ASN Wikibase Occurrence # 370243
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.
| Date: | Thursday 16 August 2007 |
| Time: | 15:13 LT |
| Type: |  Bell 407 |
| Owner/operator: | Phi, Inc. |
| Registration: | N433PH |
| MSN: | 53679 |
| Year of manufacture: | 2005 |
| Total airframe hrs: | 2215 hours |
| Engine model: | Rolls-Royce C-47-B |
| Fatalities: | Fatalities: 0 / Occupants: 2 |
| Aircraft damage: | None |
| Category: | Serious incident |
| Location: | Gulf of Mexico, -
 United States of America
|
| Phase: | En route |
| Nature: | Unknown |
| Departure airport: | E Cameron 109 |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
Shortly after departing in a single-engine helicopter from a platform in the Gulf of Mexico, the commercial pilot heard a "high pitched winding noise" and a "pop" followed by a loss of engine power . The pilot landed the helicopter safely on the water with the floats fully inflated. Shortly thereafter, a large wave impacted the helicopter and broke out the right windshield and rolled the helicopter inverted. The pilot and the passenger were able to exit the helicopter and deploy one of the on-board life rafts. They were later rescued by a local boat and the USCG. Examination of the engine revealed the power turbine (PT) outer shaft was intact; however, there were two spiral fractures observed on the shaft. One spiral fracture was approximately 3-inches-long and originated between a crack within one curvic tooth and the mid-shaft. At the mid-shaft location, as the shaft wall thickens, the spiral direction changed 90 degrees and continued for approximately another half-inch. The second spiral fracture was approximately 180 degrees from the first and was approximately one half-inch in length with one end starting at the root of a curvic tooth. The loaded faces of the curvic-coupling teeth were galled. The fourth stage turbine connector nut was in its proper location and appeared to be undamaged. The deformable lock feature was still engaged with the nut. The easy removal of the nut from the shaft was hampered by the presence of a piece of curvic tooth fragment that was wedged between the nut and the shaft. Once the tooth fragment was removed, the nut rotated freely and was removed. The ring described by the forward face of the shaft, exhibited areas of polishing consistent with contact against the ring described by the aft face of the pinion gear. According to the Rolls-Royce metallurgical examination report, the fracture surfaces exhibited evidence of fatigue. The manufacturer also stated that there have been 16 other instances where the power turbine outer shaft had cracked since 1990; however, none of these resulted in an engine shut down. The only damage noted in these cases was fretting on the mating wheel. Each of the cracks initiated in the curvic coupling, and fretting was found at the fracture origin. The fretting was attributed to a loss of clamp load either from inadequate torque on the PT nut, or raised metal on the curvics that prevented proper seating. As a result of these 16 events, and prior to the PHI accident, Rolls Royce implemented several mitigating actions to prevent a future occurrence. These included changes to the assembly process, enhanced instructions in the overhaul manual on better handling practices to better protect the curvic couplings. The source of the fractures could not be determined.
Probable Cause: Fatigue failure of the power turbine outer shaft for undetermined reasons.
Accident investigation:
 |
|
Sources:
NTSB DFW07IA184
Location
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 25-Mar-2024 08:36 | ASN Update Bot | Added |
Corrections or additions? ... Edit this accident description
The Aviation Safety Network is an exclusive service provided by:
Quick Links:
| ASN Home | Send Correction / Feedback |
| FSF Home | Disclaimer | Copyright |
| Contact Us | Privacy Policy |
| Press / Media |
CONNECT WITH US:
©2024 Flight Safety Foundation