Fuel efficiency, endurance, and noise requirements are pushing modern aircraft to lighter, more flexible designs. This causes the structural modes to occur at lower frequencies increasing the coupling with the rigid body dynamics. The traditional approach to handle aeroservoelastic inter- action is to design gain-scheduled flight control laws based on the rigid body dynamics and then use filters to avoid exciting the structural modes. This decoupled approach may not be possible in future, more flexible aircraft without reducing the flight control law bandwidth. Linear parameter varying (LPV) techniques provide a framework for modeling, analysis, and design of the control laws across the flight envelope. This paper applies LPV techniques for the roll control of NASA Dryden's X-53 Active Aeroelastic Wing testbed. LPV techniques are first used to analyze a gain- scheduled classical controller. Gain scheduling is still the dominant design method in industrial flight control laws and LPV analysis tools can play an important role in certifying the performance of these systems. Next, an LPV controller is designed and its performance is compared against the gain-scheduled classical controller.