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Is that a laden swallow? It makes a difference!

There are good suggestions above. I would also add Flabel’s book. There is a course associated with this book (or used to be). I started with the Boeing flight safety classes which gives a solid approach to the basics. I would also add that a mentor is very beneficial. A user of this...

Maybe they were thinking more of weight distribution on the trailer? Just a guess.

My quest is not why. That is easily understood. My question is how! I guess I can research this but currently working on a hard landing study. Not enough time. Thanks for the info RB.

Perhaps they should change the name of their company to Everground?

That's TMA. People should always DYA. ugh! TMA = too many acronyms DYA = define your acronyms (or drink your alcohol)

RB says: but I think the question was more along the lines "I can't get L72 or 2014, but I can get 2024" The OP says this in his last sentence: The main question here is can 2024 be substituted for 2014? as an equivalent?

Berkshire, ANC-5 has 2014. It used to be called 14S and has allowables for both bare and clad flavors. ANC-5 shows the cross reference at the beginning of the aluminum section. Many years ago, I wrote some material substitutions for landing gear into standard repairs. That's a good story...

Would load indicating washers work? https://www.pccfasteners.com/assets/local/documents/product-literature/pli_brochure.pdf?fireglass_rsn=true

The simple solution is to find the fastener load, then bearing stress, and compare to the material bearing allowable.

I was in a meeting with engineers, production, and quality. There were many suggestions of methods to solve the particular problem that was the subject of the meeting. The quality manager shot down every suggestion. Someone then said, "Ed, you need to think outside of the box". Ed replied...

This site has some good beam equations. I think you are looking for 3Ac for two point loads on a pinned beam. http://sprecace.com/node/43

I would recommend a publication from Society of Automotive Engineers called "Fatigue Design Handbook". This should have a chart showing max stress vs. cycles to failure for various surface finishes. Hope this helps.

Thanks for the feedback Alistair! I should have stated an angle of slideslip (AOS) indicator. This would measure the angle of aircraft to the relative wind. Similar to the AOA measurement. I'm not an aero loads guy. I grow crack and perform static analysis but use the CFD loading for finite...

I do not think the task of using the second AOA as a verification is trivial (IMHO). A side slip will cause the two AOA's to disagree. Likely this can be programmed but then the aircraft would need a side slip indicator. It's a tough problem to solve.

Charlie, Yes I agree. I was looking at the incorrect section on the top side. Thanks for your fantastic input. It would be interesting to read the report on this.

This is what I see. The bottom side seems to have crack which is located close to the breaking point. The topside looks like a crack located at breaking point but may just be trash or something. It has a white appearance so maybe someone tried to fill it (however, it's just blurry enough...

I'm not sure if anyone has already brought this up, but it's interesting to look at the street view from google maps. Looks like cracking in the barrier wall and road. Link

Of course the relative stiffness is the key! But I'm just saying that the pole can be stiff enough that choosing to just assume pinned (edit) may not be conservative. I'm just pointing out that this is a beam column and one must understand this relative stiffness to make sure the analysis is...

But depending on how much moment is in the pole you may not be conservative by assuming pinned. It is a beam column in reality.