The design of next-generation transport aircraft addresses efficiency improvements by, e.g., modifying the wing geometry in order to delay the onset of laminar-turbulent transition in the boundary layer. A crossflow attenuated natural laminar flow (CATNLF) design can be used to avoid crossflow transition and therefore reduces the amount of viscous drag. Although the design process includes different on- and off-design cases, extensive optimization of the primary structure of the wing is usually not considered in early design stages. In order to ensure a robust laminar wing design, the impact of mass cases with various payload and fuel mass configurations on the laminar-turbulent transition must be analyzed to provide possible stiffness constraints for the structural optimization process of the aircraft. Within this paper, transitional CFD simulations are conducted on a transport aircraft configuration with a backward-swept laminar wing for different mass cases. The impact of the resulting wing deflections on the transition location in the boundary layer is studied. Despite the relatively large bending deformations achieved with the heaviest mass case, almost no differences in transition location can be found at the considered design point, which indicates a robust behavior of the laminar wing design.