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One more extended query to this problem: It is understood that the bolt doesn't transfer the compression loading whereas the compression is transferred through contact between plates in a particular region. The region through which the contact is transferred can be evaluated using the heel-toe...

Thanks der8110 and rb1957. I meant the 'Detail Desing Points' (potential for fatigue crack initiation) which are considered for deriving inspection routine for SSI (Structurally Significant Item) as DDPs. I am still looking for airframe manuals. Meanwhile, few more thoughts on this. Bolts...

Why are the standard parts (actuator rod, bearing, bush or fastener) not considered as critical DDPs? How does the inspection routines are derived for those standard parts? The Manufacturer would have conducted the fatigue test. Unless those have super fatigue life, why aren't those parts...

I remember the example for stress concentration superposition. Considering the following case: 1) A hole in a plate 2) A notch at the edge of the hole Stress concentration for each calculated separately. 1) Hole - Kt of 3 2) Notch - Kt of 2 Stress concentration superposition (assuming the notch...

Thanks for the answers... The increment in cost for having scalloped edges might vary for types of manufacturing?. For example, having a scalloped edges in a machined doubler comparing to a sheet doubler. Honestly, I have no clue about how much it will cost involves for making a component. And...

From fatigue aspect, is it possible that scalloping the components at free edges would be more critical than non-scalloped component? Assume, minimum edge distances of holes are maintained, it is well designed that no stress concentration interactions between fastener holes and scalloped portion...

Thanks rb1957 for clarifying the exact location of the problem (no frames are near to cut-out). Yes, the local stress concentration effect is significant closer to cut-out. [highlight #729FCF]...the test is to calculate crack opening size and compare with a tip-to-tip crack ...[/highlight] I...

When we do Damage Tolerance Analysis for fuselage skin panel cut-outs, We usually assume a primary flaw (0.05") on one side of cut-out and continuing damage on other side of cut-out (e.g. 0.005"). When we grow the crack, at some point of time, cracks on both sides of the cut-out are assumed to...