Scott Hersha
Well Known Member
Here's a question for the group about G load limits on our airplanes. I currently have an RV4 with a max gross weight of 1500#. The aerobatic gross weight is 1375. I believe that at 1375# my design limits are +6/-3G's. My question is - are G load limits v.s. gross weight linear? If so, the design load limits at the design gross weight (1500 pounds) would be +5.5/-2.75. What I would like to do is increase my gross weight to 1600# to allow me to take a human for a ride in the back seat (v.s. a stuffed animal). If I could raise my gross weight to 1600, that would fill my requirements, and the linear calculation on G-limits would be +5.15625/-2.578. I don't know if this is correct, or if the structural G limits are linear. I understand that testing needs to be done at the increased gross weight (1600#), to determine controllability, stall characteristics, and performance calculations - entering phase I again to accomplish this. I also know that this has been done before, but I don't know the limits that were declared. I would be happy to declare Utility Category limits (+4.4/-1.79 G's) anytime I potentially exceed my design aerobatic gross weight limits if I knew that increasing my gross weight (while lowering the G limits) doesn't violate my limitations, and any insurance coverage requirements. Like I said, I know this has been done before - thoughts?