Inspection assembly, system, and method for a gas turbine engine

An inspection method for a gas turbine engine having an engine core, a casing, and a static aerodynamic fairing, the inspection method comprising:

• providing an inspection assembly comprising:
• an elongate member extending along a longitudinal axis from a first end to a second end;
• a coupler disposed proximal to the first end of the elongate member;
• and
• a sensor member pivotally coupled to the elongate member at the second end, the sensor member comprising at least one sensor configured to sense one or more parameters of the gas turbine engine;
• inserting the elongate member at least partially through the static aerodynamic fairing of the gas turbine engine into a portion of the engine core radially inboard of the static aerodynamic fairing;
• engaging the sensor member with a guidance surface of a guidance member that forms part of or is configured to be fixedly coupled to a static structure located within the engine core of the gas turbine engine, wherein the guidance surface is inclined to the longitudinal axis of the elongate member by a guidance angle, wherein, in an insertion position, the sensor member is inclined by a first inclination angle with respect to the longitudinal axis, wherein, in a sensing position, the sensor member is inclined by a second inclination angle with respect to the longitudinal axis, and wherein the second inclination angle is greater than the first inclination angle;
• pivoting the sensor member relative to the elongate member from the insertion position to the sensing position while the elongate member is being inserted into the engine core;
• locking, via a locking mechanism, the sensor member in the sensing position;
• and
• removably coupling, via the coupler, the elongate member to the casing of the gas turbine engine.

An inspection assembly for a gas turbine engine having an engine core, a casing, and a static aerodynamic fairing, the inspection assembly comprising:

• an elongate member extending along a longitudinal axis from a first end to a second end, wherein the elongate member is configured to be at least partially inserted through the static aerodynamic fairing of the gas turbine engine into a portion of the engine core radially inboard of the static aerodynamic fairing;
• a coupler disposed proximal to the first end of the elongate member, wherein the coupler is configured to removably couple the elongate member to the casing of the gas turbine engine;
• and
• a sensor member pivotally coupled to the elongate member at the second end, the sensor member comprising at least one sensor configured to sense one or more parameters of the gas turbine engine, wherein the sensor member is pivotable relative to the elongate member between an insertion position and a sensing position, wherein, in the insertion position, the sensor member is inclined by a first inclination angle with respect to the longitudinal axis, wherein, in the sensing position, the sensor member is inclined by a second inclination angle with respect to the longitudinal axis, and wherein the second inclination angle is greater than the first inclination angle;
• wherein, upon insertion of the elongate member into the engine core, the sensor member is configured to engage with a guidance surface of a guidance member that forms part of or is configured to be fixedly coupled to a static structure located within the engine core of the gas turbine engine, wherein, upon engagement with the guidance surface, the sensor member is configured to pivot relative to the elongate member from the insertion position to the sensing position while the elongate member is being inserted into the engine core, and wherein, upon pivotal movement of the sensor member to the sensing position, the sensor member is configured to be locked in the sensing position.