A tool for performing inspection and/or maintenance operations on an engine defines a longitudinal direction and a tangential direction. The tool includes a base extending along the longitudinal direction and including a body, a first extension member extending from the body in the tangential direction at a first location, and a second extension member extending from the body in the tangential direction at a second location. The second location is spaced from the first location along the longitudinal direction. The tool also includes a pivot member rotatably coupled to the base and moveable between an insertion position in which the pivot member is oriented generally along the longitudinal direction and a deployed position in which the pivot member is oriented away from the longitudinal direction.

A method is provided for treating a fuel system of a turbine engine. During this method, a treatment system is connected to the turbine engine. Preservation fluid is drawn out of the fuel system using the treatment system.

A damage evaluation device evaluates damage of equipment, including an operation data obtaining unit which detects a state of the equipment to obtain the state as operation data; an operating state quantity evaluation unit which calculates an operating state quantity including at least one of temperature and generated stress at a predetermined evaluation-target site of the equipment, based on the operation data; a material deterioration evaluation unit which evaluates a material deterioration quantity of a material forming the equipment, based on the operating state quantity; a risk evaluation unit which evaluates at least one of a cumulative damage quantity of the material forming the equipment and failure risk, based on the operating state quantity and the material deterioration quantity; and a recommended maintenance time presentation unit which presents a recommended maintenance time of the equipment based on a result of the evaluation of the risk evaluation unit.

A rotor loading system for an aircraft turbine engine has a first tool having first proximal and first distal ends. The first proximal end defines a traction interface about a first axis and a first surface radially outward of the traction interface. The first distal end defines first projections spaced circumferentially and extending to outward of the first surface. The system has a second tool with second proximal and second distal ends. The second proximal end defines a torque interface about a second axis and a second surface radially outward of the torque interface. The second distal end defines second projections spaced circumferentially and extending to outward of the second surface. One of the first and the second tool is received by the other one of the tools such that: the first and the second axis are colinear and each of the first projections is received between two second projections.

A selectively flexible extension tool includes: a line assembly comprising a first line and a second line; and a plurality of sequentially arranged links, the line assembly operable with the plurality of sequentially arranged links to move the plurality of sequentially arranged links between a slacked position and a tensioned position, the plurality of sequentially arranged links together comprising a first line guide and a second line guide, the first line of the line assembly extending through the first line guide and the second line of the line assembly extending through the second line guide; wherein the first line defines a first displacement when the plurality of sequentially arranged links are moved from the slacked position to the tensioned position, wherein the second line defines a second displacement when the plurality of sequentially arranged links are moved from the slacked position to the tensioned position, and wherein the first displacement is substantially equal to the second displacement.

A turbojet engine with two thrust reverser modules. Each module includes an outer casing, an inner casing and a securing system for securing the inner casing to the outer casing which comprises first and second hoods. A housing between the hoods has a securing wall, a seal with a sausage secured to the securing wall, and a crusher rigidly secured to the second hood and arranged so as to crush the sausage towards the securing wall when the second hood goes from the spaced-apart position to the close-together position. Therefore, the sausage moves in the longitudinal direction, thus limiting shearing of the seal and transverse movements owing to the manufacturing and assembly tolerances and the movements in flight.

A damage evaluation device evaluates damage of equipment, including an operation data obtaining unit which detects a state of the equipment to obtain the state as operation data; an operating state quantity evaluation unit which calculates an operating state quantity including at least one of temperature and generated stress at a predetermined evaluation-target site of the equipment, based on the operation data; a material deterioration evaluation unit which evaluates a material deterioration quantity of a material forming the equipment, based on the operating state quantity; a risk evaluation unit which evaluates at least one of a cumulative damage quantity of the material forming the equipment and failure risk, based on the operating state quantity and the material deterioration quantity; and a recommended maintenance time presentation unit which presents a recommended maintenance time of the equipment based on a result of the evaluation of the risk evaluation unit.

A method for repairing an at least externally coated hollow component. The direct mechanical machining of a coated component after use removes the need for a coating-removal and selective hollowing step and a selective repair of cracks, since a design adaptation leads to a component being engineered or used such that it can be used again as a result of external dimensional stipulations.

A device cleans a core engine of a jet engine. The device has: a nozzle installation configured to introduce a cleaning medium into the core engine; a connector configured to connect the device in a rotationally fixed manner to a shaft of a fan of the jet engine; and a line connection configured to supply the cleaning medium, the line connection being connected to the nozzle installation by a rotary coupling. The nozzle installation has first contact faces configured to bear axially on fan blades of the fan, the first contact faces being configured for defined positioning of the nozzle installation relative to the jet engine.

An electric module for an aircraft turbomachine includes an electric machine stator having an annular shape around an axis (A) and being configured to surround a rotor of the electric machine, and an annular support element of the stator. The support element includes an outer annular surface configured to be swept over by a gas stream (F) from the turbomachine with a view to conductively cooling the stator.