Id 105 - ATPL - The determination of the maximum mass on brake release, of a certified turbojet aeroplane with 5°, 15° and 25° flap angles on take-off, leads to the following values:Flap angle: 5° 15° 25°Runway limitation (kg): 66000 69500 715002nd segment climb limitation: 72200 69000 61800Wind correction:Headwind: +120 kg / KT Tailwind: -360 kg / KTGiven that the tailwind component is equal to 5 KT, the maximum mass on brake release and corresponding flap angle will be:

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