OK, I will have to take that as gospel, since I have zero personal skill/experience with actually setting up or cutting parts this way. My only experience was watching someone design bulkhead parts on CAD before he water cut them (for my Cessna landing gear re-design project), and it took a long time designing each part to fit each individual location. So I thought if you could create a universal gusset there would be some huge savings. If that is not the case in reality, then so be it, we'll take that idea out back and napalm it. Or, to quote Goldfinger... "goodbye, Mr. Bond..." On to the next idea: I think that (unlike some of the Baslee style structures) this T'n'G fuselage should judiciously use some 4130 strap fittings that are riveted to the tubes where highly stressed bolts will go. Wing attach, landing gear attach, cabane struts, etc. Some of the ultralight style aircraft use all aluminum for this, but I believe that steel is likely a better choice for bolt loads. Attaching a steel strap fitting or "finger patch" type fitting to aluminum tube, using rivets, will require some gen-u-wine engineering calculations (to be sure you're in bearing failure and not in shear failure). So I would guess that the number of fasteners needs to be higher, to reduce the load on each fastener (because the difference in material stiffness could load the fasteners unevenly as the flight load is applied)??? I'm guessing there would b e a lamination of two or three thinner steel straps to "taper" the thickness - to me that sounds like it is going in the right direction. Any input or volunteer effort from our HBA engineering brain trust?