Abstract: A seal is disclosed having a pair of side walls, a base extending between the side walls, a first concave surface extending inwardly from one of the side walls, a second concave surface extending inwardly from the other side wall, and a convex surface extending between the first concave and second concave surface to form a rounded peak having an apex. The seal has a seal width defined between the seal side walls, and a seal height defined between the apex of the rounded peak and the base. The width is at least twice the height of the seal. The seal is located in a channel recess of a first component opposite a second component to seal between the first component and the second component, the channel recess having a floor and a height defined between the floor and a surface of the first component in which the channel recess is formed.

Abstract: A fiber-reinforced composite structure includes a cut edge; an elastomeric cap covering the cut edge; and an adhesive sealant bonding the elastomeric cap to the cut edge. The fiber-reinforced composite structure is joined to a component and the elastomeric cap includes a generally Z or L-shaped cap with a web bonded to the cut edge of the fiber-reinforced structure and a flange bonded to the component and extending away from the fiber-reinforced structure.

Abstract: A joint comprising: a first component having a face and a bore defined by a bore wall; a second component; a fastener joining the first component to the second component, the fastener comprising a head and a shaft protruding from the head; and a polysulphide gasket comprising a ring which is compressed between the head of the fastener and the face of the first component; and a collar between the shaft of the fastener and the bore wall. The gasket comprises a ring of sealing material surrounding a hole for receiving a fastener, the sealing material comprising an at least partially cured polysulphide sealant. The gasket has a region of increased thickness positioned towards the inner periphery of the ring which flows to form the collar.

Abstract: A sealing member for forming a seal in an aircraft, the sealing member comprising: a sealing material; and a stiffening element which provides structural support to the sealing material and comprises a material with a glass transition temperature below +50° C. The stiffening element is relatively flexible when the aircraft is at low altitude (high temperature) but becomes relatively stiff (increasing resistance to seal flutter) when the aircraft is at cruise altitude (low temperature).

Abstract: A foldable seal comprising an elastomeric seal substrate and at least one molded-in stiffener plate embedded within the seal substrate. Also, a method of manufacturing the seal.

Abstract: A sealing member for forming a seal in an aircraft, the sealing member comprising: a sealing material; and a stiffening element which provides structural support to the sealing material and comprises a material with a glass transition temperature below +50° C. The stiffening element is relatively flexible when the aircraft is at low altitude (high temperature) but becomes relatively stiff (increasing resistance to seal flutter) when the aircraft is at cruise altitude (low temperature).

Abstract: A method of controlling an elastomeric damper. The damper is heated by passing an electric current through the damper or through a heating element in contact with the damper said heating causing a decrease in stiffness of the damper. The elastomeric damper may comprise an elastomeric material filled with electrically conductive particles, and the damper may be heated by passing an electric current through the elastomeric material. Alternatively the damper may be heated using a discrete resistive heating element, such as a coil embedded within the elastomeric damper or wound around it.

Abstract: A sealing member for forming a seal in an aircraft, the sealing member comprising: a sealing material; and a stiffening element which provides structural support to the sealing material and comprises a material with a glass transition temperature below +50° C. The stiffening element is relatively flexible when the aircraft is at low altitude (high temperature) but becomes relatively stiff (increasing resistance to seal flutter) when the aircraft is at cruise altitude (low temperature).

Abstract: A tank for containing a fluid, such as fuel, oil or gas within a chamber. The walls of the chamber are partially defined by a rigid structure having an opening; and partially defined by an elastomeric diaphragm which is attached around its periphery to the rigid structure and covers the opening in the rigid structure. An attachment frame engages the diaphragm and the rigid structure, and extends around the periphery of the diaphragm. The attachment frame has a first portion which engages the diaphragm, and a second portion which is positioned outside an outer edge of the diaphragm and attached to the rigid structure.

Abstract: A blade seal comprising: a base; a tip; a first part formed from an elastomeric material which extends continuously from the base to the tip; and a second part formed from an elastomeric material mixed with conductive filler which extends continuously from the base to the tip. The blade seal is manufactured by compressing the first and second parts together; and curing one or both of the parts as they are compressed together.

Abstract: A bonding lead comprising a core; and a sheath bonded to the core. The core comprises a substrate of fibers coated with nano-objects with at least one dimension between 1 nm and 200 nm. The nano-objects form a continuous electrically conductive network from one end of the bonding lead to the other with some of the nano-objects coating the fibers and others forming bridges between adjacent fibers. The nano-objects may be carbon nanotubes and the core may be woven or knitted. A conductive connector is provided at each end of the bonding lead, for instance a tab formed from an electrically conductive polymer. The lead can be used to dissipate static charge and/or lightning current between components, typically within an aircraft fuel tank.

