Helped a fellow put wings on a Sling today. I was surprised to learn Sling main spar bolts are AN, 125 ksi tensile, 76 Ksi shear, +/- .0015” on the diameter whereas RVs use NAS66, 170 ksi tensile, 95 ksi shear, +/- .0005” on the diameter.
I’m curious what those on VAF who know about bolted joints think. Maybe the aluminum spar plastically deforms until the bolts share the load?
I’m curious what those on VAF who know about bolted joints think. Maybe the aluminum spar plastically deforms until the bolts share the load?