Interesting article, CH274. My perception is that helicopters are more conservative in materials usage than fixed wing. This is most likely because the level of vibration that a helicopter fuselage and mounting structures have to withstand are an order of magnitude above their fixed wing counterparts. Also a big part of fixed wing loading is the pressurisation, which tends to dictate the material thickness
Fatigue on a good day can be a tricky beast to predict. I also get the impression that crack repairs are more acceptable on helicopters, probably because the crack will not immediately cause a catastrophic decompression. Obviously a newer composite will not have had the repair techniques developed yet.