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I don't know about exposure, but on the merits it's good news. If the NTSB preliminary report is correct, it supports what at least one structural expert with Skymaster knowledge told me when I analyzed the SIDs. Here's the gist:
"If fatigue-tested to failure, no one knows where it will fail. Cessna doesn't know and I don't know. But I know that the wing-fuselage attach points are the least likely to fail. If I had to guess it would be just outboard of the strut, or perhaps the strut itself, but not at the strut attach point with the wing but further down."
He dismissed a failure at the wing-fuselage attach points because of the massive over-design and because the front attachment, which carries the heavier load, is in compression in flight, meaning that the wing is pushing down on the top of the fuselage, rather than trying to pull up (i.e., separate) from the fuselage.
Ernie
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