Fuselage skin is all-composite in Boeing 787. Repair programs for composite fuselage skin are given in Boeing 787 structural repair manual, including composite fuselage skin repair with titanium plates riveting. However, the maintenance theory of these repair programs and repair procedures, strength, stiffness and other mechanical properties of these repair programs are not described. Based on this, two dimensional finite element models of composite fuselage skin repair with titanium plates riveting are established in this paper. Stress size and distribution of matrix, patch and fill flat are analyzed on these two repair programs. Studies have shown that repairing large composite fuselage skin penetration crack with titanium plates riveting can meet the static strength requirements. Destroy sources of titanium patches of these two repair programs will occur at different locations.