Direct Lift Control (DLC) uses control devices at the wing that allow for directly adjusting lift. When properly combined with adjustment of angle of attack, the non-minimum-phase behavior associated with elevator controls is removed, and the load factor response time and disturbance rejection improve considerably. DLC has seen only limited application though, due to the absence of suitable control devices and actuation capability on current wing designs. Future concepts tend to move towards more use of multi-functional control devices along the trailing edge to accommodate for integration of load alleviation and cruise performance optimizing functions. This allows for providing DLC capability by means of a suitable allocation scheme, providing good reasons for its renewed consideration. From this perspective, this work addresses the crucial aforementioned proper integration with angle of attack adjustment to allow for optimal use of DLC. Two architectures are proposed and compared through simulation analyses based on an experimental aircraft intended to demonstrate advanced wing concepts. Hardware-in-the-Loop tests are also performed replacing the DLC control devices and actuation system with a physical control surface system. Both architectures show considerable improvement in handling, disturbance rejection and passenger comfort in comparison with traditional concepts.