Method for mounting an aircraft pylon

Patent metadata

Field	Value
Publication number	US-11208215-B2
Application number	US-201916560023-A
Country	US
Kind code	B2
Filing date	Sep 4, 2019
Priority date	Sep 19, 2018
Publication date	Dec 28, 2021
Grant date	Dec 28, 2021

Abstract

A method for mounting an aircraft pylon connected to a wing includes: a step of pre-positioning first and second contact surfaces respectively provided on the wing and the pylon, a step of installing and tightening temporary connection elements, so as to keep the first and second contact surfaces clamped against one another, a step of installing and expanding at least one radially expandable element in at least one pair of first and second receptacles respectively provided on the wing and the pylon, a step of installing and tightening final connection elements connecting the pylon and the wing in the mounted state, a step of removing the radially expandable element(s) and the temporary connection elements, and of installing the remaining final connection elements and shear pin(s).

First claim

The invention claimed is:

1. A method for mounting an aircraft pylon connected to a wing by at least one front wing attachment, comprising: at least one first plate secured to the wing having a first contact surface; at least one second plate secured to the pylon having a second contact surface; a plurality of final connection elements which, when the pylon is mounted, connect the first and second plates by holding the first and second contact surfaces against one another at a plane of contact that is inclined for each final connection element, the first and second plates respectively comprising a pair of first and second through-holes; at least one shear pin which, when the pylon is mounted, straddles a pair of first and second receptacles which are respectively provided in the first and second plates and which each have a cross section identical to that of the shear pin, wherein the mounting method comprises: pre-positioning the first and second contact surfaces, such that the first and second contact surfaces are approximately parallel and close to or in contact with one another, and of approximately pre-aligning the first and second through-holes of each pair of first and second through-holes and pre-aligning the first and second receptacles of each pair of first and second receptacles; installing and tightening temporary connection elements in certain pairs of first and second through-holes, so as to keep the first and second contact surfaces clamped against one another; installing and expanding at least one radially expandable element in at least one pair of first and second receptacles; installing and tightening final connection elements in at least some of the pairs of first and second through-holes that are not occupied by the temporary connection elements; removing the at least one radially expandable element and installing the at least one shear pin, and removing the temporary connection elements and installing the final connection elements.

2. The method for mounting the aircraft pylon according to claim 1 , wherein each temporary connection element comprises at least one compression element positioned below the pylon, the step of tightening the temporary connection elements serving to obtain a compression force of each compression element, the compression force of each compression element of the temporary connection elements and the radially expandable element being configured so as to allow the first and second contact surfaces to slide with respect to one another during the step of expanding the radially expandable element.

3. The method for mounting the aircraft pylon according to claim 2 , wherein the compression force of each compression element of the temporary connection elements and the radially expandable element are configured so as to keep the first and second plates immobile with respect to one another when the radially expandable element is not expanded.

4. The method for mounting the aircraft pylon according to claim 1 , wherein the step of pre-positioning the first and second contact surfaces is carried out using a lifting system configured to tilt then lift the pylon.

5. The method for mounting the aircraft pylon according to claim 4 , wherein the lifting system comprises at least two strands and wherein the lifting system is configured to occupy a connected and loaded state in which the strands are taut, with the lifting system supporting the pylon, a connected and unloaded state in which the strands are slack, with the lifting system not supporting the pylon, and a detached state in which the pylon is detached from the lifting system.

6. The method for mounting the aircraft pylon according to claim 5 , wherein the lifting system passes from the connected and loaded state to the connected and unloaded state after the step of tightening the temporary connection elements.

7. The method for mounting the aircraft pylon according to claim 1 , wherein the at least one radially expandable element is an expandable ring configured to occupy a retracted state in which the expandable ring has a cross section allowing it to be inserted into the pair of first and second receptacles and an expanded state in which the expandable ring has a cross section equal to or greater than that of the first and second receptacles.

8. The method for mounting the aircraft pylon according to claim 1 , wherein each of the at least one radially expandable element is removed and replaced with one of the at least one shear pin prior to removal of the temporary connection elements.

9. The method for mounting the aircraft pylon according to claim 8 , wherein one of the at least one shear pin is positioned in each pair of first and second receptacles not occupied by a radially expandable element prior to removal of the at least one radially expandable element.

10. The method for mounting the aircraft pylon according to claim 1 , wherein the wing attachment comprises, when the pylon is mounted, at least one front shear pin of the at least one shear pin is arranged in a first transverse plane and at least one rear shear pin of the at least one shear pin is arranged in a second transverse plane which is offset to the rear relative to the first transverse plane, wherein a first of the at least one radially expandable element is installed in a pair of first and second receptacles arranged in the first transverse plane, and wherein a second of the at least one radially expandable element is installed in a pair of first and second receptacles arranged in the second transverse plane.

Assignees

• Airbus Operations Sas

Inventors

• Martinez Pascal
• Pautis Olivier

Classifications

• B64D27/404

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• B64D27/402

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

• B64D27/18 Primary

  within, or attached to, wings · CPC title

• B64D27/12

  within, or attached to, wings · CPC title

• B64D27/06

  within, or attached to, wings · CPC title