Patent ID: 9663238
Date: 2017-05-30
CPC Classifications: B64D,F02C,Y10T

Claim:
1. A nacelle inlet for a turbo-fan engine for an aircraft, the nacelle inlet comprising: a lip skin comprising an inner barrel including a forward flange having a second mating surface; a bulkhead comprising wherein the first, second and third mating surfaces are each machined to be approximate developable surfaces with the first and second mating surface having parallel ruling lines with the third mating surface, said angle flange adapted for mating of the fourth and fifth mating surfaces prior to engagement between the first leg of the angle flange and the spanning member by a plurality of fasteners, wherein sliding engagement of the first, second and third mating surfaces positions the spanning member, and wherein sliding engagement of the fourth and fifth mating surfaces joins the first leg and the spanning member with greater or lesser overlap of the first leg and the spanning member determined by position of the first and third mating surfaces.