A translating cowl (transcowl) assembly for a thrust reverser system for a turbine engine, the transcowl assembly comprising: an outer skin comprised of a first composite material, the outer skin further comprising the characteristics of (i) being substantially continuous in both a circumferential direction and a longitudinal direction, (ii) an outer skin outer surface providing aerodynamic continuity with a nacelle, and (iii) an outer skin inner surface; an inner skin comprised of a second composite material and configured to provide an aerodynamic exit flow path for engine exhaust, the inner skin further comprising the characteristics of (i) an inner skin outer surface configured to couple circumferentially with the outer skin inner surface, (ii) an inner skin inner surface comprising a contoured depression configured to provide clearance for movement of a blocker door, the contoured depression having a cross-section comprising three sections: a first section that is substantially concave forward to aft; a second section that is substantially convex forward to aft; a third section that is approximately linear forward to aft; and a metallic bracket disposed between the outer skin inner surface and the inner skin outer surface, and configured to (i) attach the outer skin to a thrust reverser actuation system, and (ii) distribute a structural load associated with the thrust reverser actuation system onto the outer skin, wherein the blocker door is one of two or more blocker doors, and wherein the inner skin comprises, for each blocker door of the two or more blocker doors, a respective contoured depression configured to provide clearance for movement of the blocker door, wherein the inner skin comprises two or more segments abutted circumferentially, wherein each segment of the two or more segments comprise a contoured depression, and the two or more segments provide, for each blocker door of two or more blocker doors, a respective contoured depression an outer skin comprised of a first composite material, the outer skin further comprising the characteristics of (i) being substantially continuous in both a circumferential direction and a longitudinal direction, (ii) an outer skin outer surface providing aerodynamic continuity with a nacelle, and (iii) an outer skin inner surface; an inner skin comprised of a second composite material and configured to provide an aerodynamic exit flow path for engine exhaust, the inner skin further comprising the characteristics of (i) an inner skin outer surface configured to couple circumferentially with the outer skin inner surface, (ii) an inner skin inner surface comprising a contoured depression configured to provide clearance for movement of a blocker door, the contoured depression having a cross-section comprising three sections: a first section that is substantially concave forward to aft; a second section that is substantially convex forward to aft; a third section that is approximately linear forward to aft; and a first section that is substantially concave forward to aft; a second section that is substantially convex forward to aft; a third section that is approximately linear forward to aft; and a metallic bracket disposed between the outer skin inner surface and the inner skin outer surface, and configured to (i) attach the outer skin to a thrust reverser actuation system, and (ii) distribute a structural load associated with the thrust reverser actuation system onto the outer skin, wherein the blocker door is one of two or more blocker doors, and wherein the inner skin comprises, for each blocker door of the two or more blocker doors, a respective contoured depression configured to provide clearance for movement of the blocker door, wherein the inner skin comprises two or more segments abutted circumferentially, wherein each segment of the two or more segments comprise a contoured depression, and the two or more segments provide, for each blocker door of two or more blocker doors, a respective contoured depression