Two aluminum plates, which are part of an aircraft structure, are held together by a grade 7½, UNF bolt. The effective area of the aluminum plates in compression is estimated to be 12 times the cross-sectional area of the steel bolt. The bolt is initially tightened to 90% of its proof strength. Gust loads, varying from zero to P, tend to pull the plates apart (this results in negligible bolt bending). With a safety factor of 1.3, what is the maximum value of P that will not cause eventual bolt fatigue failure? What clamping force will remain when this value of P acts?