Originally Posted by Wilyflier
Can any one equate the design strength of the VS with the max possible deceleration "G" in any sort of flat ditching, and the forward "G" required to permit a fin and rudder to rip clean off its fittings?
The whole aircraft should basically hang together (as far as compromising the pax cabin) at 9g deceleration...
I have no idea though, what decel 'g' in a flat ditching situation would fail the fin as suggested by the BEA report... other than more than 3g