>>1054863Not entirely sure if the engineers factor in 1.5 x load limits, but there's a good reason they don't advertise their structural tolerances. Even if you exceed the limit and introduce structural damage, it may not be apparent without thorough inspection. The whole point is that once structural deformation is introduced, the aircraft is no longer guaranteed to withstand the loads it was certified to. If the airframe is deformed it will not distribute loads as it was designed, and stressed joints or hairline cracks caused by an over-G will introduce a likely failure point/stress concentration point.
Those stress risers don't disappear, and only get worse until the component fails. It may not fail on that flight, or even the next several. But it will fail eventually.
