger baggage in zone C, Total fuel 50 US gallons, trip fuel 40 US gallons.
#27. The position of the C of G of an aircraft?
#28. Where is the C of G of the aircraft illustrated below?
#29. How far will the C of G of the MRJT 1 aircraft move when its flaps are retracted from 15° to 0° at a mass of 60000 Kg?
15° to 0°
#30. Where is the C of G of an aircraft if it has a nose wheel at +305 inches supporting 22000 Kg, left and right main gear at +1245 inches supporting a total of 75300 Kg, and body gear at +1378 inches supporting 64900 Kg?
#31. What are the total mass and C of G position of the aircraft in the diagram if the load on the nosewheel is 750 Newtons, and those on the main wheels are 5950 N and 5950 Newtons. Use g = 9.81 Kg/N.
#32. Calculate the C of G position of the aircraft below? Left main wheel load = 12250 Kg. Nose wheel load = 2650 Kg. Right main wheel load = 12150 Kg.
#33. What are the total mass and C of G position of the aircraft in the diagram if the load on the nosewheel is 975 Newtons, and those on the main wheels are 9750 N and 9750 Newtons. Use g = 9.81 Kg/N.
#34. Where is the C of G of an aircraft if the results of a routine weighing are as follows:
#35. Where is the C of G of an aircraft if the results of a routine weighing are as follows:
#36. What are the total mass and C of G position of the aircraft in the diagram if the load on the nosewheel is 1000 Newtons, and those on the main wheels are 9000 N and 9000 Newtons. Use g = 9.81 Kg/N.
#37. Where is the C of G of an aircraft if the results of a routine weighing are as follows:
#38. Where is the C of G of an aircraft if the results of a routine weighing are as follows:
#39. What are the total mass and C of G position of the aircraft in the diagram if the load on the nosewheel is 1000 Newtons, and those on the main wheels are 9000 N and 9000 Newtons. Use g = 9.81 Kg/N.
#40. Where is the C of G of an aircraft if the results of a routine weighing are as follows:
#41. What are the total mass and C of G position of the aircraft in the diagram if the load on the nosewheel is 1000 Newtons, and those on the main wheels are 9000 N and 9000 Newtons. Use g = 9.81 Kg/N.
#42. The datum of an aircraft is directly above the centre of the main wheels, and the nosewheel 275 inches forward of the main wheels. Where is the C of G if the readings during a routine weighing were 579 Ib at the nosewheel, 7435 Ib at the left main wheel and 7460 Ib at the right main wheel?
#43. Where is the C of G of an aircraft if the results of a routine weighing are as follows: Scales: Nose wheel, Right main wheel, Left main wheel. Distance from datum: +78 inches, +257 inches, +257 inches. Load: 650 Ib, 9950 Ib, 9970 Ib.
#44. Where is the C of G of the aircraft illustrated below?
#45. The datum of an aircraft is directly above the centre of the main wheels, and the nosewheel 225 inches forward of the main wheels. Where is the C of G if the readings during a routine weighing were 455 Ib at the nosewheel, 7430 Ib at the left main wheel and 7440 Ib at the right main wheel?
#46. Calculate the C of G position of the aircraft below? Left main wheel load = 16250 Kg. Nose wheel load = 5150 Kg. Right main wheel load = 16150 Kg.
#47. Where is the C of G of an aircraft if the results of a routine weighing are as follows: Scales: Nose wheel, Right main wheel, Left main wheel. Distance from datum: +85 inches, +290 inches, +290 inches. Load: 650 Ib, 9950 Ib, 9970 Ib.
#48. The datum of an aircraft is directly above the centre of the main wheels, and the nosewheel 205 inches forward of the main wheels. Where is the C of G if the readings during a routine weighing were 600 Ib at the nosewheel, 6000 Ib at the left main wheel and 6000 Ib at the right main wheel?
#49. Calculate the C of G position of the aircraft below? Left main wheel load = 16250 Kg. Nose wheel load = 6650 Kg. Right main wheel load = 16150 Kg.
