Geared turbofan engine with integral gear and bearing supports

A gas turbine engine (10) includes a bearing (58) and a bearing support (66) having a first wall (76) extending between first and second ends and operatively supported by the bearing (58) at a first end. An engine case (48) is secured to the second end radially outward of the first end. A second wall (78) integral with and extending transversely from the first wall (76) provides a flexible support (74). The second wall (78) has a flange (82), and a gear train component (46) is secured to the flange (82). The gas turbine engine (10) includes a support structure which supports the main rotatable structure via bearings and gear train components. The support provides both the necessary structural support for the rotor structure as well as desired flexibility for a fan drive gear system.