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Just an opinion. 1. Guaranteed minimum means the design value is smaller than the actual property. No, it is the A- or B-basis. See subparagraphs b1 and b2 for clarification. 2. This means you prove your value through testing. No, a single test is not enough. You must comply with respective...

Steven, You are definitely confusing something. What is the goal of your analysis? Why do you worry about the plastic region reaching the End Of Part? The Neuber's rule should not be used for the entire cross-section. It is valid for a relatively small vicinity of the notch. It is good for...

Hi, gutboy17. Some opinion. 1. Bearing area is calculated as defined, i.e., projection of the rivet. 2. Of course, the countersunk head reduces the bearing stress compared to the protruding head rivet. There is no direct relation between the bearing and shear strength. It is important to...

Thermally shrunk bushings may be no good any more in airplanes because of the risk of condensation. Use press fit or FTI cold expanded bushings instead.

Will HL62-10 or similar fit?

Good questions, AeroNatanio! And you have already receved very good answers. I'll just try to put my two cents on the subject. ======================================== Can I ask another question what happens if it involves fatigue? ===================================== Nothing...

It is a good writing style. Rather an intention of it. You have three forces acting on bolt (c). You must have three projections on each axis. One projection in each case is equal to zero. That's all meaning of the two zeros there.

Because there is no sense to do that for a static strength analysis. Plasticity (permanent deformation) is localized in a small area in this case and USUALLY do not affect the function of the part. Fatigue analysis is a different story.

Thank you rb1957! May I say that cracks found in a joint or fitting (where we have significant load transfer from fastener to fastener) are localized, while cracks found at a wing skin panel spanwise splice (load transfer is almost zero) are generalized in terms of the wing fatigue life? Or...

The question may be stupid, but I cannot find any clear definition of both generalized and localized cracking. Does anybody know the difference, preferably in aircraft structures? Thank you.

Thank you Will, The Sleeve Bolts are interesting. However, if we switch from TL to the Sleeve Bolts, how can we substantiate the aircraft service life? I would say this is a significant design change. We have to prove that the service life is at least not reduced compared to the original one...

Thank you Will, Your detailed description has made clear which factors contribute to superiority of the automated drilling. (Actually, you doubled my knowledge of the process). However, I am not a process engineer. My task is just to evaluate how much of fatigue life we lose when performing...

Thank you gentlemen, My goal is to quantify the difference in fatigue life between automated and manual drilling processes for Taper-Lok installation. My standard approach is to try to conduct an analysis first. The idea was to identify principal physical parameters (like surface roughness...

Thank you gentlemen for your replies. The picture is clearer for me now. However, is there a quantitative measure of the automated drilling/fastener installation benefits in terms of fatigue life for joints with, say, Hi-Lok or Taper-Lok fasteners? The only approach I heard is a smaller...

Thank you, rb1957! It was a valuable piece of information. The pink text book does contain a chart with comparison of relative fatigue lives and Kt for automated rivetting and hand bucked rivets. No details though. A question to all : Is it reasonable to assume that the automated drilling...

Hi all, Automated drilling for fastener installation has been used in airplane assembly for long time. It is known (or believed) it provides better fatigue life. Particularly, I mean wing box stringer-skin joints. I want to quantify the advantage of the automated drilling process over the...