ERA17LA098

Factual narrative

On January 30, 2017, at 1404 eastern standard time, a Cessna P210N, N4796P, sustained substantial damage when it made a forced landing about 1-mile north of the Schuykill County Airport (ZER), Pottsville, Pennsylvania, after a total loss of engine power. The private pilot/registered owner and the passenger sustained minor injuries. A visual flight rules flight plan was filed for the flight that originated at the Allentown Queen City Municipal Airport (XLL), Allentown, Pennsylvania, about 1330, destined for the Erie-Ottawa International Airport (PCW), Port Clinton, Ohio. Visual meteorological conditions prevailed for the personal flight conducted under the provisions of 14 Code of Federal Regulations Part 91. The pilot stated that the day before the accident he topped the airplane off with fuel (for 90 gallons total), completed a preflight inspection, started the engine, and taxied a short distance to make sure the airplane was operating okay. Everything was normal and he parked the airplane outside overnight. The following day, he arrived at the airport but did not do a preflight inspection or sump the fuel tanks. He started the engine and departed. The pilot climbed to 12,500 ft mean sea level (msl) and leveled off. When he reduced engine rpm for cruise flight, the engine "just shut off immediately." There was no warning or any indication of an engine problem prior to it shutting down and the propeller continued to windmill. The pilot attempted to re-start the engine for 3-4 minutes to no avail. He declared an emergency and proceeded to ZER, the nearest airport, but landed off field about 1 mile north of the airport. The airplane collided with trees and came to rest upright on an embankment. The left and right wings sustained substantial damage and the engine had separated from the firewall. The tail section also sustained structural damage. A postaccident examination of the airplane revealed that left and right-wing fuel tanks were breached and the fuel selector rotated freely to each detent. The fuel sump drains were removed, and both were heavily corroded due to exposure to moisture. The engine sustained impact damage but the cylinders, components, and accessories remained attached to the engine. The oil pan was damaged, and the engine could not be test run. The engine was manually rotated, and compression and valve train continuity were established on each cylinder. Engine timing was also confirmed. Both magnetos were placed on a test-bench and produced spark to their respective leads. The spark plugs were removed and compared to the Champion Check-A-Plug chart. Each plug exhibited normal operating signatures. The fuel pump was removed, and the coupling was intact, but the pump was locked up and could not be rotated. The pump was disassembled and the internal components (including the housing bolts and screws) were corroded due to exposure with moisture. The fuel manifold was removed and placed on a test-bench. The flow check was normal. The manifold's fuel inlet screen was removed, and a small amount of debris was observed. The fuel metering unit sustained impact damage and the mixture control was bent and the fuel inlet AN fitting was broken. The screen was removed and absent of debris. The unit was disassembled, and the mixture cam, throttle cam, and the metering plug exhibited a large amount of corrosion consistent with exposure to moisture. The airplane had been sitting outside exposed to snow before and after it was recovered. Since the fuel system had been breached, it could not be determined when the corrosion occurred. The pilot confirmed he had no previous issues with water in the airplane's fuel system. The oil sump was removed, and some residual oil remained. No metallic material was observed. The oil pick-up tube and screen were absent of debris. The oil pump was disassembled, and no anomalies were noted. The oil filter was opened, and the element was absent of debris. No mechanical anomalies were noted that would have precluded normal operation of the engine. The last annual inspection for the airplane and engine were completed on June 8, 2016, at a tachometer time of 3,663 hours. The engine was installed new in 2010, and had accrued about 644.6 hours. The pilot held a private pilot certificate with a rating for airplane single-engine land. His last Federal Aviation Administration (FAA) third-class medical was issued on October 9, 2015. The pilot reported a total of 3,000 flight hours and 1,500 hours in the same make/model as the accident airplane. A weather observation taken about 19 miles southwest of the accident site, at Muir Army Airfield (MUI), Fort Indiantown Gap (Annville), Pennsylvania, at 1358, reported wind from 280 degrees at 7 knots, with variable wind between 240 and 310 degrees, visibility 10 statute miles, few clouds at 7,500 feet, temperature -1-degree C, dew point -4 degrees C, and an altimeter setting of 29.81 inches of mercury. The private pilot reported that he did not perform a preflight inspection, including sumping the fuel tanks, before departing for a cross-country flight with full fuel tanks. When the airplane reached 12,500 ft mean sea level and the pilot reduced engine rpm for cruise flight, the engine suddenly, and without warning, stopped producing power. The pilot tried several times to restart the engine to no avail and subsequently conducted a forced landing, during which the airplane collided with trees. The airplane sustained substantial damage to the fuselage, both wings, and the tail section. Postaccident examination of the airplane revealed that both wing fuel tanks were breached and that the fuel strainer drains for each wing were corroded due to exposure to moisture. Similar corrosion was also observed in the engine's fuel pump and fuel metering unit. The airplane had been sitting outside exposed to snow before and after it was recovered from the accident site. Given that the fuel system had been breached, it could not be determined when the corrosion occurred or whether the pilot's failure to sump the fuel tanks contributed to the loss of power. Examinations of the airframe and engine revealed no evidence of any preimpact mechanical malfunctions or failures that would have precluded normal operation, and the reason for the loss of engine power could not be determined. Source: NTSB Aviation Accident Database Retrieved: 2026-02-12

NTSB Findings

FAA avdata. C = Cause, F = Factor.

• C Not determined-Not determined-(general)-(general)-Unknown/Not determined - C
• — Environmental issues-Physical environment-Object/animal/substance-Tree(s)-Contributed to outcome
• — Personnel issues-Task performance-Inspection-Preflight inspection-Pilot