Originally Posted by
ScandinavianInterest
If the 12 stop pins are not torqued, how to ensure that each of them take an even part of the load?
One would not necessarily need to torque the pins to come close to an even load distribution. There could be even a gap in the unloaded condition.
You would like to achieve first that both the 12 contact pads on the fuselage door frame are all in their theoretical design position, and the 12 abutment faces of the stop pins in the plug are as well. I am not sure if the faces are in one plane or staggered, but it does not matter.
Easy with the plug pins (threads), a tad more tricky on the fuselage pads, if it is actually done there.
With some effort you could get it geometrically right. The actual load distribution under load is then also depending on the plug`s and fuselages`s general and local stiffness properties. Looks quite homogenous on both fuselage and the boxy plug frame. With about 0,5 tons at cruise alt on each pin stuff will elastically flex and settle.