Originally Posted by
megan
Concours, the horizontal stabiliser did not fail in the initial sequence. The aircraft was 27 knots in excess of VNE, the pilot pitched up 8° and the wings failed at the design limit load of +8.3G. No negative G is involved as the aircraft only pitches in a positive direction.For what it's worth I take exception to the lack of observation and deduction evident in your post.What about it?
BRDuBois, by my calculations using the VMC as a starting point, the maximum load the fin/rudder can generate is just a smidgen under 24,000, which occurs at VA. Full rudder beyond VA invites failure. Being back of the envelope stuff we are in agreement. A reminder though that in a balanced turn very little rudder is required.
Sorry, you’re wrong. Slow the video down, and look at the HS(s). They failed
upward, just as the wings did. Without tail downforce, the aircraft instantly lost positive g. Now it is possible that pitch change is not
discernible, but given the failure of both elements upward, it follows there is loss of alpha stability, so it is intuitive that the wings were lost ultimately due to load reversal.
You’ll figure it out.
clue: what is the difference between “failed” and “separated”?