Piper PA-28RT-201T N2148J accident near Morgan, Texas

Probable cause

A partial loss of engine power due to a corrosion-related fatigue crack of the No. 3 cylinder barrel.

NTSB analysis

While in cruise flight, the pilot observed the manifold pressure drop, followed by a loud rattling engine noise with strong vibrations. The pilot shut down the engine and diverted toward a nearby airport. The pilot reported that he thought the airplane was too high on the downwind leg; however, after he turned the airplane onto the final leg, he realized that the headwind would prevent him from making it to the runway. The pilot performed a forced landing into rough terrain short of the runway, which resulted in substantial damage to the right wing.

Postaccident examination of the No. 3 cylinder revealed the cylinder barrel was fractured between the cooling fins and the threaded section used for mounting the cylinder head. A metallurgical examination revealed a fatigue crack that originated at a corrosion pit on the outer diameter surface of the cylinder barrel.

The inboard-facing side of the first cylinder cooling fin was tinted black for a 180° arc, with the center of the arc in line with the fatigue crack. Manufacturer guidance includes inspection of cylinder fins for any signs of oil or soot leakage that might indicate a cylinder or head-to-barrel junction structural integrity breach. The engine was operated about 30 hours since the last annual inspection.

Text from the NTSB. Open the NTSB docket for CEN22LA227 for the full record.