Abstract: A visual warning assembly, configured to make a warning from one vehicle to another vehicle. The visual warning assembly has a case with a front face joined to a base and an antenna. A channel display button, a channel selector button, a power button, a green lighted button, a yellow lighted button and a red lighted button, arranged on the front face. A mounting ball is magnetically joined to the base. A microcontroller is electrically coupled to the green lighted button, the yellow lighted button, and the red lighted button. The microcontroller is programmed with instructions to: receive a communication from a second visual warning assembly. Then, engage one member of a lighted button set consisting of the red button, the yellow button, and the green button creating an indicating light.

Abstract: A visual warning assembly, configured to make a warning from one vehicle to another vehicle. The visual warning assembly has a case with a front face joined to a base and an antenna. A channel display window, a channel selector button, a power button, a green lighted button, a yellow lighted button and a red lighted button, arranged on the front face. A mounting ball is magnetically joined to the base. A microcontroller is electrically coupled to the green lighted button, the yellow lighted button, and the red lighted button. The microcontroller is programmed with instructions to: receive a communication from a second visual warning assembly. Then, engage one member of a lighted button set consisting of the red button, the yellow button, and the green button creating an indicating light. Finally, receiving a signal from a user making the indicating light an activated button.

Abstract: A shroud panel (60) is attached to a wing skin overhang (28) by a series of pivoting butt straps (86) to permit relative strains to occur.

Abstract: A moveable control surface mounting rib assembly (110) comprises a rib (144) which is attached to one side of a spar member (112) and a stiffener (160) attached to another side of the spar member. The stiffener abuts the upper and lower flanges of the spar member in order to react the loads. The invention is applicable to the mounting of any movable control surface.

Abstract: A bridging seal comprising a stack of two or more layers of elastomer, the bridging seal having a first edge and a second edge opposite the first edge, adjacent layers being attached to each other at the first and second edges, wherein adjacent layers of the bridging seal have opposing surfaces and a substantial portion of the opposing surfaces is unbonded. The bridging seal may be used to seal a gap between two aerodynamic surfaces on an aircraft.

Abstract: An aircraft wing assembly, comprising a front spar, a rear spar, and upper and lower wing covers extending between the front and rear spars, wherein the upper and/or lower wing cover overhangs the rear spar and has a non-linear trailing edge profile forming an array of tabs and cut-outs. Also, a method of assembling the aircraft wing.

Abstract: A joint between an aircraft wing box cover and a leading/trailing edge structure, the cover and the structure having flush aerodynamic outer surfaces, wherein the structure has an integrally formed land that extends over an inner surface of the cover, and the land of the structure is fastened to the cover. Also a method of forming the joint.

Abstract: A bridging seal comprising a stack of two or more layers of elastomer, the bridging seal having a first edge and a second edge opposite the first edge, adjacent layers being attached to each other at the first and second edges, wherein adjacent layers of the bridging seal have opposing surfaces and a substantial portion of the opposing surfaces is unbonded. The bridging seal may be used to seal a gap between two aerodynamic surfaces on an aircraft.

Abstract: An aircraft wing assembly, comprising a front spar, a rear spar, and upper and lower wing covers extending between the front and rear spars, wherein the upper and/or lower wing cover overhangs the rear spar and has a non-linear trailing edge profile forming an array of tabs and cut-outs. Also, a method of assembling the aircraft wing.

Abstract: An aircraft structure, for example a wing (20), includes a structural skeleton having structural elements (for example, spars (60) and ribs (70)) enclosed within a skin (200). A fastener (110a,b) is fastened to the skeleton and wholly within the skin (200). The fastener (110a,b) fastens to the structure (20) a bracket (120) for carrying stores (80). The fastener (110a,b) includes a body (300) defining an internal bore (230). The body (300) includes an internal threaded region (330), within the internal bore (230), for fastening the bracket (120) to the aircraft structure (20).