Fastener Assembly

• US 20080292427A1
• Filed: 12/14/2006
• Published: 11/27/2008
• Est. Priority Date: 12/16/2005
• Status: Abandoned Application

• Current Assignee: Airbus Operations Limited (Airbus SE)
• Original Assignee: Airbus UK Limited (Airbus SE)
• Inventors: Moore, John, Rowe, James Henry
• Application Number:
  US12/095,363
• Publication Number:
  US 20080292427A1
• Time in Patent Office: Days
• US Class Current: 411/339
• CPC Class Codes: F16B 35/041 Specially-shaped shafts shape of thread F16B33/02
• CPC Class Codes: F16B 37/00 Nuts or like thread-engaging members specially shaped for rotations by a tool F16B23/00
• CPC Class Codes: F16B 43/00 Washers or equivalent devices; Other devices for supporting bolt-heads or nuts circlips F16B21/18; for indicating tensile load F16B31/02; forming a whole with the bolt or nut F16B33/00; locking bolts or nuts by means of a fixed plate or ring, or washer-like resilient plates F16B39/10, F16B39/24
• CPC Class Codes: F16B 5/025 specially designed to compensate for misalignement or to eliminate unwanted play
• CPC Class Codes: Y10T 29/49948 Multipart cooperating fastener [e.g., bolt and nut]

Abstract

A fastener assembly includes a bolt having first and second ends and comprising a bolt head at the first end, a first shank portion having a smooth circumferential surface of a first diameter and a second shank portion coaxial with the first shank portion and of a second diameter smaller than the first diameter. At least a part of the second shank portion is externally screw threaded and the first shank portion is positioned between the bolt head and the second shank portion. A nut has first and second ends and includes a first bore extending from the first end of the nut and of a diameter greater than the first diameter for fitting over part of the first shank portion of the bolt, and, in the region of the second end, a screw threaded bore for screw threaded engagement with the screw threaded second shank portion, the screw threaded bore being coaxial with and leading into the first bore.

Claims

1. A slave bolt assembly for use in the manufacture of aircraft components including:

a bolt having first and second ends and comprising

a bolt head at the first end,

a first shank portion, adjacent to the bolt head, having a smooth circumferential surface of a first diameter arranged to engage the walls of holes in the components and thereby align the components, and

a second shank portion, positioned between the first shank portion and the second end and coaxial with the first shank portion, of a second diameter smaller than the first diameter, at least a part of the second shank portion being externally screw threaded; and

a nut having first and second ends and comprising

a first bore extending from the first end of the nut and of a diameter greater than the first diameter for fitting over part of the first shank portion of the bolt, and

a screw threaded bore, in the region of the second end, for screw threaded engagement with the screw threaded second shank portion, the screw threaded bore being coaxial with and leading into the first bore

wherein engagement of the second shank portion and the screw threaded bore is arranged to allow components to be clamped together by the first end of the nut and the bolt head.

2. A slave bolt assembly according to claim 1, in which the bolt head is at one end of the first shank portion.

3. A slave bolt assembly according to claim 1, in which the second shank portion extends from the end of the first shank portion to the second end of the bolt.

4. A slave bolt assembly according to claim 1, in which the screw threaded bore extends through the second end of the nut.

5. A slave bolt assembly according to claim 1, in which the first bore in the nut is of greater axial length than the screw threaded bore.

6. A slave bolt assembly according to claim 1, in which the assembly further includes a washer at the first end of the nut around the first bore.

7. A slave bolt assembly according to claim 6, in which the washer is formed separately from the nut and is fastened to the nut.

8. A slave bolt assembly according to claim 7, in which the washer is formed with a front face part extending over the end face of the first end of the nut, an outer circumferential part extending rearwardly of the front face part and a retaining part that extends inwardly from the outer circumferential part and engages the nut to retain the washer on the nut.

9. A slave bolt assembly according to claim 6, in which the first end of the nut is formed with a flange and the washer is fitted over the flange.

10. A slave bolt assembly according to claim 1, in which the bolt head is of generally frusto-conical shape to define a countersunk bolt head.

11. A slave bolt assembly according to claim 10, further including a washer arranged to change the rear face of the bolt head from an inclined face to a face perpendicular to the axis of the bolt.

12. A slave bolt assembly according to claim 11, in which the washer is a snap fit on the bolt and includes an internally projecting portion that fits in a groove at the junction of the first shank portion and the bolt head.

13. A method of assembling aircraft components, the method comprising the following steps:

holding the components in desired relationship with holes in the articles aligned,

providing a bolt having first and second ends and comprising a bolt head at the first end, a first shank portion having a smooth circumferential surface of a first diameter and a second shank portion coaxial with the first shank portion and of a second diameter smaller than the first diameter, at least a part of the second shank portion being externally screw threaded, the first shank portion being positioned between the bolt head and the second shank portion,

inserting the second end of the bolt into and through the aligned holes, the first shank portion of the bolt engaging the walls of the holes to align the components,

providing a nut having first and second ends and including a first bore extending from the first end of the nut and of a diameter greater than the first diameter of the first shank portion, and, in the region of the second end, a screw threaded bore coaxial with and leading into the first bore, and

screwing the nut onto the bolt with the first bore of the nut fitting over part of the first shank portion of the bolt and the screw threaded bore of the nut in screw threaded engagement with the screw threaded shank portion such that the components are clamped together by the first end of the nut and the bolt head.

14. A method according to claim 13, including the further step of forming the holes in the components in predetermined locations.

15. A method according to claim 13, including the further subsequent steps of:

drilling further holes in the components,

unscrewing the nut from the bolt,

removing the bolt from the aligned holes, and

separating the articles.

16. The method of claim 15, including the further subsequent steps of:

deburring the further holes, and

refastening the components with the further holes in alignment.

17. A method according to claim 13, in which at least one of the components to be fastened together is of composite material.