No fatalities

Fuel Exhaustion Leads to Ditching After Dual Engine Power Loss (C-FBCR)

Shelter Cove, United States of AmericaTakeoff (climb)

On March 18, 1999, a Rockwell Aero Commander 500 (registration C-FBCR) operated by Thomas M. Fisher was involved in an aviation accident near Shelter Cove, United States of America during takeoff. No fatalities were reported. Investigators recorded the probable cause as: Fuel exhaustion due to the pilot's failure to ensure that an adequate fuel supply was onboard. A contributing factor was the lack of suitable terrain for the forced landing. This summary draws on records from the Bureau of Aircraft Accidents Archives (B3A).

Sourcesthe Bureau of Aircraft Accidents Archives (B3A)Primary reportUpdated 2026-06-11Data APIEditorial standards
Aircraft registered C-FBCR
Aircraft registered C-FBCR. Photo: RAF-YYC from Calgary, Canada / CC BY-SA 2.0, via Wikimedia Commons

A pilot reported fuel exhaustion after both engines lost power during climb, leading to a ditching offshore. Investigation found no mechanical malfunction but noted pilot's failure to ensure adequate fuel.

Incident Overview

A pilot departing on a short flight reported that both engines lost power simultaneously during initial climb at approximately 400 feet above the ocean. The pilot stated that a brief surge of power occurred when the wings were rocked, but all engine power was then completely lost. The pilot turned toward the shoreline, reduced airspeed, and ditched the airplane about 0.25 miles offshore. Overnight tide and wave action subsequently beached most of the airplane.

Pilot's Account

Prior to departure, the pilot believed the airplane contained between 30 and 40 gallons of fuel, which he considered adequate for a 15-minute flight to another airport where he intended to purchase additional fuel. The fuel gauge registered 40 gallons at departure. The pilot did not report experiencing any mechanical malfunctions during the flight.

Examination and Findings

An FAA coordinator examined recovered portions of the airframe and engines. The examination found no physical evidence of any mechanical malfunction with the components that were examined. However, due to airframe damage sustained during immersion in salt water and subsequent destruction to components, the Safety Board was unable to document the integrity of the fuel quantity indicator system.

Official Findings

The probable cause of the incident was determined to be fuel exhaustion resulting from the pilot's failure to ensure that an adequate fuel supply was onboard. A contributing factor was the lack of suitable terrain for the forced landing.