Originally Posted by Nick Lappos
Thus, the multi engine design must meet the stringent requirements of primary structure (where a total power loss is in the order of 1: billion probability!)
Thanx Nick. How is this demonstrated in primary structure? I take it once the fatigue cycle and material characteristic is established, this is the main criterion for airframe life. What is the powertrain power loss probability requirement in a (relatively) low disk loading heli, and how is that demonstrated?
Mart