Been talking with a friend lately about the feasibility of a full greenhouse-style skylight in a Cessna-style semi-monocoque construction aircraft. Aside from the fact that a comprehensive STC would need to be granted for such a thing for a certified aircraft, and it would take 5 years of taking your DER to lunch, what are the engineering issues behind this?
What's up there in a Cessna? 2 carrythrough spars, some fuel lines, some control cables, maybe some wiring. Full greenhouse skylights are common in rag and tube construction, but in a monocoque construction the aluminum skin can be critical to the stress-bearing structure of the wing, which is why the modern Cessna wing only requires 1 strut. But what about that region between the wings directly above the cockpit? How much stress does that bear, and is there a good reason (Feds aside) that that skin could not be replaced with acrylic/Lexan/Plexiglas?
I use the Cessna example because it is ubiquitous and well known. There are a few monocoque kits available (Rebel, Tundra) that I would more heavily consider if I could open up that cockpit visibility and make it less cave-like. The old Cessna 120-style porthole skylights are a poor substitute for a full greenhouse.




