In your first response to me, you indicated that 50-70 in/lbs with thicker tension AN365-428A nuts... The bolt are now 60 in/lbs +- 4%. Now why 100 in/lbs?
Good question. Because on further reflection, although the canard lift tab bolts are in single shear, part of their purpose it to put substantial friction force between the lift tab and F-22 in order to transfer the lift loads. Because, if the F-22 was build correctly, there's an AL bushing that the bolt/nut squeezes (and the plans call for an AN4-12A bolt, not a 13A, so be careful that you're not bottoming out the bolt threads) you can't crush the foam/fiberglass structure of the F-22 bulkhead, I think that it's better to go tighter than just a "bolt in shear" level.
But I don't think that there's anything unsafe about the 50 - 70 in-lb range - you just get more margin if you go to the maximum capability of the bolt and nut, which is 100 in-lb.
I'm sorry for revising my thought process as I went along and confusing you. As long as you've got more than 50 in-lb on the bolt, you'll be safe.
Sadly, the plane (VE, LE, COZY) don't spec a torque for these bolts, which are just about the most important ones in the plane :-).
I believe the specification to the letter at 50-70 in/lbs. This is the table that I found...
This is what I was trying to avoid......improper info on my part during application.
So that table you found is 1/2 of Table 7-1 in Chapter 7 of AC43.13-1B (downloadable from the FAA, and an indispensable reference tool). It's only the torque levels for bolts in shear - it doesn't show the maximum allowable torque limits for bolts in tension, which is where the 100 in-lb. comes from.
SO......I should be using the Advisory Circular then?
Unless there's some good reason to use some random document found on the web (like the AC doesn't mention the issue and there's no other master source), AC43.13-1B is the canonical document for aircraft maintenance.
I did read a previous thread that indicated 10 fl/lbs was way too much. Bordering on crushing the structure.
You won't crush the structure of the VE if the bushing was installed during the build process, but you WILL deform the bolt, possibly stripping the threads and/or stretching the bolt. 100 in-lb is 8 and a tiny bit ft-lb, so yeah - 10 ft-lb (not 10 ft/lb) is way too much and will harm the bolts.
Sorry for confusing you and changing the story midstream. Basically, in this case, anything between 50 in-lb (lowest # to use for bolts in shear with an AN365 nut) and 100 in-lb (highest # to use without harming the bolt/nut) will keep your canard on the airplane safely. Which is why I rarely use a torque wrench to install the bolts - once I know by feel with a certain wrench how much 100 in-lb is, I just go somewhat less than that, and call it good.
Hope this is clearer than mud.