A kit of parts for forming an aerofoil assembly is disclosed having a torsion box structure including a first attachment point and a second attachment point, the first and second attachment points being separated from each other along a separation axis, and a fixed leading or trailing edge structure including corresponding first and second attachment points, wherein a first structure includes a slidebly mounted abutment piece slideable along a slide path extending in a direction parallel to the separation axis and a fixing mechanism for fixing the slidebly mounted abutment piece. A second structure includes a corresponding abutment feature having a first abutment surface facing in a direction parallel to the separation axis of the second structure, such that, in use, the abutment piece prevents relative movement of the first and second structures.

A kit of parts for forming an aerofoil assembly is disclosed having a torsion box structure including a first attachment point and a second attachment point, the first and second attachment points being separated from each other along a separation axis, and a fixed leading or trailing edge structure including corresponding first and second attachment points, wherein a first structure includes a slidebly mounted abutment piece slideable along a slide path extending in a direction parallel to the separation axis and a fixing mechanism for fixing the slidebly mounted abutment piece. A second structure includes a corresponding abutment feature having a first abutment surface facing in a direction parallel to the separation axis of the second structure, such that, in use, the abutment piece prevents relative movement of the first and second structures.

An aircraft joint between overlapping first and second components includes a fastener having a head and a shank, and a fastener retainer fixedly attached to the second component at the overlap region. The fastener retainer has a recess and a through hole. The fastener head is situated in the recess and between the fastener retainer and the second component. The fastener shank extends through the hole in the fastener retainer and into the first component to fasten the first component to the second component. The joint may be between an aircraft wing cover and a wing panel.

An aircraft joint between overlapping first and second components includes a fastener assembly. The fastener assembly includes a threaded fastener and a boss having an outer diameter and a threaded internal bore. The boss is fixedly attached to the second component at the overlap region. The first component has a through hole having a diameter sized to receive the outer diameter of the boss. The boss is received in the through hole from a first side of the first component. The fastener extends through the through hole from a second side of the first component opposite the first side. The fastener is threadably received in the internal bore of the boss and reacts against the second side of the first component to fasten the first component to the second component.

An aircraft joint includes a first component having an outer aerodynamic surface and an inner surface, a second component having an outer aerodynamic surface and an inner surface, and a strap assembly bridging between the inner surfaces of the first and second components. The strap assembly has a first strap part attached to the inner surface of the first component, a second strap part attached to the inner surface of the second component, and a third strap part received in the first and second strap parts in a sliding manner. The third strap part when received in the first and second strap parts constrains movement of the first component relative to the second component in a direction normal to the outer aerodynamic surfaces of the first and second components in the vicinity of the strap assembly.

A leading edge slat of a wing element of an aircraft. The aircraft defining a mark including a main fuselage axis x and a spanwise axis y. The wing procuring a lift along an axis z. The wing element having a skin forming the leading edge slat, a spar linked to the skin and a stiffening structure linked on the leading edge side to the spar and to the skin. The stiffening structure being formed from a formed sheet metal having a plurality of bosses distributed according to the length of the leading edge. The bosses extending between the spar and the inner face of the skin.

A method and apparatus for compacting composite stringers. In one illustrative embodiment, an apparatus comprises a compacting structure, a compactor vacuum system, and a carrier vacuum system. The compacting structure has a shape configured to contact layers of uncured composite material for a composite stringer. The compactor vacuum system is associated with the compacting structure. The compactor vacuum system is configured to cause the compacting structure to apply a pressure to the layers of uncured composite material when a compactor vacuum is applied to the compactor vacuum system. The carrier vacuum system is associated with the compacting structure. The carrier vacuum system is configured to hold the layers of uncured composite material against the compacting structure when a carrier vacuum is applied to the carrier vacuum system.

A leading edge structure for a flow control system of an aircraft is disclosed having a leading edge panel that surrounds a plenum, wherein the leading edge panel has a first side portion, a second side portion opposite the first side portion, an inner surface facing the plenum and an outer surface in contact with an ambient flow, and wherein the leading edge panel comprises a plurality of micro pores forming a fluid connection between the plenum and the ambient flow, wherein the plenum is connected to an air outlet arrangement configured for causing an underpressure in the plenum, so that air from the ambient flow is drawn through the micro pores into the plenum and from there discharged through the air outlet arrangement into the ambient flow.

A structural assembly for an airfoil structure comprising at least one connection member configured to connect a leading-edge member, or a trailing-edge member, of an airfoil structure to a torsion-box member, such that the connection member prevents the leading-edge member, or trailing-edge member, from pivoting relative to the torsion-box member away from an operational position. At least one corresponding support is provided wherein the support is configured to be attachable to the connection member and further configured to be attachable to at least one system element.

A structural assembly for an airfoil structure comprising at least one connection member configured to connect a leading-edge member, or a trailing-edge member, of an airfoil structure to a torsion-box member, such that the connection member prevents the leading-edge member, or trailing-edge member, from pivoting relative to the torsion-box member away from an operational position. At least one corresponding support is provided wherein the support is configured to be attachable to the connection member and further configured to be attachable to at least one system element.