HISTORY OF FLIGHTOn December 22, 2022, about 1518 Pacific standard time, a Cessna 150, N7032X, sustained substantial damage when it was involved in an accident near Santa Monica Municipal Airport (SMO), Santa Monica, California. The pilot sustained minor injuries, and the passenger was fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. The pilot reported that the accident flight was to be local, following a route northwest along the Pacific Ocean coastline with a pilot-rated passenger. The pilot reported that after topping off the airplane’s fuel tanks, the airplane seemed “sluggish” during the taxi to runway 21. The pilot canceled his takeoff request, taxied to his hangar, and shut down the engine to troubleshoot the anomaly. Initially he believed that it may have been due to low tire pressure, so he verified the tire pressure and started the engine. While taxiing from the hangar to the runway, a magneto check and carburetor heat check were within normal limits. The pilot contacted ground control, taxied to the runway, and departed runway 21 to the southwest. During the initial climb, about 575 ft agl, the pilot intercepted the coast near Ocean View Park and turned to the right to follow the coastline northwest (Figure 1). ADS-B data indicated that four minutes into the flight, while over Sunset Beach, the airplane had climbed to 1,025 ft agl with a consistent airspeed of about 70 mph. The pilot reported that he ensured that the carburetor heat was off, the mixture was rich, the throttle was in the maximum position, and that the ignition switch was in the Both position. Subsequently, he heard what he described as a “bang” and made a left 180° turn. The pilot contacted the SMO tower controller and attempted to return to SMO. However, the airplane’s descent rate increased, and the pilot initiated a forced landing to the shoreline about 2,200 ft south of the Santa Monica Pier. The airplane touched down heading south in the shallow water of the shoreline and nosed over.

Figure 1: View of the accident airplane’s ADS-B flight path AIRCRAFT INFORMATIONExamination of the aircraft maintenance logbooks revealed that the annual inspection was completed four months before the accident. At the time of the annual inspection, the engine time since overhaul was 1,737.0 hours and the engine total time was 3,344.0 hours. The engine logbook indicated that an overhaul was completed August 28, 1970, and a top overhaul was completed in 1972. After the annual inspection, there were no additional logbook entries. The engine manufacturer recommended time between overhaul is 1,800 hours or 12 years. AIRPORT INFORMATIONExamination of the aircraft maintenance logbooks revealed that the annual inspection was completed four months before the accident. At the time of the annual inspection, the engine time since overhaul was 1,737.0 hours and the engine total time was 3,344.0 hours. The engine logbook indicated that an overhaul was completed August 28, 1970, and a top overhaul was completed in 1972. After the annual inspection, there were no additional logbook entries. The engine manufacturer recommended time between overhaul is 1,800 hours or 12 years. WRECKAGE AND IMPACT INFORMATIONExamination of the accident site revealed evidence consistent with the airplane heading southeast when the main landing gear contacted water along the shoreline and subsequently nosed over. The airplane came to rest with the nose of the airplane oriented toward the northwest, the right wing oriented west toward the ocean, and the left wing oriented east toward the shore. The upper fuselage and both wings were submerged in water along the shoreline. The airplane was subsequently pulled to shore by first responders to prevent the current from pulling the airplane further into the ocean. The engine mounts sustained substantial damage. Examination of the recovered wreckage revealed that no holes in the engine crankcase. All accessories remained attached to the accessory case and revealed no impact damage. None of the rocker covers revealed gross deformations. The air induction housing sustained impact damage, and the exhaust assemblies sustained minor damage. Initially, the propeller could not be turned by hand, and exhibited binding and restriction when rotated in the opposite direction; subsequent binding remained when rotated in the direction of rotation. The propeller spinner was crushed and remained attached to the propeller flange by only two of the six hub bolts. About 5 quarts of oil were extracted from the oil sump. The No. 1 piston was seized to the cylinder and the piston skirt had damage to the upper and lower sections in alignment with piston rod movement. The No.1 piston rod and bearing were separated from the crankshaft and the connecting rod endcap and bearing remained in the crankcase. The connecting rod bolts were stretched, and the nuts remained attached to each bolt, but the bolt heads were separated and not present. The oil sump was removed and contained residual oil and metallic fragments. The crankcase halves were disassembled, and the crankshaft main bearings were intact and showed normal operational wear. The crankcase halves showed no signs of fretting or main bearing shift in the bearing saddle areas. The crankcase oil galley plugs were removed, and the oil galleys were free from obstruction. Internal mechanical damage was observed at the Nos. 1 and 2 cylinder bays. The Nos. 2, 3, and 4 connecting rod ends were removed to observe the condition of the rod bearings. The No. 2 connecting rod bearings revealed thermal discoloration and metal deformation consistent with oil starvation. The No. 3 cylinder connecting rod bearings displayed thermal discoloration and metal deformation, with one bearing seized to the connecting rod. The No. 4 cylinder connecting rod bearings revealed only thermal discoloration. The oil filter was removed and cut open; the filter screen was unremarkable. The oil pump was removed and disassembled revealing no anomalies to the gear or the internal pump housing. The oil filter adapter was present, secure, and revealed no anomalies. The oil filter adapter housing was disassembled, and the fiber gasket was intact with no visible damage. The oil filter adapter housing components were undamaged including the copper crush gasket located on the spool. The engine sump oil pickup tube appeared unimpeded.