Abstract: An assembly for an aircraft propulsion system includes a case assembly, at least one seal, a first pressure sensor, and a computing system. The case assembly forms a cavity. The at least one seal is disposed on the case assembly. The at least one seal is configured to seal the cavity. The first pressure sensor is in fluid communication with the cavity. The first pressure sensor is configured to measure a first pressure within the cavity. The computing system is in signal communication with the first pressure sensor. The computing system includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to compare the first pressure to a pressure threshold value to identify a wear condition of the at least one seal.

Abstract: A tool for shaping an abradable liner of a turbofan engine is disclosed. The turbofan engine includes a shaft to support a fan rotatable about a rotation axis. The abradable liner is configured to surround the fan and has an axial length in the direction of the rotation axis. The tool includes a support configured to be mounted to the shaft and rotatable about the rotation axis. The shaping head is mounted to the support for rotation about the rotation axis and configured to shape the abradable liner by removing material from the abradable liner. A radial position of the shaping head is adjustable relative to the rotation axis. The shaping head may sized to extend substantially across the axial length of the abradable liner.