Patent ID: 8672260

Claim:
A mounting system for securing a gas turbine engine to an aircraft support structure comprising: an outer link assembly attachable to the aircraft support structure and the gas turbine engine, the outer link assembly including first and second links disposed in a first plane transverse to the centerline of the gas turbine engine; an upper thrust link disposed along the centerline, wherein the outer link assembly supports vertical loads produced by the gas turbine engine, wherein vertical loads of the gas turbine engine are only supported by structures disposed within the first plane and the upper thrust link extends from an axial forward surface through a slot defined through an outer case of the gas turbine engine within the first plane and into a pocket defined on the aircraft support structure and is secured within the slot and the pocket by at least one fastener extending through the slot, pocket and upper thrust link; and at least one lower thrust link attachable to the aircraft support structure and the gas turbine engine, the at least one lower thrust link attached to the gas turbine engine at a mount location within the first plane transverse to the centerline of the gas turbine engine, wherein the at least one lower thrust link transfers thrust loads produced by the gas turbine engine, and does not support vertical loads produced by the gas turbine engine.