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Scott--

Yeah, yeah, I've heard all that before...

But what about the Young's Modulus of the spruce longerons (E=1,500,000)
vs. the Young's Modulus of the fiberglass fuselage (E=10,600,000), hmmm?
This is a much bigger ratio than between glass-epoxy and carbon fiber
(E=35,000,000). Shouldn't the "stiffer" glass-epoxy fuselage break before
the spruce longerons in the standard design?

And wouldn't the epoxy (E=2500) joining the two layers fail long before
either the glass-epoxy or the carbon fiber failed?

Yes, the worst that will happen to my plane is that cracks develop where
the epoxy holding the carbon fiber to the pre-preg fails in shear, in which
case I am back to the "standard" strength and will have to repaint my plane.