Abstract: Guide systems for installing aircraft structures are disclosed. An example apparatus includes a first guide structured to be supported by a first hinge component of a first aircraft structure and a second guide structured to be supported by a second hinge component of a second aircraft structure. The first guide is to receive the second guide when the second structure is at an installation angle relative to the first structure. Engagement between the first guide and the second guide to enable rotational movement of the first hinge component and the second hinge component when the second aircraft structure moves to an installed position.

Abstract: An engine attachment system includes a strut box. The strut box includes a longitudinal axis, a forward portion that extends along the longitudinal axis, and an aft portion that extends from the forward portion along the longitudinal axis. The engine attachment system includes a forward attachment apparatus that is coupled to the forward portion of the strut box and that is coupleable to a forward spar of the wing. The engine attachment system includes an aft attachment apparatus that is coupled to the aft portion of the strut box and that is coupleable to an aft spar of the wing. When the strut box is coupled to the wing by the forward attachment apparatus and the aft attachment apparatus, the aft portion of the strut box is positioned under the wing. The strut box is coupleable to an engine.

Abstract: Flexible aft cowls are disclosed. In some examples, an aircraft engine having a flexible aft cowl is disclosed. In some examples, the aircraft engine comprises an aft cowl having a flexible portion defining a throat area adjacent an engine core nozzle of the aircraft engine. In some examples, the flexible portion to move radially between a first radial position in response to pressure within a nacelle not exceeding a pressure threshold and a second radial position in response to pressure within the nacelle exceeding the pressure threshold. In some examples, the throat area defined by the flexible portion is greater when the flexible portion is in the second radial position than when the flexible portion is in the first radial position.

Abstract: Guide systems for installing aircraft structures are disclosed. An example apparatus includes a first guide structured to be supported by a first hinge component of a first aircraft structure and a second guide structured to be supported by a second hinge component of a second aircraft structure. The first guide is to receive the second guide when the second structure is at an installation angle relative to the first structure. Engagement between the first guide and the second guide to enable rotational movement of the first hinge component and the second hinge component when the second aircraft structure moves to an installed position.

Abstract: Flexible aft cowls are disclosed. In some examples, an aircraft engine having a flexible aft cowl is disclosed. In some examples, the aircraft engine comprises an aft cowl having a flexible portion defining a throat area adjacent an engine core nozzle of the aircraft engine. In some examples, the flexible portion to move radially between a first radial position in response to pressure within a nacelle not exceeding a pressure threshold and a second radial position in response to pressure within the nacelle exceeding the pressure threshold. In some examples, the throat area defined by the flexible portion is greater when the flexible portion is in the second radial position than when the flexible portion is in the first radial position.

Abstract: There is provided a load distribution panel assembly for a gas turbine engine. The assembly has a panel structure having at least one circumferential structural panel having a first end, and a second end coupled to a fixed structure of the gas turbine engine. The circumferential structural panel has a first compliant portion extending away from the first end, and has a second stiffened portion angled with respect to and extending radially away from the first compliant portion, and terminating at the second end. The second stiffened portion has a closed stiffened cavity portion integral with a perimeter flange portion. The panel assembly converts fore/aft point load(s) applied to it by load applying apparatus(es), to hoop tension and compression loads, and reacts a load offset in in-plane load(s), to provide uniform load distribution of the fore/aft point load(s) to the fixed structure.

Abstract: There is provided a load distribution panel assembly for a gas turbine engine. The assembly has a panel structure having at least one circumferential structural panel having a first end, and a second end coupled to a fixed structure of the gas turbine engine. The circumferential structural panel has a first compliant portion extending away from the first end, and has a second stiffened portion angled with respect to and extending radially away from the first compliant portion, and terminating at the second end. The second stiffened portion has a closed stiffened cavity portion integral with a perimeter flange portion. The panel assembly converts fore/aft point load(s) applied to it by load applying apparatus(es), to hoop tension and compression loads, and reacts a load offset in in-plane load(s), to provide uniform load distribution of the fore/aft point load(s) to the fixed structure.