Abstract: A routing clip for securing a line to a structure comprising: a base for attaching the clip to a structure; and a clamp comprising: a first flexible strap which extends from the base and has one or more projections extending from its side; and a second flexible strap which extends from the base and has a passageway for receiving the first flexible strap and a locking surface which is arranged to engage one of the projections on the first flexible strap to prevent the first flexible strap from being withdrawn from the passageway. At least part of the clip is made from an elastomeric material.

Abstract: An aircraft wing comprising first and second fuel pipe segments which are coupled together with a pipe coupling device comprising a corrugated tube formed from an elastomer filled with conductive material. The pipe coupling device is particularly useful for connecting together fuel pipe segments in an aircraft wing as it removes the need to attach bonding leads between fuel pipe segments to dissipate lightning currents and static.

Abstract: A foldable seal comprising an elastomeric seal substrate and at least one moulded-in stiffener plate embedded within the seal substrate. Also, a method of manufacturing the seal.

Abstract: An aircraft wing assembly comprising: a spar; a fuel tank; a track container which is attached to the spar and extends into the fuel tank; a track which extends through the spar and into the track container; and a high-lift device, such as a slat or flap, carried by the track. The track container comprises a stiffening element encased in an elastomeric sheath. The track container is manufactured by placing a stiffening element and elastomeric material together in a mould; and compressing and heating them to cure and shape the elastomeric material.

Abstract: A joint with a first component; a second component; and an electrical assembly which provides an electrical pathway between the first and second components with an electrical resistance between 100 k? and 10 M?. The electrical assembly comprises a bonding lead; and a pair of connection assemblies each connecting the bonding lead to a respective one of the components. Each connection assembly comprises: a fastener with a shaft which passes through a hole in the component and a hole in the bonding lead, the hole in the bonding lead passing between an inner face of the bonding lead which faces towards the component and an outer face of the bonding lead which faces away from the component, and a washer which is carried by the shaft of the fastener and engages the component and the inner face of the bonding lead. Each washer provides the path of least electrical resistance between the bonding lead and a respective one of the components, each said path having an electrical resistance between 50 k? and 5 M?.

Abstract: A joint on an aircraft, the joint comprising: a first component; a second component; and a bonding lead which provides an electrical pathway between the first and second components. The bonding lead comprises a conductive core and a sheath which covers a substantial length of the core and has a lower electrical conductivity than the core. The path of least electrical resistance between the first component and the core of the bonding lead comprises the sheath, typically with an electrical resistance between 50 k? and 50 M?. By making the electrical resistance of the core much smaller than that of the sheath, the total resistance of the bonding lead remains substantially the same regardless of its length.

Abstract: A method of sealing a gap between first and second aerodynamic surfaces. The width of the gap between the two surfaces is measured to obtain a gap measurement. The width of a seal member is pre-formed in accordance with the gap measurement. The seal member is fitted into the gap such that the seal member is substantially flush with the first and second aerodynamic surfaces. Apparatus for performing the method is also described. The apparatus comprising: a metrology device adapted to measure the width of the gap between the first and second aerodynamic surfaces; a seal member dispenser for dispensing a seal member; and a cutter adapted to cut the seal member to size in accordance with the measurements obtained by the metrology device.

Abstract: A joint with a first component; a second component; and an electrical assembly which provides an electrical pathway between the first and second components with an electrical resistance between 100 k? and 10 M?. The electrical assembly comprises a bonding lead; and a pair of connection assemblies each connecting the bonding lead to a respective one of the components. Each connection assembly comprises: a fastener with a shaft which passes through a hole in the component and a hole in the bonding lead, the hole in the bonding lead passing between an inner face of the bonding lead which faces towards the component and an outer face of the bonding lead which faces away from the component, and a washer which is carried by the shaft of the fastener and engages the component and the inner face of the bonding lead. Each washer provides the path of least electrical resistance between the bonding lead and a respective one of the components, each said path having an electrical resistance between 50 k? and 5 M?.

Abstract: A split grommet assembly comprising a grommet and a clamping ring. The grommet has a body portion with a peripheral edge and a sealing groove round the peripheral edge of the body portion. The grommet also has a gland portion with a peripheral edge, and a hole passing through the body and gland portions. The body and gland portions are each split along a split line which runs from the hole to their peripheral edges. The clamping ring encircles the peripheral edge of the gland portion and can be opened to permit an elongate object to be fitted into the hole via the split line, and closed to apply a compressive load to the peripheral edge of the gland portion which resists opening of the body along the split line.