ASN Wikibase Occurrence # 309988
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: | Wednesday 17 July 2013 |
| Time: | 12:00 LT |
| Type: |  Piper PA-34 |
| Owner/operator: | Phoenix East Aviation, LLC |
| Registration: | N767PE |
| MSN: | 34-7350042 |
| Year of manufacture: | 1972 |
| Total airframe hrs: | 11575 hours |
| Engine model: | Lycoming I0360 SER |
| Fatalities: | Fatalities: 0 / Occupants: 2 |
| Aircraft damage: | None |
| Category: | Serious incident |
| Location: | Palm Coast, Florida -
 United States of America
|
| Phase: | Standing |
| Nature: | Training |
| Departure airport: | Daytona Beach International Airport, FL (DAB/KDAB) |
| Daytona Beach International Airport, FL (DAB/KDAB) | |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
The pilot receiving instruction was recovering the airplane from a demonstrated minimum control airspeed condition. According to the flight instructor, the airplane was initially about 5,000 ft in a "clean" configuration. Both pilots then felt two "kicks" in the rudder system, which they then verbally confirmed to each other did not result from either of them making inputs. The pilot receiving instruction then heard a "snap," and the rudder pedals began to "pump" full deflection right and left. Subsequently, the flight instructor took control of the airplane and found that neither applying full rudder nor using both feet on the rudder neutralized the deflections. Even with both pilots trying to neutralize the rudders, the deflections continued. The flight instructor subsequently diverted the airplane to a nearby airport and landed it uneventfully.
During the on-scene examination, the rudder trim tab control rod was found fractured near the trim tab end. The control rod was replaced, and, during subsequent flights, no further rudder anomalies occurred. Metallurgical examination of the rod revealed that it had failed in overload, and no evidence of fatigue or corrosion was found.
Further examination revealed that the rudder trim control rod was composed of a low-alloy, 1000-series carbon steel. An airplane manufacturer representative indicated that the rod should have been composed of a higher grade, 4000-series steel. The airplane was manufactured in 1972, acquired by the current owner in 2005, and had 11,575 hours of operation at the time of the incident. It could not be determined when or by whom the rod was installed on the airplane; it was not installed during the airplane's current ownership.
Probable Cause: The installation of an incorrect rudder trim tab control rod by unknown maintenance personnel, which resulted in the rod failing in flight due to overload and subsequent uncontrolled rudder oscillations.
Accident investigation:
 |
|
Sources:
NTSB ERA13IA326
Location
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 01-Apr-2023 16:08 | 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