WPR11FA125 · Beech 95-B55 (T42A)

During the initial climb, the landing gear warning horn sounded. The pilot diagnosed the problem and determined that the landing gear had retracted successfully and that the indication system was in error. He continued the flight with the horn intermittently sounding. During the descent phase, the pilot was given an unexpected direct route to the airport, and, as a result, he rushed through the descent checklist items. The pilot decided to perform a low pass over the arrival runway to confirm that the landing gear had extended. The pilot said that during the low pass he started to have difficulty controlling the airplane. An onboard engine monitoring system recorded a total loss of engine power to the right engine at that time. The pilot did not recognize that his difficulty in maintaining altitude and airplane control was a result of a loss of engine power to one engine; he subsequently lost control of the airplane, which collided with a storage facility in a nose-down inverted attitude. Witness reports, photographic evidence, and a postaccident examination revealed that the pilot did not retract the landing gear and flaps after the loss of power, as instructed in the airplane's operating instructions for a go-around with one engine inoperative.

The airplane's operating instructions recommend that the main fuel tanks be selected during descent and while landing. The pilot stated that he customarily uses the auxiliary fuel tanks during cruise flight and the main tanks while climbing and descending; however, both fuel selector valves were found in the auxiliary tank position at the accident site. The airplane's fuel tanks were serviced to capacity about 2.5 flight hours before the accident. Calculations of fuel consumption for the flights since the last fueling would have resulted in the use of a quantity of fuel that would have either been equal to or slightly exceeded the capacity of the auxiliary fuel tanks. Damage to the fuel system precluded an accurate assessment of the quantity and distribution of the remaining fuel onboard at the time of the accident. The engine monitoring system recorded a small rise in exhaust gas temperatures just before the loss of power; this rise is consistent with a lean fuel/air mixture, which would be present in a fuel starvation or exhaustion event. The postaccident examination did not reveal any anomalies with the airframe or engine that would have precluded normal operation.

The pilot's increased workload, due to the unexpected routing and possible problem with the landing gear, during the abbreviated final approach clearance and subsequent low pass could have resulted in a task overload, which resulted in his mismanagement of the fuel system during the landing phase.

Verbatim NTSB analysis and probable cause from the NTSB dataset