A cap for a temporary fastener comprises a hollow, cup-shaped body and an inwardly tapered neck. The hollow body fits over a workpiece-engaging portion of the temporary fastener, and the neck extends from the hollow body. The tapered neck terminates in a hollow tip that is sized and configured to fit over aligned holes in the joined workpieces and to contact a minimal surface area of the outermost workpiece to reduce surface damage to the workpieces such that any damage will be removed when the holes are countersunk in the normal course of assembly.

A method for assembling a fuselage section which comprises producing a lower part of the section from at least two panels and an upper part of the section from at least two panels, then assembling the lower and upper parts so as to obtain the fuselage section. A lower or upper mounting support, a gear and a production unit are used in the method.

A multiple anvil fixture possesses multiple anvils engaged to a base in a fixed relation to each other with the anvils are oriented in a common direction. Each of the anvils includes a first structure and a second structure. The first structure and the second structure are slidably engaged. Each of the anvils has an extended position and a recoiled position and a biasing-element to bias the first structure and the second structure in the extended position. The multiple anvil structure can be used to rivet brackets onto containers. The anvil protrudes through the container in the extended position to help align holes in the feet of the brackets with openings in the container. The anvil then recoils beneath the container to serve for the fixation of rivets.

An aircraft panel production method has: a step in which a holding jig holds a body panel, which has a plurality of plate-like members having a curved cross-sectional shape, such that the cross section of the body panel has an upwardly bulging curved shape; a step in which the plate-like members of the body panel held by the holding jig are overlapped with each other and the overlapping portions are joined by a rivet; a step in which the holding jig, which is holding the body panel of which the plate-like members have been joined to each other, is moved; and a step in which a frame that follows the curved shape of the body panel is joined, by a rivet, to the plate-like members of the body panel which is held by the holding jig which has been moved.

An aircraft panel production method has: a step in which a holding jig holds a body panel, which has a plurality of plate-like members having a curved cross-sectional shape, such that the cross section of the body panel has an upwardly bulging curved shape; a step in which the plate-like members of the body panel held by the holding jig are overlapped with each other and the overlapping portions are joined by a rivet; a step in which the holding jig, which is holding the body panel of which the plate-like members have been joined to each other, is moved; and a step in which a frame that follows the curved shape of the body panel is joined, by a rivet, to the plate-like members of the body panel which is held by the holding jig which has been moved.

A clamping method includes a step (S3) for applying, by a first support portion disposed on one surface side of a plurality of superposed members and a second support portion disposed on the other surface side of the plurality of members, a predetermined first pressure to the plurality of members, and sandwiching the plurality of members; a step (S4) for forming a through hole with respect to the plurality of members by a cutting tool with the first pressure; a step (S5) for applying a predetermined second pressure to the plurality of members after the through hole is formed, and sandwiching the plurality of members by the first and second support portions, the second pressure being lower than the first pressure; and a step (S6) for fixing a fastening part inserted into the through hole to the plurality of members by a riveting device with the second pressure applied.

A clamping method includes a step (S3) for applying, by a first support portion disposed on one surface side of a plurality of superposed members and a second support portion disposed on the other surface side of the plurality of members, a predetermined first pressure to the plurality of members, and sandwiching the plurality of members; a step (S4) for forming a through hole with respect to the plurality of members by a cutting tool with the first pressure; a step (S5) for applying a predetermined second pressure to the plurality of members after the through hole is formed, and sandwiching the plurality of members by the first and second support portions, the second pressure being lower than the first pressure; and a step (S6) for fixing a fastening part inserted into the through hole to the plurality of members by a riveting device with the second pressure applied.

A component manufacturing method includes a step in which a robot for attachment gripping a long frame presses the frame against a tabular skin and a step in which, in a state in which the frame is pressed against the skin, a robot for riveting gripping a first rivet inserts the first rivet into a first through-hole formed in the skin and a second through-hole formed in the frame. In the step, the robot for riveting changes a position in the gripped first rivet in a direction perpendicular to an axial direction of the first rivet according to a force received by the first rivet from the skin or the frame.

A cap for a temporary fastener comprises a hollow, cup-shaped body and an inwardly tapered neck. The hollow body fits over a workpiece-engaging portion of the temporary fastener, and the neck extends from the hollow body. The tapered neck terminates in a hollow tip that is sized and configured to fit over aligned holes in the joined workpieces and to contact a minimal surface area of the outermost workpiece to reduce surface damage to the workpieces such that any damage will be removed when the holes are countersunk in the normal course of assembly.

A cap for a temporary fastener comprises a hollow, cup-shaped body and an inwardly tapered neck. The hollow body fits over a workpiece-engaging portion of the temporary fastener, and the neck extends from the hollow body. The tapered neck terminates in a hollow tip that is sized and configured to fit over aligned holes in the joined workpieces and to contact a minimal surface area of the outermost workpiece to reduce surface damage to the workpieces such that any damage will be removed when the holes are countersunk in the normal course of assembly.