# Accident 20050724017949A: Hynes B2B, Plymouth, MA, July 24, 2005

- Type: FAA accident report (Accident/Incident Data System), as reported
- Date: July 24, 2005, 11:00 local time
- Place: Plymouth, MA
- Airport: Plymouth Municipal
- Damage: Destroyed
- Phase of flight: Hovering
- Operating rules: General operating rules (Part 91)
- Location: 41.9147° N, 70.7367° W: From the FAA
- Nearby events: https://openairdocs.org/map.md?lat=41.9147&lon=-70.7367&mi=10
- Aircraft: N9018Y, a cancelled registration (https://openairdocs.org/deregistered/N9018Y-2013-05-13) (OpenAirDocs)
- Registry model: Brantly B-2B (registry code 1440506, https://openairdocs.org/model/brantly-b-2b) (OpenAirDocs)
- Registry engine: Lycoming O&VO-360 series (registry code 41514, https://openairdocs.org/engine/lycoming-o-vo-360-series) (OpenAirDocs)
- Reported make and model: HYNES B2B
- People aboard: 1
- Fatal injuries: 0
- Pilot flight hours: 4,000 total, 91 in this make and model, 30 in the last 90 days
- NTSB investigation: [NTSB IAD05LA107](https://openairdocs.org/ntsb/IAD05LA107) (OpenAirDocs)
- FAA source: FAA Aviation Safety Information Portal (https://asip.faa.gov/)
- Page: https://openairdocs.org/incident/20050724017949A

## Narrative

As the FAA filed it, in capitals; the FAA replaces private details with ^PRIVACY DATA OMITTED^.

(-23) PILOT REPORTED THAT WHILE IN HOVER AT TWO FEET AGL, THE HELICOPTER BEGAN TO ROTATE TO THE RIGHT AND TAIL ROTOR INPUT WAS INEFFECTIVE. AS THE SPEED OF THE ROTATION INCREASED, HE ATTEMPTED TO LAND. THE HELICOPTER CAME TO REST ON ITS LEFT SIDE APPROXIMATELY 250 FEET FROM RUNWAY 15 AND 200 FEET FROM RUNWAY 24. A GROUND SCAR 4 FEET TO THE RIGHT AND 6 FEET FORWARD OF THE NOSE IS 6 INCHES DEEP. A SECOND GROUND SCAR WAS NOTED 21 FEET AFT OF AND 22 FEET FROM WHERE THE TAIL BOOM CAME TO REST. PAINT CHIPS WERE FOUND AT THIS LOCATION CONSISTENT WITH PAINT ON THE TAIL BOOM. THE TAIL FIN AND TAIL ROTOR ASSEMBLY SEPARATED FROM THE TAIL BOOM AT THE BASE OF THE VERTICAL FIN. THE TAIL FIN ROTATED COUNTERCLOCKWISE AROUND THE TAIL ROTOR DRIVE SHAFT HOUSING AT IMPACT. GROUND SCARS FROM THE MAIN ROTOR WERE EVIDENT AND ALL THREE MAIN ROTOR BLADES WERE LIBERATED. SIGNIFICANT STRUCTURAL DAMAGE WAS EVIDENT TO THE FUSELAGE. SUBSEQUENT INSPECTION AT DISASSEMBLY REVEALED A FAILURE OF THE TAIL ROTOR DRIVE SHAFT AT THE INPUT TO THE LOWER 90 DEGREE GEARBOX ON THE ENGINE INPUT SIDE. THERE WAS EVIDENCE OF OIL SPRAY ON THE LEFT SIDE OF THE TAIL ROTOR, FUSELAGE, AND COCKPIT CANOPY.

## The NTSB's investigation of this event (1)

From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date, checked against the reported serial number, make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model.

- [NTSB IAD05LA107](https://openairdocs.org/ntsb/IAD05LA107), Jul 24, 2005: Brantly Helicopter B-2B (N9018Y), Plymouth, MA, substantial damage. Probable cause: Fatigue failure of the intermediate tailrotor driveshaft, which resulted in a loss of directional control at a hover.

From the FAA Accident/Incident Data System. Reports are matched to registry aircraft by N-number and event date, checked against the reported make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. For accidents, the NTSB's own investigation is the fuller record.

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