From my understanding the first blade that was sent to the US is yet to be looked at
If this is true then it is an amazing situation. We have a blade that failed in flight and fortunately the aircraft was able to land, and the manufacturer issues a change for the blade to be reworked. Is this the blade that hasn't been looked at? If so, what is the basis for the modification for the blade? Just a knee jerk "it must be a stress concentration problem" by the manufacturer without any engineering forensics on the failure? Really?
Add to that, we have had a fatal crash with the same blade type. I would have thought that would add impetus to the investigation of the first blade.
Even then, I bet that the analysis will concentrate on the fatigue crack itself without investigation other possible initiating factors. I would like to see a thorough forensic assessment on any contribution of adhesive bond issues, even if it is to exclude such causes.
Regards
blakmax