#50. Where is the C of G of an aircraft if the results of a routine weighing are as follows: Scales: Nose wheel, Right main wheel, Left main wheel. Distance from datum: +78 inches, +257 inches, +257 inches. Load: 650 Ib, 9950 Ib, 9970 Ib.
#51. Where is the C of G of an aircraft if the results of a routine weighing are as follows: Scales: Nose wheel, Right main wheel, Left main wheel. Distance from datum: +48 inches, +125 inches, +125 inches. Load: 450 Ib, 6950 Ib, 6970 Ib.
#52. Calculate the C of G position of the aircraft below? Left main wheel load = 16250 Kg. Nose wheel load = 6650 Kg. Right main wheel load = 16150 Kg.
#53. Where is the C of G of an aircraft if the results of a routine weighing are as follows: Scales: Nose wheel, Right main wheel, Left main wheel. Distance from datum: +67 inches, +252 inches, +252 inches. Load: 850 Ib, 8750 Ib, 8740 Ib.
#54. Where is the C of G of an aircraft if the results of a routine weighing are as follows: Scales: Nose wheel, Right main wheel, Left main wheel. Distance from datum: +52 inches, +256 inches, +256 inches. Load: 850 Ib, 5950 Ib, 5750 Ib.
#55. The datum of an aircraft is directly above the centre of the main wheels, and the nosewheel 175 inches forward of the main wheels. Where is the C of G if the readings during a routine weighing were 379 Ib at the nosewheel, 5435 Ib at the left main wheel and 5450 Ib at the right main wheel?
#56. Where is the C of G of the aircraft illustrated below?
#57. The datum of an aircraft is directly above the centre of the main wheels, and the nosewheel 295 inches forward of the main wheels. Where is the C of G if the readings during a routine weighing were 750 Ib at the nosewheel, 9750 Ib at the left main wheel and 9760 Ib at the right main wheel?
#58. Calculate the C of G position of the aircraft below? Left main wheel load = 15000 Kg. Nose wheel load = 2750 Kg. Right main wheel load = 14950 Kg.
#59. An aircraft has twin main gear legs 25 m aft of the nose wheel, and twin body gear legs 5 m aft of the main gear. When the aircraft is weighed the loads are 15000 Kg on the nose gear scales, 32000 Kg on each main gear scale and 24000 on each body gear scale. Where is the C of G?
#60. Calculate the C of G position of the aircraft below? Left main wheel load = 13750 Kg. Nose wheel load = 3755 Kg. Right main wheel load = 14075 Kg.
#61. An aircraft has twin main gear legs 25 m aft of the nose wheel, and twin body gear legs 5 m aft of the main gear. When the aircraft is weighed the loads are 15000 Kg on the nose gear scales, 32000 Kg on each main gear scale and 24000 on each body gear scale. Where is the C of G relative to the main gear?
#62. Calculate the C of G position of the aircraft below? Left main wheel load = 12750 Kg. Nose wheel load = 1745 Kg. Right main wheel load = 12348 Kg.
#63. An aircraft has twin main gear legs 25 m aft of the nose wheel, and twin body gear legs 5 m aft of the main gear. When the aircraft is weighed the loads are 15000 Kg on the nose gear scales, 32000 Kg on each main gear scale and 24000 on each body gear scale. Where is the C of G relative to the body gear?
#64. Calculate the C of G position of the aircraft below? Left main wheel load = 15000 Kg. Nose wheel load = 2750 Kg. Right main wheel load = 14950 Kg.
#65. The datum of an aircraft is directly above the centre of the nosewheel, and the main wheels are 230 inches aft of the nosewheel. Where is the C of G relative to the main wheels if the readings during a routine weighing were 750 Ib at the nosewheel, 9750 Ib at the left main wheel and 9760 Ib at the right main wheel?
