Wellington, FL, USA
N40KG
BEECH A36
The pilot departed for a planned 4-hour instrument flight rules, cross-country flight, and about 5 hours 13 minutes into the flight, the engine lost power. The pilot reported that he then landed the airplane on a wet roadway and lost directional control as the wheels hydroplaned on the wet surface. The airplane subsequently struck a sign and electrical power pole, resulting in substantial damage. The quantity of fuel onboard the airplane at the time of the accident could not be determined due to damage sustained to the airframe during the accident. Although the pilot advised an air traffic controller during the forced landing, "I believe I ran out of fuel," at least 12 usable gallons should have remained based on the amount of fuel the pilot reported the airplane had before departing on the flight and the total fuel use calculated by an onboard fuel flow indicator. A postaccident test run of the engine showed that it started normally and ran with no anomalies noted. Download of non-volatile memory from an engine monitoring device showed that the loss of engine power was immediately preceded by a rise in exhaust gas temperature and a rapid reduction in fuel flow, consistent with an interruption of fuel flow. The pilot did not report the position of the fuel selector before the loss of engine power, and its preaccident position could not be determined because the pilot had selected it to the off position before egressing the airplane after the accident.
On September 23, 2013, at 1237 eastern daylight time, a Beech A36, N40KG, was substantially damaged during a forced landing following a total loss of engine power near Wellington, Florida. The commercial pilot was not injured. Visual meteorological conditions prevailed and the airplane was operating on an instrument flight rules flight plan. The flight had originated from Washington Dulles International Airport (IAD), Dulles, Virginia, about 0730, and was destined for Boca Raton Airport (BCT), Boca Raton, Florida. The personal flight was conducted under the provisions of Title 14 Code of Federal Regulations Part 91. According to the pilot, he performed a preflight inspection and noted that a total of 74 (usable) gallons of fuel were onboard the airplane. He subsequently departed from IAD and climbed the airplane to a cruise altitude. While in cruise, the pilot referenced the airplane's GPS and noted that the expected total duration for the flight was about 4 hours. Later during the flight, the pilot referenced the installed engine monitor and fuel totalizer, and compared it with the GPS's estimate of the amount of time remaining for the flight. In the vicinity of Melbourne, Florida, the pilot was instructed by air traffic control to begin descending the airplane, and was given radar vectors around weather that was in the vicinity. During the descent, the pilot noted that the fuel totalizer predicted that the airplane had about 10 gallons of fuel remaining, with an estimated endurance of about 75 minutes. About 20 miles from the destination airport, and while flying at an altitude of about 4,000 feet, the engine experienced a total loss of power. The pilot attempted to restart the engine to no avail, and subsequently declared an emergency to air traffic control. After realizing that the airplane would not be able to reach the nearest airport, the pilot performed a forced landing to a highway below. During the landing, the airplane bounced, veered left, then right as it hydroplaned on the wet road surface. The airplane eventually came to rest after striking a utility pole, resulting in substantial damage to the airframe. After the landing, the pilot turned off the master switch, ignition and fuel selector and exited the airplane unharmed. Review of archived FAA Air Traffic Control (ATC) radio communication transcripts showed that the pilot was provided a handoff and checked in with an air traffic controller at Palm Beach Terminal Radar Approach Control facility at 1243, and reported he was approaching his assigned altitude to 4,000 feet. After being provided two radar vectors, the pilot advised ATC at 1244:49, "uh can you give me vectors to the nearest field uh I believe I ran out of fuel four zero kilo golf declaring an emergency at this time." The controller subsequently provided a vector toward Wellington Aero Club Airport (FD38), West Palm Beach, Florida, which was about 6 miles south of the flight's position at that time. The pilot finally advised the controller the he would not be able to reach the diversionary airport, and no further transmissions were received. A Federal Aviation Administration inspector performed a cursory examination of the airplane at the accident site. According to the inspector, the airplane's right wing struck a roadway sign and the left wing struck a power transmission pole, resulting in substantial damage to both wings. Damage to the wings precluded determining the quantity of fuel onboard the airplane at the time of the accident, though the inspector did note that there was no smell of fuel present at the accident site. After the airplane was recovered from the accident scene, the engine was separated from the airplane, placed on a test stand, and run under the supervision of the inspector. The engine started normally and was run to a maximum of 2,300 rpm, a limit imposed due to the test propeller installed on the engine. Oil and fuel pressure were observed to be within nominal limits, as was the loss of rpm noted when testing both magnetos. A JP Instruments EDM-700 engine monitoring device was recovered from the airplane and downloaded in the National Transportation Safety Board Vehicle Recorders Laboratory. The unit was in good condition and the data were extracted normally. The unit contained recorded data over 12 power cycles, recorded at a sample rate of once every 6 seconds. The recorded data spanned dates of July 30, 2013, through the accident flight on September 23, 2013, as recorded by the unit's internal clock. The entire accident flight recording was 5 hours and 31 minutes in duration. The duration during which the fuel flow was greater than 9 gallons per hour (gph) was 5 hours and 13 minutes. The parameters recorded were exhaust gas temperature (EGT), cylinder head temperature (CHT), voltage, fuel flow, and oil temperature. The calculated shock cooling rate, total fuel used, and maximum difference between EGT sensors were also recorded. No other parameters were recorded by the unit. The unit was configured such that 98 gallons was full fuel. At about 11:58 (4 hours and 40 minutes after the fuel flow first went above 9 gph), the engine parameters began to fluctuate slightly. At this time, the fuel used was 56 gallons. At 12:28:30, the CHTs and EGTs began a gradual decrease, coincident with a reduction in fuel flow from about 12 gph to 10 gph. At 12:29:48, the EGTs began to increase, peaking at 12:30:24. At 12:30:30, the fuel flow reduced to 0 gph for the remainder of the recording, and the CHTs and EGTs began to rapidly decrease. The recording ended at 12:37:48, 7 minutes and 48 seconds after the fuel flow first reduced to 0 gph. The final recorded total fuel used for the flight was 62 gallons.
A total loss of engine power due to an interruption in fuel flow, which was most likely due to fuel starvation. Contributing to the accident was the pilot’s failure to maintain control of the airplane while performing the subsequent forced landing to a wet roadway.
Source: NTSB Aviation Accident Database
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