The composites did fail, at the join, Fin to Pin. If I have my pairs correct this time, the middle joint has broken (ruptured) in a fashion to suggest aftward stress, the third (aft) pair shows a similar failure from forward stress.
My continued assumption is that the Fin member(s) are of resin matrix construction, and carry the pin (of six total) that bears the stress of all dynamic stresses on the join to the fuselage. The failure appears to have propagated from the pin area outward, in each case. This would suggest a failure of similar description resulting from two opposing forces. Since the fracture is not complete, it is reasonable to assume that these cracks developed while the Fin was restrained in the airframe by the brackets and hoops. I think no one has postulated that the Fin (VS) "simply flew off", but that the failure was continuous, and resulted from several different loadings to include airloads.
If the VS was 'broken' in situ, sufficient movement may have been available to corrupt the sweep of the Rudder (or its attenuation) such that the RTL may have been 'lost', but only in the performance sense.
The depression on the LE of the Fin could be explained by its water entry from free fall as well as a "roll" across the dorsal fin. The damage looks casually like a blunt, rather than a sharp impact.