Twoicebergs You are a pro.
Presume that your reference to 7.33 g relates to the F-111 (or what else) which has a design ultimate of 11 g. Where did the 5.85 g come from particularly as the F-111 case is complicated by wing sweep, aileron substitution with spoilers and roll power from the tail.
But if we now start to consider structural loads caused by asymmetric pull outs with all of the variables introduced by the F-111 I suppose we have to placard the worst case and leave it at that unless there are operational advantages in having several worst cases.
Erudite comments?