Wing lift system capability expansion

Patent metadata

Field	Value
Publication number	US-10065749-B2
Application number	US-201614990789-A
Country	US
Kind code	B2
Filing date	Jan 7, 2016
Priority date	Jan 7, 2016
Publication date	Sep 4, 2018
Grant date	Sep 4, 2018

Abstract

A method for lifting a wing of an aircraft. A plurality of lifting assemblies is attached to a mounting ring supporting the wing. A first plurality of base assemblies is attached to a plurality of fittings connected to the fuselage of the aircraft. The plurality of lifting assemblies is moved away from the first plurality of base assemblies using a plurality of biasing systems correspondingly attached to the plurality of lifting assemblies, the moving causing the mounting ring to move away from the fuselage. The first plurality of base assemblies is removed. A second plurality of base assemblies is attached to the plurality of fittings. Thereafter, moving the plurality of lifting assemblies away from the second plurality of base assemblies using the plurality of biasing systems is repeated, the repeating moving causing the mounting ring to move away from the fuselage to the first height.

First claim

What is claimed is:

1. A method for lifting a wing connected to a mounting ring disposed on a fuselage of an aircraft to a first height relative to a fuselage of the aircraft, the method comprising:
attaching a lifting assembly to the mounting ring;
attaching a first base assembly to a fitting connected to the fuselage;
moving the mounting ring away from the fuselage to a second height via moving, using a biasing system attached to the lifting assembly, the lifting assembly away from the first base assembly;
removing the first base assembly from the fitting;
attaching a second base assembly to the fitting; and
thereafter, moving, the mounting ring further away from the fuselage to the first height, via moving, using the biasing system, the lifting assembly away from the second base assembly.

2. The method of claim 1 , further comprising the second base assembly differing from the first base assembly.

3. The method of claim 2 , further comprising the first base assembly comprising a first length and the second base assembly comprising a second length greater than the first length.

4. The method of claim 3 , further comprising the mounting ring comprising a flange limiting lifting of the mounting ring by lifting methods not using the first base assembly and the second base assembly.

5. The method of claim 3 , further comprising a first difference, between the second length and the first length, at least equal to a second difference, between the first height and the second height achieved after moving the lifting assembly but before removing the first base assembly.

6. The method of claim 5 , further comprising:
the biasing system comprising a piston; and
pressing the piston against an anvil of the first base assembly.

7. The method of claim 6 , further comprising limiting extending, out of the biasing system, the piston by a distance greater than the second height.

8. The method of claim 1 further comprising: before removing the first base assembly, inserting a retaining object between the fuselage and bottom of the mounting ring.

9. The method of claim 8 further comprising: after attaching the second base assembly, removing the retaining object.

10. The method of claim 9 , further comprising a plurality of retaining objects comprising blocks cumulatively comprising a material strength sufficient to support a weight of the mounting ring.

11. The method of claim 1 , further comprising the fitting comprising a first plurality of channels receiving bolts connecting the fitting to the first base assembly and later to the second base assembly.

12. The method of claim 11 , further comprising the lifting assembly comprise a second plurality of channels that receive second bolts connecting the mounting ring to the lifting assembly.

13. The method of claim 12 , further comprising the first plurality of channels being unaligned with the second plurality of channels.

14. The method of claim 1 further comprising:
removing the second base assembly;
attaching a third base assembly to the fitting; and
thereafter, moving the mounting ring further away from the fuselage via moving, using the biasing system, the lifting assembly away from a third base assembly.

15. The method of claim 14 further comprising: before removing the second base assembly, inserting a second retaining object between the fuselage and of the mounting ring.

16. The method of claim 15 further comprising: after attaching the third base assembly, removing the second retaining object.

17. The method of claim 1 further comprising: attaching the fitting to the fuselage.

18. The method of claim 1 , further comprising:
the lifting assembly comprising a lifting bracket; and
reacting a corresponding bending moment in the lifting bracket against the second base assembly while moving the lifting assembly.

19. A method for lifting a wing on a mounting ring disposed on a fuselage of an aircraft to a first height relative to the fuselage,
the method comprising:
attaching a lifting assembly to the mounting ring;
attaching a first base assembly to a fitting connected to the fuselage;
moving, to a second height away from the fuselage, the mounting ring via moving, away from the first base assembly, the lifting assembly;
removing the first base assembly from the fitting;
attaching a second base assembly to the fitting; and
thereafter, moving, the mounting ring to a first height via moving, using a biasing system
comprising a piston pressing against the second base assembly, the lifting assembly away from the second base assembly, the first height being a greater distance away from the fuselage than the second height.

20. The method of claim 19 further comprising:
before removing the first base assembly from the fitting, inserting a retaining object between the fuselage and a bottom of the mounting ring; and
after attaching the second base assembly, removing the retaining object.

21. The method of claim 19 , further comprising:
the lifting assembly comprising a lifting bracket; and
reacting a bending moment in the lifting bracket against the second base assembly while moving the lifting assembly.

Assignees

• Boeing Co

Inventors

• Scheerer David E
• Joyce Patrick F

Classifications

• B64F5/50 Primary

  Handling or transporting aircraft components · CPC title

• B64F5/10

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

• B64F5/0009 Primary

  Operations & Transport · mapped topic

• B64C1/26

  Attaching the wing or tail units or stabilising surfaces · CPC title