Climb gradient calculation exercise
Hi,
I´m reviewing some stuff, to keep my "atpl knowledge" up to date, and just got stuck on the following exercise:
The second segment requirement for a twin engine aircraft is 2.4%. If the total drag of the aircraft at V2 is 18500lbs and each engine produces 22000lbs of thrust. The maximum permissible take-off weight will be:
a) 145800 lbs
b) 1062500 lbs
c) 91700 lbs
d) 90300 lbs
According to the book, the correct answer is A, but still I cannot get it (I know, monkey stuff).
Climb gradient=(T-D)/W
so,
Climb gradient = (44000-18500)/W
2.4/100=25500/W
From above: W=1062500 (answer b)
What am I doing wrong? Your help is really appreciated. Enjoy the rest of the weekend.