A gas turbine engine comprising: a fan rotor comprising fan blades driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of said fan rotor relative to a speed of said fan drive turbine; a fan case surrounding said fan rotor, and an inner core housing surrounding a compressor section, including a low pressure compressor; said fan rotor delivering air into a bypass duct defined between said fan case and a splitter wall of said inner core housing, and a rigid connection between said fan case and said inner core housing including a plurality of A-frames each including a pair of legs (118, 120) rigidly connected at a connection point to said fan case, and each leg (118, 120) in said pair extending away from said connection point in opposed circumferential directions to be connected to a compressor wall of said inner core housing to form an A-shape; and the rigid connection also including a plurality of fan exit guide vanes (114, 129) rigidly connected to said fan case, the plurality of fan exit guide vanes (114, 129) including a plurality of structural guide vanes and a plurality of non-structural guide vanes, each of the plurality of non-structural guide vanes comprising an outer skin with perforations and provided over a plurality of chambers; and a lateral stiffness is defined in a radial direction, a lateral stiffness ratio of the lateral stiffness of the plurality of fan exit guide vanes (114, 129) and a lateral stiffness of a combination of the plurality of A-frame, the compressor wall, and a fan intermediate case which is forward of the low pressure compressor (44, 112) being greater than or equal to 0.6 and less than or equal to 2.0. a fan rotor comprising fan blades driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of said fan rotor relative to a speed of said fan drive turbine; a fan case surrounding said fan rotor, and an inner core housing surrounding a compressor section, including a low pressure compressor; said fan rotor delivering air into a bypass duct defined between said fan case and a splitter wall of said inner core housing, and a rigid connection between said fan case and said inner core housing including a plurality of A-frames each including a pair of legs (118, 120) rigidly connected at a connection point to said fan case, and each leg (118, 120) in said pair extending away from said connection point in opposed circumferential directions to be connected to a compressor wall of said inner core housing to form an A-shape; and the rigid connection also including a plurality of fan exit guide vanes (114, 129) rigidly connected to said fan case, the plurality of fan exit guide vanes (114, 129) including a plurality of structural guide vanes and a plurality of non-structural guide vanes, each of the plurality of non-structural guide vanes comprising an outer skin with perforations and provided over a plurality of chambers; and a lateral stiffness is defined in a radial direction, a lateral stiffness ratio of the lateral stiffness of the plurality of fan exit guide vanes (114, 129) and a lateral stiffness of a combination of the plurality of A-frame, the compressor wall, and a fan intermediate case which is forward of the low pressure compressor (44, 112) being greater than or equal to 0.6 and less than or equal to 2.0.