NTSB Factual Report

On February 20, 2003, about 1220 eastern standard time, a Cessna 402B, N554AE, registered to Johan-Pat, Inc., operated by Bel Air Transport, dba Airways Express, was ditched in the Atlantic Ocean approximately 10 nautical miles south-southwest of Marathon Airport, Marathon, Florida. Visual meteorological conditions prevailed at the time and an instrument flight rules flight plan was filed for the 14 CFR Part 91 positioning flight from Havana, Cuba, to the Miami International Airport, Miami, Florida. The airplane was substantially damaged and the airline transport-rated pilot, the sole occupant, sustained minor injuries. The flight originated about 1115, from Jose Marti International Airport, Havana, Cuba.

The pilot reported that the fuel tanks of the airplane were topped off the day before the accident at the Tamiami Airport, and he flew the airplane the next day (accident date) from there to the Miami International Airport where two passengers boarded the airplane for a 14 CFR Part 135 non-scheduled, international passenger flight to Havana, Cuba. The flight departed the Miami International Airport, proceeded to Havana, Cuba, landed, secured the airplane and cleared customs. No fuel was purchased in Cuba. Before departure he performed a preflight inspection of the airplane and noted both auxiliary fuel tanks were "more than half full" while both main fuel tanks were "half full." The flight departed between 1100 and 1130, and climbed to 8,000 feet. He reported the flight was normal when in Cuban airspace. The flight continued and when the flight arrived at TADPO, he, "...smelled a strong odor/fumes of AVGAS in the cabin." The engine instruments checked normal at that time and the flight continued. When the flight was approximately 10-12 miles from Marathon, "I smelled something burning in the cabin--like plastic material/paper or something." He reported the engine power indications were still normal at that time.

He declared "PAN" three times with the controller he was in contact with, and reported shortly thereafter the right engine began missing and surging. After a few seconds, "I observed what appeared to be fire on top of the right engine cowling near the louvers." He then immediately secured the right engine however the odor of fuel and fumes got worse to the point of irritating his eyes. He noted that the right engine manifold pressure and rpm indications were surging. He then declared an emergency with air traffic control, and started descending at blue line airspeed. The fumes/odor became worse and within 5 to 10 minutes of the right engine missing/sputtering, the left engine began, "...missing and sputtering." The rpm and manifold pressure indications of the left engine were also erratic. He "secured" the engine but reported the propeller did not completely feather; the propeller continued to windmill. He further reported that while descending the fumes/odor of aviation fuel became worse. At approximately 800 feet, he lost contact with the controller, and at 400 feet, he lowered full flaps and the landing gear. He slowed the airplane, tightened his seatbelt and shoulder harness, and intentionally stalled the airplane when it was 5 to 7 feet above the water. After touchdown on the water, he hit his head on the dashboard or windshield, and his chest and left shoulder contacted the control yoke. He released his restraint, evacuated the airplane from the passenger door, and took a life vest with him. He donned then inflated it, and sat on one of the wings but the airplane sank within seconds. He was rescued by a local fisherman 20 minutes later, and believed he briefly lost consciousness after being rescued.

The airplane was recovered and was examined by an FAA airworthiness inspector immediately following recovery. The inspector noted that there was no evidence of fire in either engine compartment area. Examination of the left propeller revealed it appeared to be in the feathered position, and the left turbocharger was seized. Fuel was noted at the left distributor valve, while water was noted at the servo fuel injector (servo). Examination of the right propeller revealed it appeared to be in the feathered position, and fuel was noted at the servo and distributor valve. A loose fuel injector line was noted at the No. 5 cylinder. The inspector did note that the inboard exhaust segment of the right engine from the header assembly was fractured.

The pilot first verbally reported to the National Transportation Safety Board (NTSB) on July 9, 2003, (4 months and 19 days after the accident), that his passport which was on the airplane at the time of the accident had burned pages. He also reported that information in writing, along with color and black and white copies of his passport showing the burned pages. He was repeatedly asked to provide a signed, dated statement which indicated where his passport was located in the airplane during the flight, and that the pages had not been burned before the flight. He did not comply with the request.

