Patent ID: 8197191

Claim:
A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange, the nacelle inlet comprising: an acoustic inner barrel having a forward portion and an aft portion; an outer shell comprising a nose lip portion having a trailing inner edge and an outer barrel portion having an aft portion; an aft mounting flange configured for attaching the inlet to the forward flange of the engine fan case; and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft mounting flange; wherein the forward portion of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft mounting flange; and wherein the aft bulkhead connects the outer barrel portion to the aft mounting flange such that a load can be transferred from the outer barrel portion to the aft mounting flange, via the aft bulkhead, with no substantial portion of the load path passing through the acoustic inner barrel.