Abstract: A hinge assembly may include a support structure and a panel hingedly coupled to the support structure via at least one hinge of a plurality of hinges. The plurality of hinges may include a first hinge having a first rotational axis, a second hinge having a second rotational, and a third hinge having a third rotational axis. The second rotational axis may be collinear and aligned with the third rotational axis such that the second hinge and the third hinge have a shared concentric axis. The first rotational axis may be eccentric to the shared concentric axis. The hinge assembly may be implemented in a nacelle to improve the aerodynamics of the interfaces between the fan cowl and adjacent structure.

Abstract: A nacelle may include a pylon, an adjustable length beam, a first fan cowl, and a second fan cowl. The adjustable length beam may have a first end and a second end and the adjustable length beam may extend in a direction substantially normal to a centerline axis of the nacelle. The first fan cowl may be pivotally coupled to the first end of the adjustable length beam and additionally may be pivotally coupled to the pylon. The second fan cowl may be pivotally coupled to the second end of the adjustable length beam and additionally may be pivotally coupled to the pylon.

Abstract: A nacelle tensioning arrangement may comprise a fairing located between a first fan cowl and a second fan cowl, and a flexible tensioning system configured to restrain at least a portion of the fairing from moving in a radial direction in response to at least one of the first fan cowl and the second fan cowl being in a closed position.

Abstract: A system is provided for an aircraft propulsion system. This system includes a nacelle structure, a nacelle cowl and an alignment assembly. The nacelle cowl is configured to move between a closed position and an open position. The alignment assembly includes a pair of mating components respectively arranged with the nacelle structure and the nacelle cowl. A first of the pair of mating components is configured as or otherwise includes a receptacle. A second of the pair of mating components is configured as or otherwise includes a locator. The locator is configured to mate with the receptacle and thereby locate the nacelle cowl relative to the nacelle structure when the nacelle cowl is in the closed position. The locator includes a base and a guide attached to the base. The guide is formed as a discrete body from the base.

Abstract: A hinge assembly may include a support structure and a panel hingedly coupled to the support structure via at least one hinge of a plurality of hinges. The plurality of hinges may include a first hinge having a first rotational axis, a second hinge having a second rotational, and a third hinge having a third rotational axis. The second rotational axis may be collinear and aligned with the third rotational axis such that the second hinge and the third hinge have a shared concentric axis. The first rotational axis may be eccentric to the shared concentric axis. The hinge assembly may be implemented in a nacelle to improve the aerodynamics of the interfaces between the fan cowl and adjacent structure.

Abstract: A nacelle may include a pylon, an adjustable length beam, a first fan cowl, and a second fan cowl. The adjustable length beam may have a first end and a second end and the adjustable length beam may extend in a direction substantially normal to a centerline axis of the nacelle. The first fan cowl may be pivotally coupled to the first end of the adjustable length beam and additionally may be pivotally coupled to the pylon. The second fan cowl may be pivotally coupled to the second end of the adjustable length beam and additionally may be pivotally coupled to the pylon.

Abstract: A system is provided for an aircraft propulsion system. This system includes a nacelle structure, a nacelle cowl and an alignment assembly. The nacelle cowl is configured to move between a closed position and an open position. The alignment assembly includes a pair of mating components respectively arranged with the nacelle structure and the nacelle cowl. A first of the pair of mating components is configured as or otherwise includes a receptacle. A second of the pair of mating components is configured as or otherwise includes a locator. The locator is configured to mate with the receptacle and thereby locate the nacelle cowl relative to the nacelle structure when the nacelle cowl is in the closed position. The locator includes a base and a guide attached to the base. The guide is formed as a discrete body from the base.

Abstract: A nacelle tensioning arrangement may comprise a fairing located between a first fan cowl and a second fan cowl, and a flexible tensioning system configured to restrain at least a portion of the fairing from moving in a radial direction in response to at least one of the first fan cowl and the second fan cowl being in a closed position.