Method of repairing damage to fuselage barrel and associated apparatus and system

1. A method of replacing a portion of a fuselage barrel of an aircraft having a seamless construction, comprising:

determining at least a first splice line and a second splice line along the fuselage barrel in a direction parallel to a longitudinal axis of the fuselage barrel;

subsequent to determining at least the first splice line and the second splice line, detecting damage in a first section of the fuselage barrel between the first splice line and the second splice line;

cutting through the fuselage barrel, after detecting damage, along the first splice line and the second splice line to physically separate the first section from a main section of the fuselage barrel;

removing the cut first section from the main section of the fuselage barrel; and

splicing a new section, that is not co-formed with the main section, to the main section of the fuselage barrel in place of the removed first section.

2. The method according to claim 1 , wherein:

the fuselage barrel extends longitudinally along the longitudinal axis from a first end to a second end; and

the first splice line and the second splice line both extend from the first end of the fuselage barrel to the second end of the fuselage barrel.

3. The method according to claim 1 , wherein splicing the new section to the main section of the fuselage barrel comprises forming a first butt joint, along the first splice line, and a second butt joint, along the second splice line, parallel to the longitudinal axis, between the new section and the main section of the fuselage barrel.

4. The method according to claim 3 , wherein splicing the new section to the main section of the fuselage barrel further comprises:

overlaying the first butt joint with a first splice plate;

overlaying the second butt joint with a second splice plate; and

fastening the first splice plate and the second splice plate to an interior surface of the main section of the fuselage barrel and an interior surface of the new section.

5. The method according to claim 4 , wherein:

removing the first section from the main section of the fuselage barrel comprises:

decoupling a frame element, extending circumferentially about the fuselage barrel, from a first shear tie coupled to the fuselage barrel over the first splice line and from a second shear tie coupled to the fuselage barrel over the second splice line;

decoupling the first shear tie from the fuselage barrel; and

decoupling the second shear tie from the fuselage barrel; and

splicing the new section to the main section of the fuselage barrel comprises:

coupling a first replacement shear tie to the first splice plate, wherein the first replacement shear tie is configured differently than the first shear tie;

coupling a second replacement shear tie to the second splice plate, wherein the second replacement shear tie is configured differently than the second shear tie; and

coupling the frame element to the first replacement shear tie and the second replacement shear tie.

6. The method according to claim 4 , wherein:

the first splice plate comprises multiple first splice plate segments arranged substantially end-to-end along the first butt joint;

the second splice plate comprises multiple second splice plate segments arranged substantially end-to-end along the second butt joint;

splicing the new section to the main section of the fuselage barrel further comprises intercoupling adjacent first splice plate segments with at least one coupler fixed to and spanning at least portions of the adjacent first splice plate segments; and

splicing the new section to the main section of the fuselage barrel further comprises intercoupling adjacent second splice plate segments with at least one coupler fixed to and spanning at least portions of the adjacent second splice plate segments.

7. The method according to claim 4 , wherein:

a plurality of stringers, circumferentially spaced apart from each other and extending along the fuselage barrel parallel to the longitudinal axis of the fuselage barrel, are coupled to the fuselage barrel;

the plurality of stringers are grouped into at least a first pair of stringers, comprising a first stringer, and a second pair of stringers, comprising a third stringer;

the first splice line extends between the first pair of stringers; and

the second splice line extends between the second pair of stringers.

8. The method according to claim 7 , wherein splicing the new section to the main section of the fuselage barrel comprises:

positioning a first filler between the first splice plate and the first butt joint and between the first stringer and a second stringer of the new section; and

positioning a second filler between the second splice plate and the second butt joint and between the third stringer and a fourth stringer of the new section.

9. The method according to claim 7 , wherein the fuselage barrel, first splice plate, second splice plate, and plurality of stringers are made from a fiber-reinforced polymer.

10. The method according to claim 1 , wherein:

the aircraft comprises multiple fuselage barrels coupled to each other in an end-to-end manner to form a fuselage of the aircraft;

removing the first section from the main section of the fuselage barrel comprises decoupling the first section of the fuselage barrel from adjacent fuselage barrels; and

splicing the new section to the main section of the fuselage barrel comprises coupling the new section to adjacent fuselage barrels.

11. The method according to claim 1 , wherein the new section is pre-manufactured, responsive to a location on the fuselage barrel of the first splice line and the second splice line.

12. The method according to claim 1 , wherein determining at least the first splice line and the second splice line comprises:

detecting a path along an interior surface of the fuselage barrel having a line of sight from one end of the path to an opposite end of the path; and

locating one of the first splice line and the second splice line along the path.

13. The method according to claim 1 , wherein each of the first section and the new section forms at least a quarter of the fuselage barrel.

14. The method according to claim 1 , further comprising, determining at least a third splice line along the fuselage barrel in a direction parallel to a longitudinal axis of the fuselage barrel.