A tie rod-locking nut assembly includes a tie rod-locking nut threaded onto a jack bolt, a jack bolt-locking nut inserted between the tie rod-locking nut and the jack bolt, an anti-loosening washer formed to wrap around an outer circumferential surface of the jack bolt-locking nut to prevent loosening of the jack bolt-locking nut, and a locking plate formed to cover the anti-loosening washer and engaging with an outer circumferential surface of the tie rod.

A propeller shaft assembly for an aircraft engine includes a shaft having a bore extending through the shaft at a front end thereof, the front end of the shaft having an outer surface facing radially outwardly from the shaft and an inner surface spaced apart from the outer surface and facing radially inwardly to the bore. The shaft has a front flange extending radially outwardly on the outer surface, the front flange having a base merging with the outer surface of the shaft. A sleeve is coupled to the shaft within the bore by an interference fit between the sleeve and the shaft, at least part of the sleeve axially aligned with the front flange. The sleeve axially extends from a front to a rear sleeve end, the rear sleeve end axially offset from the engine side surface of the front flange at the base of the front flange.

A composite component for a gas turbine engine is provided, along with its methods of formation. The composite component includes: an additively printed inner portion defining at least one flowpath feature, and a ceramic matrix composite (CMC) outer portion formed on the additively printed inner portion such that the CMC outer portion substantially surrounds the additively printed inner portion. The additively printed inner portion includes SiC; and the CMC outer portion includes a fiber reinforced ceramic matrix (e.g., including SiC) and defines at least one cooling cavity fluidly coupled to the at least one flowpath feature of the additively printed inner portion.