Patent ID: 9637241
Date: 2017-05-02
CPC Classifications: B64D

Claim:
1. An aircraft engine mount apparatus that comprises: a frame that comprises a first connector section coplanar with and directly connected to elongate members directly connected to a second connector section, such that: the elongate members extend from the first connector section, along a length of an engine of an aircraft toward an inlet of the engine, to the second connector section; and the first connector section configured to directly connect to a support structure of the engine via openings that penetrate through a thickness of the first connector section; a first linking system that comprises a fixed link and a floating link such that each fixed and floating link directly connects to the second connector section and each fixed and floating link directly connects to a bracket on a fan case of the engine; and a second linking system that comprises a bar and a number of angular-shaped links that directly connect to the bar secured between a number of lugs and directly connected to an underside of the first connector section and wherein each opposing side of the number of angular-shaped links is pivotably connected to a number of brackets on an engine core case.