Method and apparatus for supporting an aircraft structure during repair

Patent metadata

Field	Value
Publication number	US-9096331-B2
Application number	US-201314025332-A
Country	US
Kind code	B2
Filing date	Sep 12, 2013
Priority date	Sep 12, 2013
Publication date	Aug 4, 2015
Grant date	Aug 4, 2015

Abstract

Systems and methods for jacking an aircraft structure using beams coupled to seat tracks attached to a floor beam grid structure. Mechanical load distribution plates can have offset lift pin location to allow a certain percentage of the load to be applied to specific seat tracks. Different quantities of seat tracks can be utilized per requirements. Attachment rails that interface with the seat tracks use the same hardware that is used to fasten aircraft seats to the seat tracks. This helps handle the load and prevent damage to the seat tracks. The jacking apparatus also includes load swivels and a hanger link to prevent any side or twisting loads from being applied.

First claim

The invention claimed is:

1. A method for supporting an aircraft structure comprising :
(a) placing a beam so that one end protrudes out a first window opening on one side of a fuselage, another end protrudes out a second window opening on another side of the fuselage, and a portion of the beam inside the fuselage overlies a floor that is attached to the fuselage;
(b) mechanically coupling the beam to seat tracks on the floor; and
(c) raising the beam until at least a portion of the weight of the aircraft structure is supported by the beam via the mechanical coupling of the beam to the seat tracks.

2. The method as recited in claim 1 , wherein the beam is raised by jacking a pair of support posts which support the opposing ends of the beam.

3. The method as recited in claim 1 , wherein steps (a) through (c) are performed for each one of a multiplicity of beams.

4. The method as recited in claim 1 , wherein step (b) comprises:
coupling a load distribution plate to the beam;
coupling first and second rails to first and second seat tracks respectively; and
coupling the load distribution plate to the first and second rails.

5. The method as recited in claim 1 , wherein step (a) comprises:
placing a first beam segment so that one end protrudes out the first window opening on the one side of the fuselage and another end overlies the floor;
placing a second beam segment so that one end protrudes out the second window opening on the other side of the fuselage and another end overlies the floor; and
splicing the ends of the first and second beam segments that overlie the floor to each other.

6. The method as recited in claim 1 , further comprising terminating step (c) before the rising beam exerts any force on respective window frames surrounding the first and second window openings.

7. An apparatus for supporting an aircraft structure comprising:
a first beam having opposing ends;
first and second support posts that support the opposing ends of said first beam;
first and second jacks that respectively support said first and second support posts;
a first load distribution plate coupled to and disposed below said first beam; and
first and second rails coupled to and disposed below said first load distribution plate.

8. The apparatus as recited in claim 7 , further comprising:
a second beam having opposing ends;
third and fourth support posts that support said opposing ends of said second beam;
third and fourth jacks that respectively support said third and fourth support posts; and
a second load distribution plate coupled to and disposed below said second beam and coupled to and disposed above said first and second rails.

9. The apparatus as recited in claim 7 , further comprising:
a second beam having opposing ends;
a first load transfer beam that supports one opposing end of said first beam and one opposing end of said second beam, and is supported by said first support post;
a second load transfer beam that supports the other opposing end of said first beam and the other opposing end of said second beam, and is supported by said second support post; and
a second load distribution plate coupled to and disposed below said second beam, and coupled to and disposed above said first and second rails.

10. The apparatus as recited in claim 7 , wherein said first load distribution plate is coupled to said first beam by means of a saddle, a hanger link coupled to said saddle, and a swivel coupled to said hanger link and to said first load distribution plate.

11. The apparatus as recited in claim 7 , wherein said first beam comprises first and second beam segments and first and second splice plates attached to and connecting said first and second beam segments.

12. A system comprising an aircraft structure and a support apparatus, wherein said aircraft structure comprises a fuselage having respective multiplicities of window openings on opposite sides thereof, a floor attached to said fuselage, and first and second seat tracks attached to said floor, and wherein said support apparatus comprises:
a first beam arranged so that one end protrudes out a first window opening on one side of said fuselage, another end protrudes out a second window opening on another side of the fuselage, and a portion of the beam inside the fuselage overlies said floor;
first and second support posts that support said ends of said first beam;
first and second jacks that respectively support said first and second support posts; and
first and second rails coupled to said first beam, said first rail being coupled to said first seat track and said second rail being coupled to said second seat track.

13. The system as recited in claim 12 , wherein said first and second rails are coupled to said first beam by a tool assembly comprising a first load distribution plate that is coupled to said first and second rails.

14. The system as recited in claim 13 , wherein said tool assembly further comprises a saddle in contact with said first beam, a hanger link coupled to said saddle, and a swivel coupled to said hanger link and to said first load distribution plate.

15. The system as recited in claim 12 , further comprising:
a second beam having opposing ends;
third and fourth support posts that support said opposing ends of said second beam; and
third and fourth jacks that respectively support said third and fourth support posts,
wherein said first and second rails are coupled to said second beam.

16. The system as recited in claim 15 , wherein said first and second rails are coupled to said first beam by a first tool assembly comprising a first load distribution plate that is coupled to said first and second rails and are coupled to said second beam by a second tool assembly comprising a second load distribution plate that is coupled to said first and second rails.

17. The system as recited in claim 12 , further comprising:
a second beam having opposing ends;
a first load transfer beam that supports one opposing end of said first beam and one opposing end of said second beam, and is supported by said first support post; and
a second load transfer beam that supports the other opposing end of said first beam and the other opposing end of said second beam, and is supported by said second support post,
wherein said first and second rails are coupled to said second beam.

18. The system as recited in claim 17 , wherein said first and second rails are coupled to said first beam by a first tool assembly comprising a first load distribution plate that is coupled to said first and second rails and are coupled to said second beam by a second tool assembly comprising a second load distribution plate that is coupled to said first and second rails.

19. The system as recited in claim 12 , wherein said first beam comprises first and second beam segments and first and second splice plates attached to and connecting said first and second beam segments.

20. A method for lifting an aircraft structure comprising:
(a) supporting a plurality of beams on a plurality of support posts;
(b) mechanically coupling the plurality of beams to a plurality of seat tracks attached to a floor of the aircraft structure; and
(c) jacking the plurality of support posts until the plurality of beams exert forces on the plurality of seat tracks sufficient to lift the aircraft structure.

21. The method as recited in claim 20 , wherein the aircraft structure comprises a fuselage to which the floor is attached, the fuselage having a first p

Assignees

• Boeing Co

Inventors

• Gehlsen Paul Ronald

Classifications

• B64F5/40 Primary

  Maintaining or repairing aircraft · CPC title

• B66F11/00 Primary

  Lifting devices specially adapted for particular uses not otherwise provided for (ground-engaging vehicle fittings for supporting, lifting or manoeuvring the vehicle B60S9/00) · CPC title

• B64F5/0081 Primary

  Operations & Transport · mapped topic