ASN Wikibase Occurrence # 298772
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: | Sunday 2 July 2000 |
| Time: | 10:50 LT |
| Type: |  Hughes 369D |
| Owner/operator: | Florida Department of Natural Resoures |
| Registration: | N88MP |
| MSN: | 911027D |
| Year of manufacture: | 1981 |
| Total airframe hrs: | 4556 hours |
| Engine model: | Allison 250-C20B |
| Fatalities: | Fatalities: 0 / Occupants: 1 |
| Aircraft damage: | Substantial |
| Category: | Accident |
| Location: | DESTIN, Florida -
 United States of America
|
| Phase: | Unknown |
| Nature: | Unknown |
| Departure airport: | PANAMA CITY , FL (KPFN) |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
The pilot said he had been flying the helicopter at an altitude of about 500 feet, 100 knots indicated airspeed, and 65 to 70 pounds per square inch torque, when he felt a high frequency vibration through the antitorque pedals. He said the vibration dissipated but soon began again, and became excessive with 'strong' forces in the pedals. The forces were soon followed by a loud 'bang' and the aircraft yawed violently to the right, and the nose pitched down. He said the antitorque pedals had no effect, so he lowered the collective control and applied aft cyclic control input to the stop the yaw, and level the aircraft. He said the yaw rate slowed, but did not stop, and at about 70 to 80 degrees of right yaw, he reduced the throttle in an attempt to further reduce/control the yaw condition, and the aircraft yaw stopped. He was then able to execute an autorotative landing to an open field. The on scene examination of the aircraft showed that the stabilizer, as well as an 18-inch section of the hollow portion of the tail had separated from the aircraft in flight. The 90-degree gearbox also partially separated from the aircraft, and was only held by one remaining bolt, and there were contact marks and paint transfer signatures, consistent with those from multiple tail rotor blade strikes at the fracture point. The aft 6 inches of the tailboom with attach points, tail rotor gearbox, and tail rotor assembly were retained for metallurgical examination. The examination revealed that the fractured tail rotor gearbox studs were fatigue failures. In addition, both elastomer bearings in the tail rotor drive fork were examined, and were found to have failed due to fatigue.
Probable Cause: improper maintenance inspection of the tail rotor by maintenance personnel and improper preflight inspection of the tail rotor by the pilot, which resulted in worn elastomeric bearings being continued in service, resulting in failure of the tail rotor assembly, and damage to the helicopter during a hard landing.
Accident investigation:
 |
|
Sources:
NTSB MIA00TA200
History of this aircraft
Other occurrences involving this aircraft
| 7 November 2017 | N138WH | Winco, Inc. | 2 | Calcasieu Parish north of Sulphur, LA | |
non |
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 15-Oct-2022 22:30 | 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