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An aircraft takes off at an aerodrome at 2000 ft and climbs to its cruise altitude of FL200, considering ISA conditions. Its CAS during the climb is 220 kt and the QNH is 1013 hpa. The TAS to be considered for dead reckoning during the climb is...

  • A

    280 kt.

  • B

    277 kt.

  • C

    269 kt.

  • D

    273 kt.

Refer to figure.
"Average TAS used for descent problems is calculated at the altitude 1/2 of the descent altitude."

"Average TAS used for climb problems is calculated at the altitude 2/3 of the climb altitude."

The aircraft takes off from an aerodrome at 2000 ft and climbs to FL200. So, 2/3 of the climb altitude is: 2/3 (FL200 - 2000) = FL120.

Climb 12 000 ft above the aerodrome altitude ⇒ 2000 ft + 12 000 ft = 14 000 ft = FL140

The ISA temperature at FL140 is: 15°C - (2°C x 14) = -13°C.

Using your Flight/Nav computer find the TAS at FL140:

  • In the airspeed correction window set the temperature -13°C against 14 000 ft.
  • Above CAS 220 kt (22) on the inner scale, read the TAS 273 kt to be considered for dead reckoning during climb on the outer scale.

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