Abstract: A method of reassembling a gas turbine engine including steps to support a core engine on a core stand and support a fan case on a fan stand that includes a base frame coupled a fan case frame by a hinge. The fan case frame is arranged to (i) rotate about an axis of the hinge between abutting the base frame and being perpendicular to the base frame, and (ii) tilt about a yaw axis perpendicular to the hinge, which is located in a plane of the fan case frame. The method includes rotating and tilting the fan case frame to align the fan case and core engine, translating at least one of the core engine and the fan case into axial abutment, coupling the fan case and the core engine to reassemble the gas turbine engine, and decoupling the fan case from the fan stand.

Abstract: A method of reassembling a gas turbine engine including steps to support a core engine on a core stand and support a fan case on a fan stand that includes a base frame coupled a fan case frame by a hinge. The fan case frame is arranged to (i) rotate about an axis of the hinge between abutting the base frame and being perpendicular to the base frame, and (ii) tilt about a yaw axis perpendicular to the hinge, which is located in a plane of the fan case frame. The method includes rotating and tilting the fan case frame to align the fan case and core engine, translating at least one of the core engine and the fan case into axial abutment, coupling the fan case and the core engine to reassemble the gas turbine engine, and decoupling the fan case from the fan stand.

Abstract: A method of separating a gas turbine engine includes steps to support the gas turbine engine on a core stand, and to move a fan stand into axial alignment with a core stand. The fan stand includes a base frame and a fan case frame coupled to the base frame at one edge by a hinge. The fan case frame rotates about an axis of the hinge between abutting the base frame and being perpendicular to the base frame, and includes a coupling arrangement that couples a fan case to the fan case frame. The method further includes steps to rotate and tilt the fan case frame into abutting relation with the fan case, couple the fan case to the fan case frame, decouple the fan case and core engine, and translate at least part of the core stand axially to separate the gas turbine engine.

Abstract: A gas turbine engine fan stand (40) comprising a base frame (42) and a fan case frame (44) coupled together at one edge by a hinge (46). The fan case frame (44) is arranged to: rotate about the hinge (46) between abutting the base frame (42) and substantially perpendicular thereto; and tilt about a yaw axis (52) perpendicular to the hinge (46) and in the plane of the fan case frame (44). The fan case frame (44) further comprising a coupling arrangement (56) arranged to rotate about a roll axis (60) and to couple a fan case (36) to the fan case frame (44). A gas turbine engine stand assembly (68) comprising a fan stand (40) and a core stand (38). A method of splitting a gas turbine engine (10) and a method of reassembling a gas turbine engine (10).

Abstract: A gas turbine engine fan stand including a base frame and a fan case frame coupled together at one edge by a hinge. The fan case frame is arranged to: rotate about the hinge between abutting the base frame and substantially perpendicular thereto; and tilt about a yaw axis perpendicular to the hinge and in the plane of the fan case frame. The fan case frame further including a coupling arrangement arranged to rotate about a roll axis and to couple a fan case to the fan case frame. A gas turbine engine stand assembly including a fan stand and a core stand. A method of splitting a gas turbine engine and a method of reassembling a gas turbine engine.

Abstract: A gas turbine engine stand comprising an engine frame and a base frame. The base frame has a slide rail to enable axial translation of the engine frame relative to the base frame. A load transfer arrangement engages with a part of the engine frame and slidingly engages with the slide rail. There is a locking mechanism to lock the engine frame to the base frame to prevent relative axial translation. The gas turbine engine stand is used, inter alia, for splitting a core engine from a fan case.

Abstract: A gas turbine engine stand (38) comprising an engine frame (48) and a base frame (46). The base frame (46) has a slide rail (51) to enable axial translation of the engine frame (48) relative to the base frame (46). A load transfer arrangement (54) engages with a part (50) of the engine frame (48) and slidingly engages with the slide rail (51). There is a locking mechanism (62) to lock the engine frame (48) to the base frame (46) to prevent relative axial translation. The gas turbine engine stand (38) is used, inter alia, for splitting a core engine (34) from a fan case (36).

Abstract: A gas turbine engine fan stand (40) comprising a base frame (42) and a fan case frame (44) coupled together at one edge by a hinge (46). The fan case frame (44) is arranged to: rotate about the hinge (46) between abutting the base frame (42) and substantially perpendicular thereto; and tilt about a yaw axis (52) perpendicular to the hinge (46) and in the plane of the fan case frame (44). The fan case frame (44) further comprising a coupling arrangement (56) arranged to rotate about a roll axis (60) and to couple a fan case (36) to the fan case frame (44). A gas turbine engine stand assembly (68) comprising a fan stand (40) and a core stand (38). A method of splitting a gas turbine engine (10) and a method of reassembling a gas turbine engine (10).