#66. An aircraft has twin main gear legs 30 m aft of the nose wheel, and twin body gear legs 5 m aft of the main gear. When the aircraft is weighed the loads are 13000 Kg on the nose gear scales, 30000 Kg on each main gear scale and 27000 on each body gear scale. Where is the C of G relative to the body gear?
#67. What is the allowable C of G range of the MEP 1 aircraft defined in the CAP 696, when the aircraft mass is 3200 Ib?
#68. Where is the C of G of the aircraft below? Left main gear scales 14500 Kg. Nose gear scales 5450 Kg. Right main gear scales 14750 Kg.
#69. The datum of an aircraft is directly above the centre of the nosewheel, and the main wheels are 230 inches aft of the nosewheel. Where is the C of G relative to the nosewheel if the readings during a routine weighing were 750 Ib at the nosewheel, 9750 Ib at the left main wheel and 9760 Ib at the right main wheel?
#70. Where is the C of G of the aircraft below? Left main gear scales 17000 Kg. Nose gear scales 6650 Kg. Right main gear scales 16950 Kg.
#71. What is the allowable C of G range of the MEP 1 aircraft defined in the CAP 696, when the aircraft mass is 3000 Ib?
#72. Where is the C of G of an aircraft relative to its nosewheel, if the load on its two main wheels are the same as that on its nosewheel?
#73. What is the allowable C of G range of the MRJT 1 aircraft defined in the CAP 696, when the aircraft is at a mass of 55000 Kg?
#74. Calculate the C of G position of the aircraft below? Left main wheel load = 13750 Kg. Nose wheel load = 3950 Kg. Right main wheel load = 14050 Kg.
#75. What is the allowable C of G range of the MEP 1 aircraft defined in the CAP 696, when the aircraft mass is 4400 Ib?
#76. The datum of an aircraft is directly above the centre of the main wheels, and the nosewheel 395 inches forward of the main wheels. Where is the C of G if the readings during a routine weighing were 650 Ib at the nosewheel, 9700 Ib at the left main wheel and 9745 Ib at the right main wheel?
#77. What is the allowable C of G range of the MRJT1 aircraft defined in the CAP 696, when the aircraft is at its maximum zero fuel mass?
#78. The datum of an aircraft is directly above the centre of the nosewheel, and the main wheels are 230 inches aft of the nosewheel. Where is the C of G if the readings during a routine weighing were 750 Ib at the nosewheel, 9750 Ib at the left main wheel and 9760 Ib at the right main wheel?
#79. Where is the C of G position of the aircraft illustrated below? 535 Ib on nose wheel scales. 1350 Ib on left main wheel scales. 1370 Ib on right main wheel scales.
#80. Where is the C of G of the aircraft illustrated below?
#81. Where is the C of G of the aircraft below?
#82. Where is the C of G position of the aircraft illustrated below?
#83. Retraction of the landing gear in the SEP 1 aircraft defined in the CAP 696?
#84. What is the allowable C of G range of the MEP 1 aircraft defined in the CAP 696, when the aircraft is at its maximum structural take-off mass?
#85. Where is the C of G of the aircraft below?
#86. Where is the C of G position of the aircraft illustrated below
#87. What is the allowable C of G range of the MEP 1 aircraft defined in the CAP 696, when the aircraft mass is 3800 Ib?
#88. What is the allowable C of G range of the MRJT1 aircraft defined in the CAP 696, when the aircraft is at its maximum structural take-off mass?
#89. Where is the C of G of the aircraft below?
#90. Where is the C of G position of the aircraft illustrated below?
#91. Where is the C of G of the aircraft below?
#92. Where is the C of G position of the aircraft illustrated below?
#93. Where is the C of G of the aircraft illustrated below?
#94. Where is the C of G of the aircraft below?
#95. Where is the C of G of the aircraft illustrated below?
#96. Where is the C of G position of the aircraft illustrated below?
#97. Where is the C of G of the aircraft illustrated below?
#98. Where is the C of G of the aircraft below?
#99. Where is the C of G of the aircraft illustrated below?
