This paper investigates the utility of trailing edge flaps (TEF) for helicopter rotor vibration suppression using a coupled CFD/CSD rotor aeroelastic analysis. The CFD methodology uses a Reynolds Averaged Navier-Stokes (RANS) approach and is incrementally validated for 2-D and 3-D computational test cases on airfoil/wing geometries that include TEF’s. An integral flap is assumed in all computations, ie gaps are not modeled. In this context a novel grid deformation technique based on algebraic decay is implemented for efficiently modeling the deflection of integral TEF’s. Further, the CFD analysis is combined with a rotor comprehensive analysis (which provides the CSD model and rotor trim) to form a higher fidelity analysis platform for rotor aeromechanics. The coupled CFD/CSD aeroelastic analysis is first validated against DNW wind tunnel test results for a model scale rotor. Following the validation, the sensitivity of fixed frame vibratory loads to TEF actuation is investigated. Numerical experiments are used to identify an optimal flap actuation which shows simultaneous reduction in all components of 4/rev hub loads (with a maximum reduction of 50% in the Fy component).