A nacelle may comprise an inlet and a fan cowl aft of the inlet. The fan cowl may include a fan cowl panel configured to rotate between an open position and a closed position. The nacelle may further comprise a securement retainer including a first portion coupled to an interior surface of the fan cowl panel and a second portion coupled to an aft inlet flange of the inlet. The first portion of the securement retainer may be configured to engage the second portion.

A nacelle may comprise an inlet and a fan cowl aft of the inlet. The fan cowl may include a fan cowl panel configured to rotate between an open position and a closed position. The nacelle may further comprise a securement retainer including a first portion coupled to an interior surface of the fan cowl panel and a second portion coupled to an aft inlet flange of the inlet. The first portion of the securement retainer may be configured to engage the second portion.

A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.

A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.

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.

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.

An aircraft propulsion unit including a nacelle and a turbojet engine. The aircraft propulsion unit includes an external envelope, at least one fan casing, at least one actuator, and at least one support structure. The external envelope includes fan cowls. The fan casing cooperates with the fan cowls to define an interior space configured to house a thrust reverser configured to be displaced between a first position and a second position. The actuator configured to move the thrust reverser between the first position and the second position The support structure connects the fan cowls and the fan. The support structure includes at least one aperture configured to allow passage of part of the actuator.

A coupling e.g. for an actuator, includes a housing which is preferably in the form of a ring mounted around the end of an outer rod of the actuator and which can be mounted to a component e.g. a cowl being deployed. Within the housing of the coupling is provided an eccentric bearing mount and bearing arrangement mounted eccentrically to the housing so as to permit some eccentric movement.

A coupling e.g. for an actuator, includes a housing which is preferably in the form of a ring mounted around the end of an outer rod of the actuator and which can be mounted to a component e.g. a cowl being deployed. Within the housing of the coupling is provided an eccentric bearing mount and bearing arrangement mounted eccentrically to the housing so as to permit some eccentric movement.

An assembly is provided for an aircraft propulsion system. This assembly includes a forward thrust duct and a thrust reverser system. The thrust reverser system includes a thrust reverser duct, a bullnose ramp and a plurality of protrusions. The bullnose ramp is adapted to provide a transition from the forward thrust duct to the thrust reverser duct when the thrust reverser system is in a deployed configuration. The protrusions are bonded or formed integral with the bullnose ramp. Each of the protrusions is adapted to interact with boundary layer fluid flowing along the bullnose ramp from the forward thrust duct into the thrust reverser duct when the thrust reverser system is in a deployed configuration.