Wear resistant sleeve for composite cylinder

A door and hold open rod assembly of an aircraft, comprising:

• the door;
• and
• a hold open rod assembly secured to the door, the hold open rod assembly configured to support the door in an opened position when the hold open rod is deployed, the hold open rod assembly, including:
• a tubular rod body formed from a composite material;
• a localized sleeve installed to the rod body, the sleeve secured to the rod body by a shrink fit operation including the application of heat to the sleeve material;
• and
• a bushing disposed radially between the rod body and the sleeve, the bushing configured to absorb thermal energy of the application of heat.

An engine assembly of an aircraft, comprising:

• an engine body;
• a cowling configured to at least partially enclose the engine body, the cowling movable between a closed position and an opened position;
• and
• a hold open rod assembly secured to the cowling, the hold open rod assembly configured to support the cowling in an opened position when the hold open rod is deployed, the hold open rod assembly, including:
• a tubular rod body formed from a composite material;
• a localized sleeve installed to the rod body, the sleeve secured to the rod body by a shrink fit operation including the application of heat to the sleeve material;
• and
• a bushing disposed radially between the rod body and the sleeve, the bushing configured to absorb thermal energy of the application of heat.