Aircraft engine repair tool and method for removal and installation of a mid turbine frame in an aircraft engine

An assembly comprising:

• a gas turbine engine including a mid turbine frame located between a first turbine rotor and a second turbine rotor in a turbine section of the gas turbine engine during operation of the gas turbine engine, the mid turbine frame being releasably attached to a support structure within the gas turbine engine, the gas turbine engine including a shaft supporting the first turbine rotor, the mid turbine frame rotatably supporting the shaft relative to the support structure about a rotation axis, the mid turbine frame defining a first load path between the shaft and the support structure, the second turbine rotor being uninstalled from the gas turbine engine;
• and
• an aircraft engine repair tool for installing and/or removing the mid turbine frame when the mid turbine frame is released from the support structure of the gas turbine engine, the aircraft engine repair tool including:
• a stabilizer supporting the shaft via a second load path between the shaft and the support structure, the second load path being different from the first load path;
• a holder attached to the mid turbine frame;
• and
• a guide movably engaged with the shaft and attached to the holder, the guide being configured to guide a movement of the holder and the mid turbine frame relative to the shaft along the rotation axis, and to prevent a movement of the holder and the mid turbine frame relative to the shaft transverse to the rotation axis when the mid turbine frame is released from the support structure.