A proprotor assembly for a tiltrotor aircraft having a forward flight mode. The proprotor assembly includes a spinner subjected to freestream airflow during forward flight. The spinner is elongated to form a tapered leading portion and a substantially cylindrical aft portion. The spinner forms a plurality of rotor blade cutouts exposing an inner chamber. The proprotor assembly includes a plurality of proprotor blade assemblies protruding radially from the spinner through the rotor blade cutouts. The rotor blade cutouts are formed at the substantially cylindrical aft portion of the spinner to reduce the freestream airflow into the inner chamber via the rotor blade cutouts during forward flight, thereby reducing drag experienced by the tiltrotor aircraft.

In one aspect, a spinner fairing includes a base configured to be fixed relative to a hub system; a movable spinner assembly movable relative to the base; the movable spinner assembly comprising a first movable member and a second movable member. Each first and second movable member being selectively configurable between a closed position and a contracted position, in which the movable spinner assembly has a decreased shape and/or volume. In another embodiment, a spinner fairing can include at least one static member and a moveable member. In still another embodiment, a rotor head fairing assembly includes an upper housing and a lower housing coupled to a hub system; the upper housing including an upper movable member; the lower housing comprising a lower movable member. In yet another embodiment, a rotor head fairing includes at least one moveable upper housing and lower housing.

In one aspect, a spinner fairing includes a base configured to be fixed relative to a hub system; a movable spinner assembly movable relative to the base; the movable spinner assembly comprising a first movable member and a second movable member. Each first and second movable member being selectively configurable between a closed position and a contracted position, in which the movable spinner assembly has a decreased shape and/or volume. In another embodiment, a spinner fairing can include at least one static member and a moveable member. In still another embodiment, a rotor head fairing assembly includes an upper housing and a lower housing coupled to a hub system; the upper housing including an upper movable member; the lower housing comprising a lower movable member. In yet another embodiment, a rotor head fairing includes at least one moveable upper housing and lower housing.

An aircraft spinner assembly includes collar stud joints connecting spinner to forward flange connected to fan rotor disk. Collar stud joint is operable to push out spinner when stud is un-torqued. Collar may be attached to stud disposed through spinner bolt hole in spinner and collar disposed in counterbore of spinner bolt hole. An aft stud thread on collar stud may be threaded into aft nut which may be swaged into flange bolt hole in forward flange. A washer may be in counterbore between collar and spinner and made from low friction and/or sacrificial material. A forward radial clearance may surround stud between stud and spinner. A forward nut may be threaded onto forward stud threads on forward end of the collar stud and abut spinner. External aft stud threads may be on collar studs and threaded into internal flange threads within flange bolt holes in forward flange.

An aircraft spinner assembly includes collar stud joints connecting spinner to forward flange connected to fan rotor disk. Collar stud joint is operable to push out spinner when stud is un-torqued. Collar may be attached to stud disposed through spinner bolt hole in spinner and collar disposed in counterbore of spinner bolt hole. An aft stud thread on collar stud may be threaded into aft nut which may be swaged into flange bolt hole in forward flange. A washer may be in counterbore between collar and spinner and made from low friction and/or sacrificial material. A forward radial clearance may surround stud between stud and spinner. A forward nut may be threaded onto forward stud threads on forward end of the collar stud and abut spinner. External aft stud threads may be on collar studs and threaded into internal flange threads within flange bolt holes in forward flange.

A fluid-redirecting structure includes a rigid body having an upstream end, a downstream end, and an axis of rotation, the rigid body incorporating a plurality of troughs each spiralled from a tip at the upstream end to the downstream end about the axis of rotation, the troughs being splayed with respect to the axis of rotation thereby to, proximate the downstream end, direct incident fluid along the troughs away from the axis of rotation.

Embodiments are directed to an aerodynamic spinner fairing having a sidewall and one or more airflow intakes in the sidewall. The airflow intakes are closed during a first phase of flight and open during a second phase of flight. The first phase of flight may be an airplane mode for a tiltrotor aircraft, and the second phase of flight may be a helicopter mode for the tiltrotor aircraft. The airflow intakes may comprise an opening in the sidewall, and a door that is configured to move between a first position covering the opening and a second position exposing the opening to external airflow. An actuator coupled to the door may operate to move the door between the first position and the second position. One or more guide vanes within the aerodynamic spinner fairing may be configured to direct air received via the airflow intakes to provide convection cooling.

A hub for a rotary wing aircraft includes a plurality of rotor blades, and a heat dissipation system including an aerodynamic faring arranged outwardly of the hub. The aerodynamic fairing has an outer surface and an inner surface defining a component receiving zone. An electronic component is mounted to the inner surface of the aerodynamic faring in the component receiving zone.

The invention relates to a protection dish (32) for a counterbore formed in an aircraft mechanical part, said protection dish (32) having an axial cross-section about an axis (A) having substantially the shape of a U, and comprising a substantially annular wall (34) of axis (A) and a substantially cylindrical rim (36) of axis (A) connected to an outer periphery of said substantially annular wall (34). characterised in that said dish (32) is configured to be deformed in response to an axial stress (F) of a determined intensity applied on the substantially annular wall (34) thereof from a first state, wherein the substantially cylindrical rim (36) has a first transverse dimension (E) relative to axis (A), to a second state, wherein the substantially annular wall (34) being deformed, the cylindrical rim (36) has a second transverse dimension (E) relative to the axis (A) that is greater than the first transverse dimension (E) along a transverse direction (T) determined relative to axis (A).

A nosecone assembly having an axially extending centerline is provided. The assembly includes a nosecone body and at least one access panel. The nosecone body has at least one wall that defines an interior cavity. The wall has an interior surface contiguous with the interior cavity, and at least one window aperture extending through the wall. The access panel has first and second face surfaces. The access panel is attached to the wall interior surface within an attachment region that includes first and second attachment region portions partially contiguous with one another. The first and second attachment region portions define an interior unattached region, and the interior unattached region is aligned with the window aperture.