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The AD note that flipped my opinion on older airframes
I used to fight anyone who wanted to keep flying our 1980s 172s past their scheduled teardown, then I read the actual AD history showing the fatigue life was based on a single stress test from 1975. Found it buried in the FAA docket last Tuesday while researching a spar crack, and now I get why the old timers trust these things with proper inspections. Anyone else dug into the original certification data and come out on the other side?
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