... change the effective setting of structural integrity. That is, the wing would have abnormal offset and the static aeroelastic behavior of in-flight response has unusual changes. If the company operator could examine such static aeroelastic behavior and fix the problem, those two mishaps could be avoided...

... 2017 09 08 2017 The section hinge moment is defined as follows: (1) h = 1 2 ρ ( Ω r ) 2 c f 2 C h If integrated spanwise, the result is: Structural integrity Static bench test Trailing-edge flap Transient flow analysis Vertical pulling test...