A beam flange clamp includes a clamp body having a first vise jaw portion with a first gripping surface and a second vise jaw portion with a second gripping surface. The first gripping surface and the second gripping surface are oriented parallel to each other and are offset in height by a predetermined clamping distance. The clamp body further including a bolting portion protruding from the second vise jaw portion opposite of the first vise jaw portion, and at least one bolting hole is formed through the bolting portion.

A rib is disclosed for use in a torque box of a wing structure provided on an aircraft. The wing structure has a skin panel and a stringer coupled to the skin panel. The rib includes a web defining at least one stringer hole sized to receive the stringer, a shear tie coupled to the web and configured to engage the skin panel, and a clip positioned adjacent the at least one stringer hole. The clip has a base coupled to and aligned with the web, a head extending at an angle relative to the base and configured to engage the stringer, and a transition portion extending between the base and the head.

A rib is disclosed for use in a torque box of a wing structure provided on an aircraft. The wing structure has a skin panel and a stringer coupled to the skin panel. The rib includes a web defining at least one stringer hole sized to receive the stringer, a shear tie coupled to the web and configured to engage the skin panel, and a clip positioned adjacent the at least one stringer hole. The clip has a base coupled to and aligned with the web, a head extending at an angle relative to the base and configured to engage the stringer, and a transition portion extending between the base and the head.

A bonded structure is described. The bonded structure includes an outer structure including a close tolerance hole associated with a first accuracy level. The bonded structure includes an interior structure comprising an oversized hole associated with a second accuracy level that is different from the first accuracy level. The bonded structure includes an elastomeric grommet disposed in the oversized hole. The bonded structure includes one or more spacers between the outer structure and the interior structure providing a space between the outer structure and the interior structure. The bonded structure includes a fastener positioned in the close tolerance hole and in the oversized hole. The bonded structure includes a bonding media disposed in the space between the outer structure and the interior structure via one or more channels of the fastener. The bonding media, elastomeric grommet, and oversized hole collectively position the interior structure relative to the outer structure.

An aircraft (102) having a wing assembly (101) including a fixed wing (105) with a wing tip device (103). The wing tip device (103) is moveable between: a flight configuration; and a ground configuration. The outer end of the fixed wing (105) terminates at an outer rib (115), and the inner end of the wing tip device (103) terminates at an inner rib (117). The outer and inner ribs (115, 117) are located on opposing sides of an interface between the fixed wing (105) and the wing tip device (103). The fixed wing-skin (119) terminates inwardly of the interface, but the outer rib (115) has a surface-forming portion (127) forming an extension of the fixed wing-skin towards the interface. The wing tip device-skin (121) terminates outwardly of the interface, but the inner rib has a surface-forming portion (129) forming an extension of the wing tip device-skin towards the interface.

An assembly having a pylon with an upper spar and four lateral scoops, a wing with a skin, longitudinal spars and fittings, and, for each lateral scoop, two fastening assemblies, wherein the skin and the fitting each have a first bore and wherein the upper spar and the lateral scoop each have a second bore, wherein each fastening assembly has a screw passing through the first and the second bores, a nut, two eccentric rings, threaded onto one another and onto the screw, and a system for stopping the eccentric rings rotating. The assembly makes it possible to dispense with the use of the spigots while also ensuring the reaction of the shear forces contained in the XY plane by the bolts on account of the reduced tolerances between the various bores, the external and internal surfaces of the eccentric rings and the plain zones of the screws.

An aircraft propulsion system configured to be supported from an aircraft wing having a leading edge and opposing upper and lower surfaces. The aircraft propulsion system broadly comprises an engine having a core, a fan case, and a nacelle including a plurality of access panels, and an attachment assembly for securing the engine to the aircraft wing. The attachment assembly broadly comprises an upper support section including a number of spars and a number of ribs connected between the spars, a lower support section, and an aft section. The attachment assembly aerodynamically melds the nacelle and the aircraft wing together via the upper support section so that air flowing over the engine flows over the aircraft wing along the upper surface and air flowing laterally alongside the nacelle flows under the aircraft wing along the lower surface.

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.

Composite assemblies are described that include composite spars that are co-cured with one or more sacrificial members on their flanges, forming an integrated sacrificial surface for the composite spars. In one embodiment, the composite assembly includes a composite spar having a web and flanges that project from sides of the web. The composite assembly further includes a sacrificial member of composite materials co-cured with the composite spar on an outer surface of at least one of the flanges. In addition, the sacrificial member has an outer surface that has been machined into conformance with an inner surface of at least one skin panel for an aircraft structure to form a contact surface with the at least one skin panel.

This relates to a composite structural element, in particular a rib or a spar, specifically for use in a torsion box of an aircraft structure such as a vertical tailplane, wherein the structural element defines a coordinate system with a first axis “a” wherein the structural element comprises a substantially planar main section defining a coordinate system with a first axis “a” extending along the longitudinal axis “L” of the structural element and a second axis “b” extending perpendicular to said longitudinal axis “L” within the planar main section and defining an angle of +90° with the first axis “a”, wherein the structural element contains a lay-up of single plies consisting of a fiber-reinforced composite material with a substantially unidirectional fiber orientation.