An aircraft comprising: a fuselage comprising at least one variable height web composite frame beam wherein the variable height web composite frame beam is a laminate composite structural beam comprising: a variable height web; a first flange located on an outer portion of the web; a second flange located on an inner portion of the web, wherein the first flange and the second flange are separated by a first distance at a first portion of the laminate composite structural beam and separated by a second distance at a second portion of the laminate composite structural beam; wherein the laminate composite structural beam is configured to be disposed adjacent to an aircraft wheel well opening; wherein, of the laminate composite structural beam, the first distance is greater than the second distance, wherein the first portion of the laminate composite structural beam is adjacent to the wheel well opening of the fuselage, and wherein the second portion of the laminate composite structural beam is disposed farther from the wheel well opening than the first portion of the laminate composite structural beam; and wherein the laminate composite structural beam is a discontinuous beam and further comprises a first end disposed near the first portion of the laminate composite structural beam and the fuselage further comprises a wheel well beam (430, 432, 434) coupled to the first end, wherein the wheel well beam further defines a vertical portion of the wheel well, and further wherein the discontinuous laminate composite structural beam and the wheel well beam are one component. a fuselage comprising at least one variable height web composite frame beam wherein the variable height web composite frame beam is a laminate composite structural beam comprising: a variable height web; a first flange located on an outer portion of the web; a second flange located on an inner portion of the web, wherein the first flange and the second flange are separated by a first distance at a first portion of the laminate composite structural beam and separated by a second distance at a second portion of the laminate composite structural beam; a variable height web; a first flange located on an outer portion of the web; a second flange located on an inner portion of the web, wherein the first flange and the second flange are separated by a first distance at a first portion of the laminate composite structural beam and separated by a second distance at a second portion of the laminate composite structural beam; wherein the laminate composite structural beam is configured to be disposed adjacent to an aircraft wheel well opening; wherein, of the laminate composite structural beam, the first distance is greater than the second distance, wherein the first portion of the laminate composite structural beam is adjacent to the wheel well opening of the fuselage, and wherein the second portion of the laminate composite structural beam is disposed farther from the wheel well opening than the first portion of the laminate composite structural beam; and wherein the laminate composite structural beam is a discontinuous beam and further comprises a first end disposed near the first portion of the laminate composite structural beam and the fuselage further comprises a wheel well beam (430, 432, 434) coupled to the first end, wherein the wheel well beam further defines a vertical portion of the wheel well, and further wherein the discontinuous laminate composite structural beam and the wheel well beam are one component. wherein, of the laminate composite structural beam, the first distance is greater than the second distance, wherein the first portion of the laminate composite structural beam is adjacent to the wheel well opening of the fuselage, and wherein the second portion of the laminate composite structural beam is disposed farther from the wheel well opening than the first portion of the laminate composite structural beam; and wherein the laminate composite structural beam is a discontinuous beam and further comprises a first end disposed near the first portion of the laminate composite structural beam and the fuselage further comprises a wheel well beam (430, 432, 434) coupled to the first end, wherein the wheel well beam further defines a vertical portion of the wheel well, and further wherein the discontinuous laminate composite structural beam and the wheel well beam are one component.