[Defender2]

Here's a little lesson in aerodynamics. Todays airplane consist of a fuselage, wings, horizontal stabililizers, vertical stabilizers. the wings provide lift. the horizontal stabilizers provide pitch axis control(elevation). The vertical stabilizer provides Yaw axis control(rudder). The wings provide lift and attached to these wings are ailerons(or spoilers)which provide Roll Control. If an aircraft travelling at speed encounters a severe change in angle of attack in any of the axis's(Pitch,roll or yaw) design gust loads may be exceeded causing certain parts of the aircraft to rip off, such as a vertical stabilizer, wing, radome, wintip. Are you all starting to understand. In other words if certain design roll, pitch or yaw angles or combination of these are exceeded, let's include "G" limitations are exceeded, structural failure may result. Now the Question Remains, what caused a severe rapid change in angle of attack causing the subsequent inflight breakup of the aircraft?

[justlurking]

Are you all starting to understand.

Yes..... that you are way off the mark.

In other words if certain design roll, pitch or yaw angles or combination of these are exceeded, let's include "G" limitations are exceeded, structural failure may result.

If the plane is not exceeding manuevering speed (the top of the green arc), it will not experience structural failure in the absence of a pre-existing problem. The wing or control surface will become ineffective before it will break.

During the climb-out phase, a transport aircraft does not exceed manuevering speed.