Abstract: A nacelle for housing an engine includes a fan cowl sized to cover at least a first axial portion of the engine. The engine includes an inlet end, an exhaust end, and an axis extending through the engine from the inlet end through the exhaust end. The fan cowl is coupled to an engine mounting pylon via a mounting assembly including at least one power drive system. The fan cowl is movable with respect to the engine along the axis toward at least one of the inlet end and the exhaust end.

Abstract: A nacelle for housing an engine includes a fan cowl sized to cover at least a first axial portion of the engine. The engine includes an inlet end, an exhaust end, and an axis extending through the engine from the inlet end through the exhaust end. The fan cowl is coupled to an engine mounting pylon via a slider-type mounting system that includes at least one slider track assembly defining at least one slot therein. The at least one slot is configured to receive at least one fan cowl slider fitting.

Abstract: An anti-icing system includes a component surface having a composite structure including a composite layer, and at least one heating element formed within the composite layer, wherein the heating element is configured to provide a transfer of heat to the component surface.

Abstract: A nacelle for housing an engine includes a fan cowl sized to cover at least a first axial portion of the engine. The engine includes an inlet end, an exhaust end, and an axis extending through the engine from the inlet end through the exhaust end. The fan cowl is coupled to an engine mounting pylon via a mounting assembly including at least one power drive system. The fan cowl is movable with respect to the engine along the axis toward at least one of the inlet end and the exhaust end.

Abstract: A nacelle for housing an engine includes a fan cowl sized to cover at least a first axial portion of the engine. The engine includes an inlet end, an exhaust end, and an axis extending through the engine from the inlet end through the exhaust end. The fan cowl is coupled to an engine mounting pylon via a slider-type mounting system that includes at least one slider track assembly defining at least one slot therein. The at least one slot is configured to receive at least one fan cowl slider fitting.

Abstract: A process for producing through-holes in a sheet member to form a perforated article, such as an arcuate (non-planar) acoustic skin suitable for use in an acoustic panel of an aircraft engine nacelle. The process includes deforming a sheet member to have an arcuate shape with an arcuate surface, mounting and rotating the arcuate-shaped sheet member on a mandrel and then, while rotating the sheet member, directing an electron beam at the arcuate surface of the sheet member and deflecting the electron beam toward multiple locations on the arcuate surface to produce the through-holes through the sheet member in a defined hole pattern and thereby yield a perforated arcuate-shaped sheet member with holes having axes substantially normal to the arcuate surface. The holes are not subjected to elongation in a nonuniform manner after they are produced, and have the same transverse cross-sectional shape.

Abstract: A method of assembling a nacelle for a gas turbine engine that includes an inlet end, an exhaust end, and an axis that extends through the engine from the inlet end through the exhaust end is provided. The method includes providing a cowl sized to cover at least a portion of the engine and coupling the cowl to the engine such that the cowl is slideable along the axis toward at least one of the inlet end and the exhaust end.

Abstract: A nacelle assembly and a method for assembling the same is provided. The nacelle assembly includes an inner barrel and an outer structure comprising a highlight and an outer aft section, wherein the highlight is defined by a forward end of the outer structure, wherein the outer aft section includes a point defined by a maximum diameter of the nacelle assembly, wherein the nacelle assembly extends at least between the highlight and the point.

Abstract: An anti-icing system includes a component surface having a composite structure including a composite layer, and at least one heating element formed within the composite layer, wherein the heating element is configured to provide a transfer of heat to the component surface.

Abstract: A method of assembling a nacelle for a gas turbine engine that includes an inlet end, an exhaust end, and an axis that extends through the engine from the inlet end through the exhaust end is provided. The method includes providing a cowl sized to cover at least a portion of the engine and coupling the cowl to the engine such that the cowl is slideable along the axis toward at least one of the inlet end and the exhaust end.

Abstract: A process for producing through-holes in a sheet member to form a perforated article, such as an arcuate (non-planar) acoustic skin suitable for use in an acoustic panel of an aircraft engine nacelle. The process includes deforming a sheet member to have an arcuate shape with an arcuate surface, mounting and rotating the arcuate-shaped sheet member on a mandrel and then, while rotating the sheet member, directing an electron beam at the arcuate surface of the sheet member and deflecting the electron beam toward multiple locations on the arcuate surface to produce the through-holes through the sheet member in a defined hole pattern and thereby yield a perforated arcuate-shaped sheet member with holes having axes substantially normal to the arcuate surface. The holes are not subjected to elongation in a nonuniform manner after they are produced, and have the same transverse cross-sectional shape.

Abstract: A nacelle assembly and a method for assembling the same is provided. The nacelle assembly includes an inner barrel and an outer structure comprising a highlight and an outer aft section, wherein the highlight is defined by a forward end of the outer structure, wherein the outer aft section includes a point defined by a maximum diameter of the nacelle assembly, wherein the nacelle assembly extends at least between the highlight and the point.