An assembly comprising: an integral monolithic structure including: a nacelle portion generally comprising a body of rotation about an axial centerline and including an inlet region and a fan case region cooperating to define an annular wall bounding an axial channel; a ring member disposed in the axial channel; a plurality of radial elements extending from the ring member to the annular wall; and a support structure portion generally extending in an axial direction, wherein the support structure portion includes a forward section integral with the nacelle portion and having an inlet stiffening region radially outward of the annular wall, and an aft section including at least one aircraft mount region, wherein the monolithic structure is attachable to an associated aircraft at the aircraft mount region; a gas turbine engine with a casing being mounted in supporting connection with the monolithic structure and wherein at least a portion of the gas turbine engine extends through the ring member; and a non-rigid interface between the gas turbine engine and the ring member wherein, when mounted on the associated aircraft, the nacelle portion and the support structure portion cooperate to form a first load path operable to transmit an applied nacelle maneuvering force directly to the associated aircraft; and when the applied nacelle maneuvering force is present, the gas turbine engine is substantially isolated from being acted on by the applied nacelle maneuvering force. an integral monolithic structure including: a nacelle portion generally comprising a body of rotation about an axial centerline and including an inlet region and a fan case region cooperating to define an annular wall bounding an axial channel; a ring member disposed in the axial channel; a plurality of radial elements extending from the ring member to the annular wall; and a support structure portion generally extending in an axial direction, wherein the support structure portion includes a forward section integral with the nacelle portion and having an inlet stiffening region radially outward of the annular wall, and an aft section including at least one aircraft mount region, wherein the monolithic structure is attachable to an associated aircraft at the aircraft mount region; a gas turbine engine with a casing being mounted in supporting connection with the monolithic structure and wherein at least a portion of the gas turbine engine extends through the ring member; and a non-rigid interface between the gas turbine engine and the ring member a nacelle portion generally comprising a body of rotation about an axial centerline and including an inlet region and a fan case region cooperating to define an annular wall bounding an axial channel; a ring member disposed in the axial channel; a plurality of radial elements extending from the ring member to the annular wall; and a support structure portion generally extending in an axial direction, wherein the support structure portion includes a forward section integral with the nacelle portion and having an inlet stiffening region radially outward of the annular wall, and an aft section including at least one aircraft mount region, wherein the monolithic structure is attachable to an associated aircraft at the aircraft mount region; a gas turbine engine with a casing being mounted in supporting connection with the monolithic structure and wherein at least a portion of the gas turbine engine extends through the ring member; and a non-rigid interface between the gas turbine engine and the ring member wherein, when mounted on the associated aircraft, the nacelle portion and the support structure portion cooperate to form a first load path operable to transmit an applied nacelle maneuvering force directly to the associated aircraft; and when the applied nacelle maneuvering force is present, the gas turbine engine is substantially isolated from being acted on by the applied nacelle maneuvering force.