Abstract: A secondary oil system for a flight propulsion gas turbine engine having vertical and horizontal flight modes includes an annular reservoir tank in a bearing sump of the engine around a rotor shaft of the engine, a pipe connected to the primary oil system of the engine extending through the reservoir tank and conducting a primary oil flow to a bearing in the sump, an inlet orifice at the top of the reservoir tank in each of the horizontal and vertical flight modes between the pipe and the reservoir tank for conducting a part of the primary oil flow to the reservoir tank, a discharge orifice at the bottom of the reservoir tank in each of the vertical and horizontal flight modes having a flow are limiting a gravity induced secondary oil flow from the reservoir tank to a secondary oil flow rate substantially less than the primary oil flow rate, and a passage conducting the gravity induced secondary oil flow to the bearing in the sump.

Abstract: A propeller shaft nut lock assembly for retention of a propeller shaft bearing assembly includes an externally threaded shaft surface threadably receiving a thrust nut that includes an outboard undercut groove therein to receive a cup lock that is shifted to locate an eccentric segment on the cup lock into interlocking engagement with the undercut groove when a thrust nut lock centers the cup lock on the assembly, and wherein the cup lock includes a plurality of axially extending bendable tangs to indicate that the thrust nut lock assembly is seated in load transfer relationship with the bearing assembly.