Method for assembling modules into a load aerostructure of an aircraft

1 . A method for assembling modules into a load aerostructure of an aircraft, the method comprising:

a) providing at least one module assembly comprising at least a first submodule, a second submodule and at least one connection between the first submodule and the second submodule;

b) providing connecting elements for the first submodule and the second submodule, wherein each of connecting elements includes one or more parts;

c) drilling a first set of first holes with a final hole diameter in each of the connecting elements according to a predefined hole pattern for each of the connecting elements, wherein at least one of the first holes in a respective one of the connecting elements is spaced apart from another hole of the first holes in the same one of the connecting elements by a maximum distance B;

d) after the step c), attaching each of the connecting elements to a respective one of the first submodule and the second submodule of the at least one module assembly;

e) for each of the connecting elements, drilling a second set of second holes in a region of at least one structural part of the load aerostructure, wherein each of the second holes has the final hole diameter and is arranged according to the predefined respective hole pattern such that a respective second hole of the second holes corresponds to a respective first hole of the first holes; and

f) after the step e), assembling the at least one module assembly and each of the connecting elements by matching each of the second holes in the at least one structural part with a corresponding first hole of the first holes in each of the connecting elements and securing each of the matched second and first holes with fasteners,

wherein after the step f), each of the connecting elements is interposed between the region of the structural part of the load aerostructure and a respective one of the first submodule or the second submodule.

2 . The method according to the claim 1 , wherein following the step e) and before the step f), performing the following step:

providing an aperture in the structural part of the load aerostructure for each of the connecting elements, wherein each of the apertures is smaller than the each of the connecting elements to be mounted over the aperture,

wherein, for each of the connecting elements, the second set of second holes is drilled in a zone of the structural part proximal to each aperture.

3 . The method according to claim 1 , wherein at least one of the connecting elements includes a first part and a second part perpendicular to the first part:

wherein the step c) is performed for each of the first part and the second part of the at least one of the connecting elements including the first part and the second part;

wherein the step e), for the at least one of the connecting elements including the first part and the second part, the region is a first region into which the second set of second holes is drilled to correspond to the first holes in the first part of the at least one of the connecting elements including the first part and the second part; and

wherein the step e) includes drilling a third set of second holes in a second region of the structural part and the third set of the second holes corresponds to respective first holes of the first holes in the second part of the at least one of the connecting elements including the first part and the second part and the second region is proximal to the first region; and

in the step f), the assembly of the at least one module assembly and the first part and the second part of the at least one of the connecting elements including the first part and the second part is performed by matching each of the second holes in first region to respective first holes of the first holes in the first part and matching each of the second holes in the second region to respective first holes of the first holes in the second part so that after the assembly the first part of the at least one of the connecting elements including the first part and the second part is between the first region of the structural part and one of the first submodule or the second submodule and the second part of the at least one of the connecting elements including the first part and the second part is between the second region of the structural part and the one of the first submodule or the second submodule.

4 . The method according to claim 1 , wherein the step b) comprises providing two or more of the connecting elements for at least one of the first submodule or the second submodule, and

wherein in the step e), each of the connecting elements is attached to the at least one of the first submodule or the second submodule such that each of the connecting elements are spaced apart from each other on the at least one of the first submodule or the second submodule.

5 . The method according to claim 1 , wherein each of the first set of the first holes is drilled in a respective peripheral region of each of the connecting elements.

6 . The method according to claim 1 , wherein the maximum distance B is less than 300 cm.

7 . The method according to claim 1 , wherein in the step f) the securing is performed by bolting and/or riveting.

8 . The method according to claim 1 , wherein at least one of the first submodule, the second submodule, or the connecting elements are resilient.

9 . The method according to claim 1 , wherein the module assembly comprises a system that comprises at least one of: a mechanical system, an electrical system, a pneumatic system or a hydraulic system and between the first submodule and the second submodule, and

wherein the system includes the at least one connection between said first submodule and the second submodule.

10 . The method according to claim 1 , wherein the at least one module assembly comprises at least one of: a pipe, an electric harness, a pump or a reservoir.

11 . The method according to claim 1 , wherein the connecting elements are formed of a metallic or composite material.

12 . The method according to claim 2 , wherein for each of the connecting elements, the aperture in the structural part has a shape corresponding to a contour of a respective connecting element of the connecting elements to be mounted over the aperture.

13 . The method according to claim 1 , wherein at least one of the step c), the step e), or the step f) is performed by numerical control.

14 . The method according to claim 1 , wherein the structural part of the load aerostructure is at least one of: a floor, a frame or a beam.

15 . The method according to claim 1 , wherein:

the load aerostructure is a nacelle of an aircraft,

the nacelle comprises a primary structure including a ceiling, a floor and transverse frames connecting the ceiling and the floor,

before the step f), the primary structure of the nacelle is provided without at least one side wall so that at least one lateral face of the primary structure of the nacelle is open to allow performance of the step f), and

the step f), includes the at least one module assembly and each of the corresponding connecting elements being installed in the load aerostructure using the at least one open lateral face of the primary structure of the nacelle; and

after the step f), installing the at least one side wall of the primary structure of the nacelle to close the at least one lateral face of the primary structure of the nacelle.