The present invention relates to a gas turbine engine. The aircraft gas turbine engine (10) comprises a high pressure compressor (20) coupled to a high pressure turbine (24) by a high pressure shaft (32), and a low pressure compressor (18) coupled to a low pressure turbine (26) by a low pressure shaft (34). The engine (10) includes a first shaft bearing (38) supporting a forward end of the low pressure shaft (34) and being mounted to a static structure (58) forward of the high pressure turbine (24). The engine also includes a second shaft bearing (64) supporting a rearward end of the low pressure shaft (34) and being mounted to a static structure (70) between the high pressure (24) and the low pressure turbine (26). The engine further includes a third shaft bearing (74) supporting the rearward end of the low pressure shaft (34) and being mounted to a static structure (76) rearward of the low pressure turbine (26).