Methods of using and repairing seal caps as well as constructions comprising seal caps, including in some embodiments seal caps which may be useful in sealing fasteners that protrude into fuel storage cells in aircraft. In some embodiments, methods include the use of optically translucent seal cap and application of a second quantity of sealant to fill voids observed within the interior of the seal cap after cure of a first quantity of sealant.

A joint for a motor vehicle body comprises a first structural member fabricated from aluminum attached to a second structural member fabricated from steel. The second structural member has an adjoining portion that is in substantially juxtaposed abutting relation with the first structural member when the second structural member is attached to the first structural member. The second structural member has a ramp portion terminating in a bare exposed edge on the second structural member and upon which the bare exposed edge is disposed. The bare exposed edge is displaced from the first structural member to form a gap between the first structural member and the bare exposed edge to prevent corrosion of the bare exposed edge without the use of adhesives and sealants.

An article is disclosed that includes a first substrate of a first metal or metal alloy. An aluminum alloy first layer on a surface of the first substrate includes is galvanically less noble than the first metal or metal alloy. The first layer can also include elements alloyed with or in solid solution with the aluminum alloy, or can include a two or more phase composition including a first phase of aluminum and a second phase of a solid lubricant.

A union screw (1) for pipes (2) provided with at least one flare (21) comprises a metal base body (10) which accommodates the pipe (20). The union screw (1) further comprises a screw head (12), a threaded portion (13), a contact portion (15) which is configured to abut the flare (21) of the pipe (20), and a functional layer (40) with which the base body (10) is coated at least in the region of the threaded portion (13) and the contact portion (15). The functional layer (40) is multi-layered and consists of at least one base coat (41) and a top coat (42) applied to the base coat (41) at least in some areas. The base coat (41) forms a structure for creating corrosion protection and a far-reaching invariance with regard to the material of the usual friction partners of the union screw (1) which, in addition to a binder, also contains zinc in the form of zinc-containing lamellae (43), which are oriented to lie substantially flat on the base body (10).

The invention relates to a metallic fastener (10; 40) for the interference fit assembly of at least two structural elements (20, 22) comprising a through hole, the fastener comprising an enlarged head (12; 42), a shaft (14; 44) having an external diameter before installation that is greater than an internal diameter of the hole, said shaft comprising a conductive surface (26; 56). Before installation, at least the conductive surface (26; 56) is coated with a lubricating layer (30), which comprises a mixture of at least one polyolefin and one polytetrafluoroethylene, for example, having sufficient adherence to prevent its abrasion by manual manipulation of the fastener and being weak enough to be at least partly stripped from the conductive surface during the interference fit assembly of the fastener.

The invention further relates to a method for obtaining such a fastener and to a method for installing such a fastener in a structure.

The invention is applicable to the assembly of aircraft structures.

The invention provides an arrangement of a first component and a second component, wherein at least the first or the second component is a fiber-reinforced plastic composite component. The first and second components are connected to each other so as to generate a clamping connection between the components via an expansion bolt which generates a clamping force creating the clamping connection and equalizes a creep behavior of the fiber-reinforced plastic composite component.

A hollow screw and related process of making is provided, wherein the hollow screw is formed from a generally circular corrosion resistant stainless steel disk cut from flat roll stock. The hollow screw includes a head and an elongated and hollow shaft having a wall thickness between about 0.2 to about 0.7 millimeters extending therefrom and defining a shank portion and a threaded portion having a plurality of threads thereon with a rotational drive mechanism configured to facilitate tightening via the threads. The process involves annealing to soften the stamped hollow screw, followed by thread rolling, and then age hardening the hollow screw. As such, the resultant hollow screw is relatively lightweight, about 50% the mass of a solid core screw made from the same material, with a sufficient thread strength to meet most aerospace applications and contributes to important aircraft fuel economy.

An upper plate portion of a suspension member and a bottom plate portion of a bracket that is placed on an upper side thereof, and the like, as objects to be fastened, are sandwiched between a weld nut and an end surface on a vehicle upper side of a collar. A protruding portion that protrudes toward a bolt through-hole side of the bottom plate portion of the bracket is formed on an end portion on the vehicle upper side of the collar. The protruding portion is formed along an entire periphery around an axis of the collar. Also, a drainage groove that leads from the end surface on the vehicle upper side to an outer peripheral surface of the collar is formed in the collar.

A method to prevent corrosion of a susceptible article of a two-article system, in which first and second articles of the two-article system have surfaces facing one another and in which the two articles have different anodic indices includes applying a coating material to the surface of the first article and curing the coating material on the surface of the first article. The method further includes contacting and securing the surface of the first article with the surface of the second article. The two articles exhibit substantially no corrosion following exposure to a corrosive environment under standard GMW17026 for a 15 year simulated test.

A fiber-reinforced resin member is provided in which a non-conductive sleeve and first and second non-conductive sheets are disposed between a metal fastening member and CFRP laminate, electrical continuity between the metal fastening member and the CFRP laminate is cut off, and corrosion of the metal fastening member due to galvanic corrosion is prevented. A first annular space is formed between a first flange portion of a first member and the first non-conductive sheet, a second annular space is formed between a second flange portion of a second member and the second non-conductive sheet. Therefore, even if frayed carbon fiber sticks out from a gap between the non-conductive sleeve and the first and second non-conductive sheets, due to the first and second annular spaces being formed therein, it is possible to prevent the sticking-out carbon fiber from contacting the first and second members and providing electrical continuity.