According to the director of maintenance for JV Air, the day before the accident the accident pilot brought the accident airplane to his facility stating that he smelled fuel in the cockpit during priming of the engines before starting. Troubleshooting revealed a pin hole in a fuel line for the boost pump; the fuel line was located in the cockpit area. The damaged line was removed, a new line fabricated and pressure tested outside the airplane, installed in the airplane and again pressure tested. The airplane was returned to service.

Examination of the airplane by the NTSB revealed no evidence of in-flight fire to any portion of the airplane including the right engine or engine compartment area, or upper right engine cowling which contains the louvers. Additionally, examination of the aluminum fuel line that had been manufactured and installed the day before the accident revealed no evidence of failure or fuel leakage. The fractured exhaust (right hand stack assembly) was retained for further examination by the NTSB Materials Laboratory. Additionally, both propellers, engines, and propeller governors were retained for further examination.

Examination of the fractured right hand stack assembly (P/N 9910301-5) was performed by the NTSB Materials Laboratory in Washington, D.C. The examination revealed the fracture surface did not contain fatigue or through wall thickness erosion.

Examination of the left engine revealed crankshaft, camshaft, and valve train continuity. The engine driven fuel pump drive coupling was not failed. The distributor valve screen was clean, and the oil filter did not contain any ferrous particles. The oil pump gears were in place with slight scoring of the housing noted. Bench testing of the left magneto revealed spark at all ignition towers. The contact gap was noted to be .018 inch (specification is .018 inch plus or minus .006 inch). No discrepancies were noted with the left magneto. Examination of the right magneto revealed the distributor block bushing was fractured. The electrode tang was displaced on the distributor gear shaft. No damage was noted to the distributor block by contact with the electrode. No evidence of overheat or lack of lubrication was noted to the distributor gear shaft, and no teeth of the distributor gear were damaged. Carbon tracking was noted in the area of the broken distributor block. The coil from the right magneto checked within specified limits. Bench testing of the condensor from the right magneto revealed evidence of an internal short. No determination was made when the distributor block fractured. Bench testing of the left propeller governor revealed the high rpm, dump pressure, and relief valve pressure were greater than specified limits. Examination of the left propeller revealed no evidence of preimpact failure or malfunction. All propeller blades were in the feathered position and within established limits. Propeller blade No. 2 exhibited slight bend damage.

Examination of the right engine revealed crankshaft, camshaft, and valve train continuity. The engine driven fuel pump drive coupling was not failed; no unusual wear was noted on the coupling. Impact damage was noted to the inboard exhaust pipe aft of the No. 2 cylinder at the 7 and 9 o'clock positions. The oil pump gears were in place with slight scoring noted in the housing. The oil filter element did not contain any ferrous particles, and the distributor valve screen was clean. All fuel injector nozzles were clear with the exception of the No. 6 cylinder. No erosion damage was noted to the sides of the No. 6 cylinder piston. Bench testing of the left and right magnetos revealed both sparked at all ignition towers. The retard points broke during examination of the magneto. Examination of the right propeller governor revealed impact damage to the rpm stop collar. Bench testing of the governor revealed the high rpm was set within limits, the dump pressure, and relief valve pressure were greater than specified limits. Examination of the right propeller revealed no evidence of preimpact failure or malfunction. All the propeller blades were in the feathered position; two of the three propeller blades exhibited impact damage. Examination of the blade that did not have any damage indicated it was within established feather limit.

Review of the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual revealed that with respect to ditching procedures, the landing gear is listed to be "up", which is contrary to what the pilot performed in that he reported lowering the landing gear when the flight was at 400 feet.

The airplane was released to Steven M. Homenda, Regional Manager of CTC Services Aviation (LAD, Inc.), on November 5, 2003. All retained components were released to Steven M. Homenda on May 26, 2004.

NTSB Probable Cause

The loss of engine power to both engines for undetermined reasons.