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: | Tuesday 8 August 2023 |
| Time: | 16:00 LT |
| Type: |  Piper PA-24-260 Comanche |
| Owner/operator: | |
| Registration: | N503JA |
| MSN: | 24-4165 |
| Year of manufacture: | 1965 |
| Total airframe hrs: | 3849 hours |
| Engine model: | Lycoming IO-540-D4A5 |
| Fatalities: | Fatalities: 0 / Occupants: 1 |
| Other fatalities: | 0 |
| Aircraft damage: | Substantial |
| Category: | Accident |
| Location: | Fullerton Municipal Airport (FUL/KFUL), Fullerton, CA -
 United States of America
|
| Phase: | En route |
| Nature: | Private |
| Departure airport: | Fullerton Municipal Airport, CA (FUL/KFUL) |
| La Verne-Brackett Field, CA (POC/KPOC) | |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
Shortly after takeoff the airplane began to shake violently with the control yoke moving rapidly forward and aft from stop to stop. The pilot was able to perform an on-airport emergency landing after shutting down the engine, but sustained hand injuries due to the extreme control forces and oscillations.
The airplane sustained substantial damage to the stabilator structure in a manner consistent with it exhibiting aerodynamic flutter. Postaccident examination revealed that the stabilator tab actuator was disconnected from the control tab, and the bolt, nut, and washer that connected them were missing. The disconnection of the actuator allowed the tab surface to uncouple, which resulted in flutter and structural damage to the stabilator.
Circumferential scoring around the bolt hole within the tabs indicated that the bolt was likely loose for an undetermined period before failure. The nut had likely not been replaced since the airplane was manufactured almost 60 years before the accident, so its locking properties would have been significantly diminished.
Probable Cause: The separation of the stabilator actuator from the stabilator tab, which resulted in pitch control surface flutter and structural damage.
Accident investigation:
 |
|
Sources:
NTSB WPR23LA317
Location
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 07-Sep-2023 21:18 | Captain Adam | Added |
| 01-Jul-2024 08:37 | ASN Update Bot | Updated [Time, Operator, Other fatalities, Phase, Destination airport, Source, Narrative] |
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