Abstract: To provide a jig for forming a sealant layer which enables to quickly and accurately form a sealant layer having a required film thickness. The jig includes: a sealant cup 13 that overlays a sealant 28 around a collar 26; a cup holder 12 that determines a position of the sealant cup 13 with respect to a fastener member 24; and a dummy cup 11 that determines a position of the cup holder 12 with respect to the fastener member 24. The cup holder 12 is determined in position with respect to the fastener member 24 by being guided along the dummy cup 11 determined in position with respect to the fastener member 24. The sealant cup 13 is guided along a guide of the cup holder 12 so as to overlay the sealant 28 around the collar 26 after removing the dummy cup 11 from the cup holder 12 determined in position with respect to the fastener member 24.

Abstract: To provide a lightning protection fastener or the like, that can reliably seal an arc between the cap and a member such as a wing panel. An end part 30A of a cap 30 on an opening side, the end part 30 A facing a member 22 (or member 21), includes a plane 30d orthogonal to an axis line of the cap 30A and a tapered face 30c formed on an outer circumferential side of the plane 30d. A sealant 34 that spills out of the cap 30A upon mounting the cap 30A is present between the tapered face 30c and a surface 22f of the member 22 (sealant 34S).

Abstract: A method for determining an object of a test for verifying the lightning protection adequacy of a fastening part includes: a structural pattern population generating step of generating a population of structural patterns identified by a combination of a plurality of properties of the fastening part; a section extracting step of extracting those sections which are disposed in a wet area of the aircraft where fuel or fuel vapor is present, from the sections of a fastening member, for each of the structural patterns of the population; a group setting step of setting a group of structural patterns of the same predetermined properties for each of the sections; and a representative pattern selecting step of selecting a representative pattern representative of the group from the structural patterns belonging to the same group. The structural pattern narrowed down through the steps is determined as the test object.

Abstract: Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved.

Abstract: To provide a lightning protection fastener or the like, that can reliably seal an arc between the cap and a member such as a wing panel. An end part 30A of a cap 30 on an opening side, the end part 30 A facing a member 22 (or member 21), includes a plane 30d orthogonal to an axis line of the cap 30A and a tapered face 30c formed on an outer circumferential side of the plane 30d. A sealant 34 that spills out of the cap 30A upon mounting the cap 30A is present between the tapered face 30c and a surface 22f of the member 22 (sealant 34S).

Abstract: To provide a jig for forming a sealant layer which enables to quickly and accurately form a sealant layer having a required film thickness. The jig includes: a sealant cup 13 that overlays a sealant 28 around a collar 26; a cup holder 12 that determines a position of the sealant cup 13 with respect to a fastener member 24; and a dummy cup 11 that determines a position of the cup holder 12 with respect to the fastener member 24. The cup holder 12 is determined in position with respect to the fastener member 24 by being guided along the dummy cup 11 determined in position with respect to the fastener member 24. The sealant cup 13 is guided along a guide of the cup holder 12 so as to overlay the sealant 28 around the collar 26 after removing the dummy cup 11 from the cup holder 12 determined in position with respect to the fastener member 24.

Abstract: A sealant 34 filled into a cap 30A is caused to overflow through both an opening in a first end portion 30a of the cap 30A and a through-hole 40 of the cap 30A when the cap 30A is pressed against a fastener member 25. With regard to the cap 30A, a ratio between inside diameter D1 of the opening on the side of the first end portion 30a and hole diameter D2 of the through-hole 40 in the second end portion 30b is set as follows: 0.10?D2/D1?0.27.

Abstract: In an insulating cover 50A according to the present invention, a dimension of each of an outer-circumferential-side cylindrical part 50c and an inner-circumferential-side cylindrical part 50b fitting in step parts 40 and 41 in an axial direction of a fastener body 25 is set large with respect to a tip covering part 50a covering a tip surface 26a of a fastening member 26. As a result, on an outer circumferential side and an inner circumferential side of the fastening member 26, a distance from a member 22 is sufficiently ensured by the cylindrical part 50b and 50c. The tip covering part 50a is thinner than the cylindrical part 50B and 50c. Therefore, when the fastener body 25 and the fastening member 26 are fastened together, the amount of deformation of the tip covering part 50a in a thickness direction can be made small.

Abstract: Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved.

Abstract: Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved.

Abstract: A long-life lightning protection fastener or the like to prevent explosion for aircrafts at low cost is provided, the fastener having a light weight, ensuring sufficient lightning protection, and having extremely less failures and high reliability. A ring-shaped ring member 40A made of resin is mounted on a collar 26. This ring member 40A is interposed between a member 22 and the collar 26 and is in intimate contact with both of the member 22 and the collar 26, thereby sealing an interface with the member 22 for sealing and preventing the occurrence of an arc at an outer perimeter edge of the collar 26.

Abstract: In an insulating cover 50A according to the present invention, a dimension of each of an outer-circumferential-side cylindrical part 50c and an inner-circumferential-side cylindrical part 50b fitting in step parts 40 and 41 in an axial direction of a fastener body 25 is set large with respect to a tip covering part 50a covering a tip surface 26a of a fastening member 26. As a result, on an outer circumferential side and an inner circumferential side of the fastening member 26, a distance from a member 22 is sufficiently ensured by the cylindrical part 50b and 50c. The tip covering part 50a is thinner than the cylindrical part 50B and 50c. Therefore, when the fastener body 25 and the fastening member 26 are fastened together, the amount of deformation of the tip covering part 50a in a thickness direction can be made small.

Abstract: A long-life lightning protection fastener or the like to prevent explosion for aircrafts at low cost is provided, the fastener having a light weight, ensuring sufficient lightning protection, and having extremely less failures and high reliability. A ring-shaped ring member 40A made of resin is mounted on a collar 26. This ring member 40A is interposed between a member 22 and the collar 26 and is in intimate contact with both of the member 22 and the collar 26, thereby sealing an interface with the member 22 for sealing and preventing the occurrence of an arc at an outer perimeter edge of the collar 26.

Abstract: Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved.

Abstract: An electrode and a vacuum processing apparatus are provided that are capable of improving the film deposition rate and the uniformity of the distribution of the deposited film. The electrode includes a plurality of electrodes (17A, 17B) extending from positions arranged at a predetermined interval along a surface of a substrate to be processed (3). Buffer chambers (25) each extend along and between two of the plurality of electrodes (17A, 17B). A plurality of first gas injection holes (27) are arranged in the direction in which the electrodes (17A, 17B) extend and which supply a reactant gas into the buffer chamber (25). A second gas injection hole (23) has a slit form extending in the direction in which the electrodes (17A, 17B) extend, and which supplies the reactant gas from the buffer chamber (25) toward the substrate to be processed (3).