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An aircraft climbs from ground level to a cruising flight level of 180. In the table the W/V at various flight levels in the area are given.

FL W/V
ground level 260°/25 kt,
30 270°/30 kt,
60 270°/35 kt,
90 270°/40 kt,
120 280°/50 kt,
150 285°/55 kt,
180 290°/55 kt.

Which W/V should be used to solve climb problems e.g. the calculation of the GS from TAS and the Track in climb

  • A
    270°/40 kt
  • B
    280°/50 kt
  • C
    275°/40 kt
  • D
    270°/35 kt

The average TAS during a descent is obtain from the CAS at the altitude that corresponds to 1/2 of the altitude difference.

The average TAS during a climb is obtain from the CAS at the altitude that corresponds to 2/3 of the altitude difference.

2/3 x FL 180 = FL120

The wind to be considered for the performance calculations must be considered at FL120, 280º/50 kt.

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