A protective cap (1) is proposed for an end of an elongate member (6), such as a male connecting end of a pipe or tube. The cap (1) comprises a sheath of flexible, resilient (i.e. elastic) material (2) to cover part of the outer surface of the member (6) at an end of the member. The protective cap (1) can be applied to the end of the member by unfurling at least part of the sheath 3 from a gathered configuration, such as a rolled-up configuration. The protective cap (1) includes resilient ridges (8) extending inwardly from an insert member (2), and/or a chip at least partly within the cap.

In order to integrate an aerodynamic box without a solid shim, a spar joint is provided. The spar joint comprises a first spar having a first spar contact surface and a second spar having a second spar contact surface. When the first and second spars are fixed to each other, the first and second contact surfaces engage each other in a manner forming a contact plane. The first and second contact surfaces are inclined such that a first imaginary plane that is an extension of the contact plane in a chordwise direction forms at least one intersection with a second imaginary plane that is originating from a chordwise extremal end of an aerodynamic skin. The spar joint is used in aerodynamic boxes, such as flap boxes and TE boxes. The spar joint is also used in airfoil profiles.

Structural members containing energy storage are disclosed. An example apparatus includes a first spring unit having a first plate spaced from a second plate and a first biasing element positioned between the first plate and the second plate. The first biasing element enables the first plate to move relative to the second plate in a direction along a longitudinal axis of the apparatus. A second spring unit has a third plate spaced from a fourth plate and a second biasing element positioned between the third plate and the fourth plate. The second biasing element enables the third plate to move relative to the fourth plate along the longitudinal axis of the apparatus. A battery is positioned between the first spring unit and the second spring unit.

A composite core assembly includes a composite core structure having internal material interfaces and an attachment rail coupled to the composite core structure. The attachment rail includes a first planar surface and a second planar surface adjoined with the first planar surface. The first planar surface is arranged parallel to an internal material interface plane of the composite core structure, and the first planar portion is at least partially integrated into the composite core structure in an internal material interface plane. At least a portion of the first planar surface extends beyond a perimeter surface of the composite core structure, and the second planar surface is configured to attach to the surrounding support member. The core material does not have net edge facets or flat edges positioned next to surrounding structure, and/or may not have a structure arranged parallel to the adjacent support structure to attach to the support structure.

Aircraft main landing gear drag brace backup fitting assemblies and related methods are described herein. An example aircraft wing disclosed herein includes a rear spar having a rear side and a front side opposite the rear side, a side-of-body rib coupled to the rear spar, a rib post disposed on the front side of the rear spar, where the rib post is to couple a second rib to the rear spar, a side-of-body fitting coupled to the side-of-body rib, an intercostal member coupled between the side-of-body fitting and the rib post, and a drag brace fitting disposed on the rear side of the rear spar. The drag brace fitting is coupled to the rib post and the side-of-body fitting via a first plurality of fasteners extending through the rear spar.

A control surface actuation mechanism for moving a control surface relative to a fixed aerofoil portion of an aircraft is disclosed including an articulating support, a sliding member on the articulating support and coupled to the control surface, the sliding member arranged to slide relative to the articulating support, a track with a path for attachment on the fixed aerofoil portion, and a rigid connecting element connected to the first track and to the sliding member. The first end of the first rigid connecting element is configured to move passively along the path, as the sliding member is driven to slide relative to the articulating support by an actuator.

A method of curing an aircraft component including applying a temperature sensitive adhesive to a surface of a component, the surface having a contour; positioning a heating tool including a manifold with a ventilation path such that the ventilation path is adjacent to the surface by aligning the ventilation path to the contour of the component; and heating the surface of the component with uniform airflow from the ventilation path; wherein the manifold includes a chamber with a diverging portion configured to provide uniform airflow through the ventilation path to provide heating to the surface.

Methods of assembling an aircraft wing includes adhering fuel dams to stringers and adhering the fuel dams to ribs. Fuel dams include a fuel-dam body that defines a channel shaped to receive a portion of a stringer of an aircraft wing. The fuel-dam body includes a stringer adherent surface, a rib adherent surface, and a pair of spaced-apart flanges extending from the rib adherent surface and positioned to project from the rib adherent surface on opposing sides of a notch of a rib.

A wing-box structure for an aircraft is disclosed having an upper cover, a lower cover, longitudinal forward and rearward spars, and a plurality of transverse ribs. One of the transverse ribs is retained by a pair of opposed captive features disposed on an interior side of either the forward and rearward spars or the upper and lower covers. The rib is bonded rib to the forward and rearward spars and/or the upper and lower covers at a location where the rib is retained.

A trailing edge for a composite lifting surface is disclosed having a spar, an upper panel and a lower panel each having a free edge, a seal, and an elongated profile located on the panels following a spanwise direction of the trailing edge. An elongated profile including a web extending along the spanwise direction of the trailing edge, and having first and second flange portions, and a transition zone in between the first and second flange portions extending at different heights with respect to each other. The first flange portion is configured to hold at least a part of the seal underneath, and the second flange portion is configured to contact the panel so that the first flange portion secures the seal to the panel, and the second flange portion secures the elongated profile to the panel.