ChristiaanJ,
The separation of VS in both cases (AA587 and AF447) occurred at it´s "coupling" to the fuselage. This "coupling" in EADS design appears to be the "point" that fail when the loads exceed the specs. The "connection" between "conventional metal" to "new materials" advanced VS structure.
Question:
Wouldn´t be better/safer to have a "tapered design" with greater "Fault Tolerance" and "Graceful Degradation".
I mean:
Considering the main reason for a big VS is for take off * why not to have a tapered (strength) design?
To keep some VS effect even after exceeding specs limits (due any reason)
(*) Exceptions: Windy and cross wind Landing
Rationale:
Redundancy, fault tolerance and graceful degradation are "defense lines" against our "nightmare": Murphy´s law.
