ASN logo
ASN Wikibase Occurrence # 174525
Last updated: 19 June 2020
This information is added by users of ASN. Neither ASN nor the Flight Safety Foundation are responsible for the completeness or correctness of this information. If you feel this information is incomplete or incorrect, you can submit corrected information.

Type:Silhouette image of generic B06 model; specific model in this crash may look slightly different
Bell 206-L4
Owner/operator:Rotorcraft Leasing Co., L.L.C.
Registration: N207RT
C/n / msn: 52207
Fatalities:Fatalities: 0 / Occupants: 6
Other fatalities:0
Aircraft damage: Substantial
Location:Patterson, LA -   United States of America
Phase: En route
Departure airport:SP-10, GM (NONE)
Destination airport:Patterson, LA (PTN)
Investigating agency: NTSB
The 10,300-hour pilot reported that while in cruise flight at an altitude of 500 feet and 110 knots, he heard a "loud" bang followed by "severe" and constant vibration. He stated that the pedal inputs "seemed" to have no effect in correcting the yawing of the aircraft. It was apparent to the pilot that continued flight would be impossible, and he elected to perform a forced landing. The pilot began a 180-degree autorotation to the left. While in the turn, the pilot made a "mayday" call, and reduced the throttle, which had no effect. Once the pilot closed the throttle, the "pounding and vibration" lessened. After the aircraft rolled out, and was level at 100 to 150 feet, the pilot realized they were going to hit the levee of the pond. He pulled a little collective to clear the levee, performed a cyclic turn to the right, and cushioned the landing. When the helicopter landed, the main rotor blade contacted the tailboom. Examination of the wreckage by the operator and a FAA inspector, who responded to the accident site, revealed structural damage to the tailboom. Strike marks on the tailboom, corresponding to the main rotor blade top path plane, were found adjacent to the #7 tail rotor drive shaft segment. Additionally, the left horizontal stabilizer winglet device was not found. Further examination revealed a ten-inch crack in the fixture securing the left winglet to the horizontal stabilizer. The right winglet, which was found, also had a pre-existing crack in the same area. The cracks were not visible during a visual inspection, and the crack area is under a line of structural adhesive used during manufacture of the horizontal stabilizer, and can only be seen when the winglet is removed. According to the operator, the 10-inch crack that was discovered on the left winglet appeared to have existed for some time. The operator stated that the winglet could have separated from helicopter in-flight, and struck the tail rotor, resulting in the "loud bang" that was heard by the pilot, and subsequent loss of directional control.Other than the winglet, examination of the helicopter, and its drive and flight control components did not reveal any pre-existing anomalies that could have contributed to the accident.
Probable Cause: The in-flight separation of the helicopter's left winglet due to pre-existing cracks resulting in the winglet striking the tail rotor in-flight, and subsequent loss of directional control.



Revision history:

14-Mar-2015 18:19 Noro Added
21-Dec-2016 19:28 ASN Update Bot Updated [Time, Damage, Category, Investigating agency]
07-Dec-2017 17:34 ASN Update Bot Updated [Operator, Other fatalities, Departure airport, Destination airport, Source, Narrative]

Corrections or additions? ... Edit this accident description