Splice joints for composite aircraft fuselages and other structures

A method for manufacturing an aircraft fuselage, the method comprising:

• attaching at least a first stiffener to a first composite skin, wherein the first stiffener has a first flange portion attached to the first composite skin and a first raised portion projecting away from the first composite skin, the first composite skin extending 360 degrees around a first axis;
• attaching at least a second stiffener to a second composite skin, wherein the second stiffener has a second flange portion attached to the second composite skin and a second raised portion projecting away from the second composite skin, the second composite skin extending 360 degrees around a second axis;
• positioning the first composite skin adjacent to the second composite skin so that the first and second axes are at least approximately aligned;
• and
• attaching a first end portion of a fitting to the first stiffener and the first composite skin and a second end portion of the fitting to the second stiffener and the second composite skin to join the first composite skin to the second composite skin, wherein attaching the first end portion of the fitting to the first stiffener includes attaching the first end portion to the first flange portion, and wherein attaching the second end portion of the fitting to the second stiffener includes attaching the second end portion to the second flange portion.