A turbofan engine comprising: a fan having a plurality of blades; a transmission configured to drive the fan; and three spools, wherein said three spools comprise: a first spool comprising: a first pressure turbine; and a first shaft coupling the first pressure turbine to the transmission; a second spool comprising: a second pressure turbine; a first compressor; and a second spool shaft coupling the second pressure turbine to the first compressor; and a core spool comprising: a third pressure turbine; a second compressor; and a core shaft coupling the third pressure turbine to second compressor; wherein: the fan blades have a peak tip radius R T; the fan blades have an inboard leading edge radius R H at an inboard boundary of the flowpath; a combustor is between the second compressor and the third pressure turbine; and the engine further comprises a plurality of main bearings, wherein a first of said main bearings engages a static support (164; 164') and a forward hub of the second spool, and a second of said main bearings engages the first shaft and the forward hub of the second spool; and characterized in that a ratio of R H to R T is less than about 0.40, and wherein one or more of: a length between said first of said main bearings and a center of gravity of a rotor of the first compressor is less than half of a disk to disk overall length of the first compressor; and a length between said first of said main bearings and a center of gravity of a rotor of the first compressor is less than a radius R I of the inboard boundary of the core flowpath at a leading stage of blades of the first compressor. a fan having a plurality of blades; a transmission configured to drive the fan; and three spools, wherein said three spools comprise: a first spool comprising: a first pressure turbine; and a first shaft coupling the first pressure turbine to the transmission; a second spool comprising: a second pressure turbine; a first compressor; and a second spool shaft coupling the second pressure turbine to the first compressor; and a core spool comprising: a third pressure turbine; a second compressor; and a core shaft coupling the third pressure turbine to second compressor; a first spool comprising: a first pressure turbine; and a first shaft coupling the first pressure turbine to the transmission; a first pressure turbine; and a first shaft coupling the first pressure turbine to the transmission; a second spool comprising: a second pressure turbine; a first compressor; and a second spool shaft coupling the second pressure turbine to the first compressor; and a second pressure turbine; a first compressor; and a second spool shaft coupling the second pressure turbine to the first compressor; and a core spool comprising: a third pressure turbine; a second compressor; and a core shaft coupling the third pressure turbine to second compressor; a third pressure turbine; a second compressor; and a core shaft coupling the third pressure turbine to second compressor; wherein: the fan blades have a peak tip radius R T; the fan blades have an inboard leading edge radius R H at an inboard boundary of the flowpath; a combustor is between the second compressor and the third pressure turbine; and the engine further comprises a plurality of main bearings, wherein a first of said main bearings engages a static support (164; 164') and a forward hub of the second spool, and a second of said main bearings engages the first shaft and the forward hub of the second spool; and the fan blades have a peak tip radius R T; the fan blades have an inboard leading edge radius R H at an inboard boundary of the flowpath; a combustor is between the second compressor and the third pressure turbine; and the engine further comprises a plurality of main bearings, wherein a first of said main bearings engages a static support (164; 164') and a forward hub of the second spool, and a second of said main bearings engages the first shaft and the forward hub of the second spool; and characterized in that a ratio of R H to R T is less than about 0.40, and wherein one or more of: a length between said first of said main bearings and a center of gravity of a rotor of the first compressor is less than half of a disk to disk overall length of the first compressor; and a length between said first of said main bearings and a center of gravity of a rotor of the first compressor is less than a radius R I of the inboard boundary of the core flowpath at a leading stage of blades of the first compressor. a length between said first of said main bearings and a center of gravity of a rotor of the first compressor is less than half of a disk to disk overall length of the first compressor; and a length between said first of said main bearings and a center of gravity of a rotor of the first compressor is less than a radius R I of the inboard boundary of the core flowpath at a leading stage of blades of the first compressor.