Assembly using skeleton structure

1. A method for making a fuselage section, the method comprising steps:

(a) assembling a support system comprising fiber reinforced composite material, the support system including at least three frames and six stringers;

(b) partially curing the support system via a fast cure process such that the support system attains about eighty percent of its fully cured strength;

(c) globally positioning a skin comprising uncured fiber reinforced composite material such that an inner surface of the skin corresponds to an outer surface of the support system; and

(d) fully curing the skin and the support system together;

wherein the support system is assembled on a bonding tool having a bonding surface corresponding to an inner surface of the skin;

wherein each of the three frames includes a plurality of locking features to facilitate securement of the three frames to the six stringers.

2. The method of claim 1 , further comprising the step of conducting quality control testing on the support system before the uncured skin is positioned thereon.

3. The method of claim 2 , wherein the tool is a male tool.

4. The method of claim 3 , wherein the male tool comprises at least a first attachment member, a second attachment member, and a third attachment member; and wherein:

the first attachment member is adjacent the second attachment member and connected thereto by a plurality of first connecting members;

the second attachment member is adjacent the third attachment member and connected thereto by a plurality of second connecting members;

a distance between the first and the second attachment members is different from a distance between the second and the third attachment members.

5. The method of claim 4 , wherein each attachment member comprises Masonite.

6. The method of claim 2 , wherein the tool is a female tool having an outer surface configured to correspond to an inner surface of the skin.