Abstract: A tool for immobilising a first shaft of a gas turbine engine in relation to a second shaft of a gas turbine engine, the tool comprising a cylindrical body having a first end and a second end opposite the first end, the cylindrical body having one or more interior protrusions on the inner surface of the cylindrical body for engaging with the first shaft, and the outer surface of the cylindrical body having one or more exterior protrusions for engaging with the second shaft, the tool being configured such that at least part of the tool can be inserted within and held fixed relative to a section of the second shaft, and a section of the first shaft can be inserted within and held fixed relative to the interior of the cylindrical body.

Abstract: A gas turbine engine maintenance stand for a gas turbine engine that comprises modules including an engine core module that houses a high pressure compressor and a turbine module that houses a low pressure turbine. The gas turbine engine maintenance stand has a pair of base beams, each base beam having a first end, a midsection and a second end. The stand has an engine core module support that straddles the pair of base beams at their midsection, the engine core module support having engine core module support arms that are configured to engage opposing sides of the engine core module of the gas turbine engine. The stand also has a turbine module support that straddles the pair of beams adjacent their second ends, the turbine module support having turbine module support arms that are configured to engage opposing sides of the turbine module of the gas turbine engine.

Abstract: A gas turbine engine maintenance stand for a gas turbine engine that comprises modules including an engine core module that houses a high pressure compressor and a turbine module that houses a low pressure turbine. The gas turbine engine maintenance stand has a pair of base beams, each base beam having a first end, a midsection and a second end. The stand has an engine core module support that straddles the pair of base beams at their midsection, the engine core module support having engine core module support arms that are configured to engage opposing sides of the engine core module of the gas turbine engine. The stand also has a turbine module support that straddles the pair of beams adjacent their second ends, the turbine module support having turbine module support arms that are configured to engage opposing sides of the turbine module of the gas turbine engine.