Aircraft engine attachment comprising at least one fork-type system for immobilizing a shear pin in translation, method for mounting said engine attachment and aircraft comprising said engine attachment

Patent metadata

Field	Value
Publication number	US-11434015-B2
Application number	US-202016733691-A
Country	US
Kind code	B2
Filing date	Jan 3, 2020
Priority date	Jan 9, 2019
Publication date	Sep 6, 2022
Grant date	Sep 6, 2022

Abstract

An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises, first, a groove positioned in an extension of the shear pin and, second, a fork connected to the primary structure via at least one removable link and interacting during operation with the groove in such a manner as to immobilize the shear pin in translation.

First claim

The invention claimed is:

1. An aircraft engine attachment comprising:
an attachment body connected to a primary structure of an aircraft pylon via an attachment body link comprising link elements and at least one shear pin that comprises a cylindrical body and a flange having a diameter greater than that of the cylindrical body,
the attachment body link comprising,
for each shear pin, a first hole in the primary structure and a second hole in the attachment body that are configured such as to accommodate the shear pin, the first hole comprising a shoulder against which the flange bears during operation in such a manner that the cylindrical body is positioned to straddle the first and second holes,
a first immobilization system that comprises, in addition to the shoulder, a removable stop, secured to the primary structure, configured such as to immobilize the flange between the shoulder and the removable stop, and
a second immobilization system that comprises, first, a groove positioned in an extension of the shear pin and, second, a fork connected to the primary structure via at least one removable link and interacting during operation with the groove such as to immobilize the shear pin in translation.

2. The aircraft engine attachment according to claim 1 ,
wherein the first hole comprises a principal portion that extends from a first contact face oriented towards the attachment body as far as the shoulder and an enlarged portion that extends from the shoulder as far as an access face opposite the first contact face, the enlarged portion having a diameter greater than the diameter of the flange, and
wherein the extension of the shear pin has a length such that part of the extension comprising the groove is located outside of the first hole.

3. The aircraft engine attachment according to claim 1 ,
wherein the extension has a cylindrical form coaxial relative to the cylindrical body, and
wherein the groove extends over an entire circumference of the extension and has two flanks positioned in two planes perpendicular to an axis of the cylindrical body.

4. The aircraft engine attachment according to claim 3 , wherein the attachment body link comprises at least one support plate, connected to the primary structure, to which are connected the stop plate and the one or more anti-rotation plates, said support plate comprising, for each link element, a passage orifice having a section approximately identical to a circular lower section of the head of the link element.

5. The aircraft engine attachment according to claim 4 , wherein the attachment body link comprises at least one anti-rotation system for at least one of the link elements, each anti-rotation system comprising an anti-rotation plate that has a through-orifice with a section that complements an upper section of a head of the link element such that the stop plate and the head are immobilized in rotation relative to one another, and also a removable link for connecting said anti-rotation plate to the primary structure.

6. The aircraft engine attachment according to claim 5 , wherein the fork comprises a stop plate that has two branches that are configured such as to be accommodated in the groove of the extension on either side of said extension, the branches being separated by a distance substantially equal to a diameter of a bottom of the groove.

7. The aircraft engine attachment according to claim 6 , wherein the branches are separated by a U-cutout comprising a base that describes a half-circle with a diameter substantially equal to the diameter of the bottom of the groove.

8. The aircraft engine attachment according to claim 7 , wherein the stop plate has a rectangular form and comprises, at a first minor side, the U-cutout and, close to the second minor side, at least one through-orifice provided for the removable link.

9. The aircraft engine attachment according to claim 8 , wherein the stop plate comprises curved edges at two major sides of the rectangular form.

10. An aircraft comprising an engine attachment according to claim 1 .

11. A method for mounting an engine attachment comprising an attachment body connected to a primary structure of an aircraft pylon via an attachment body link comprising link elements and at least one shear pin that comprises a cylindrical body and a flange having a diameter greater than that of the cylindrical body,
the attachment body link comprising,
for each shear pin, a first hole in the primary structure and a second hole in the attachment body that are configured such as to accommodate the shear pin, the first hole comprising a shoulder against which the flange bears during operation in such a manner that the cylindrical body is positioned to straddle the first and second holes,
a first immobilization system that comprises, in addition to the shoulder, a removable stop, secured to the primary structure, configured such as to immobilize the flange between the shoulder and the removable stop, and
a second immobilization system that comprises, first, a groove positioned in an extension of the shear pin and, second, a fork connected to the primary structure via at least one removable link and interacting during operation with the groove such as to immobilize the shear pin in translation, wherein the method comprises the steps:

connecting the attachment body to an aircraft engine,
vertically moving the aircraft engine such as to position first and second contact faces of the primary structure of the aircraft pylon and of the attachment body opposite one another,
placing the link elements,
inserting each shear pin into the first and second holes until the flange is in contact with the shoulder,
placing the removable stop,
placing the fork and causing the fork to interact with the groove of the extension of the shear pin, and
connecting the fork to the primary structure by virtue of at least one removable link.

Assignees

• Airbus Operations Sas

Inventors

• Puech Jacky
• Deforet Thomas
• Cayssials Julien

Classifications

• B64D27/402 Primary

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B64D2027/268

  Operations & Transport · mapped topic

• B64D27/26 Primary

  Operations & Transport · mapped topic

• B64D27/40 Primary

  Arrangements for mounting power plants in aircraft · CPC title