The 787 marketing materials point out that the CFRP fuselage allows a higher cabin altitude of 6000 ft vs. 8000 ft on conventional aluminum airliners. This obviously implies a higher pressure differential between the inside and the outside, made possible by the greater strength and fatigue resistance of CFRP. I also understand that these cabin altitudes are quoted at the aircraft's ceiling altitude (43000 ft in the case of the 787).

What are the implications for the flying experience? Specifically, will the 787's cabin altitude be varied in such a way as to maintain this higher pressure differential through a wide band of cruise altitudes, well below ceiling altitude -- given that the pressure differential is the same for 6000 ft cabin @ FL430 and 3600 ft cabin @ FL350 ?

A simpler way of asking is, will the 787 cabin altitude be 6000 ft or 3600 ft when cruising at FL350 ?