ASN Wikibase Occurrence # 44330
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 18 September 2005 |
| Time: | 11:35 |
| Type: | Akrotech G300 |
| Owner/operator: | Private |
| Registration: | N300NW |
| MSN: | G-3001 |
| Total airframe hrs: | 834 hours |
| Engine model: | Lycoming AEIO-540-EXp |
| Fatalities: | Fatalities: 1 / Occupants: 1 |
| Aircraft damage: | Destroyed |
| Category: | Accident |
| Location: | Yukon, OK -
 United States of America
|
| Phase: | Manoeuvring (airshow, firefighting, ag.ops.) |
| Nature: | Private |
| Departure airport: | Yukon, OK (F29) |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
The 6,700-hour commercial pilot had just started a practice session in preparation for an aerobatic competition when she initiated a 45-to-55-degree nose-up climb. As the airplane began to ascend, witnesses observed the acrylic canopy separate in fragments from the airplane. The airplane continued to climb before it rolled to the right and entered an approximate 60-degree nose-down descent. The engine remained at full power during the descent and no flight control movements were observed after the canopy had separated. A witness made several attempts to contact the pilot via radio, but there was no response. Examination of the canopy revealed that it fastened to the fuselage by two metal hinges that fastened directly to the fuselage with four flat-head bolts. There was no evidence of bonding material or adhesive in the area of the fuselage underneath the mounting plate of either hinge. The forward hinge was never located; however, a closer view of the location where the front canopy hinge was located indicated there were "rub" marks on the surface of the fuselage underneath the hinge pin lock wire, which was indicative to contact wear with the bent end of the hinge pin. The hinge pin lock wire was also worn and flattened in areas, which corresponded to contact wear with the bent end of the hinge pin. The rear hinge was fractured into two pieces through the mounting plate at the fuselage side of the hinge. Deformation was observed around the rivet holes where the hinge was attached to the fuselage, indicative of overstress. Bolt holes in the mounting plate at the canopy side of the hinge were deformed, and the edges of the holes were cracked or fractured, consistent with overstress. One of the four bolts remained in the mounting plate on the canopy side of the hinge. Rub marks similar to those found in the area of the front hinge pin lock wire were not present. In addition, there was no damage to the hinge pin lock wire. A review of aircraft logbooks revealed that the airplane was built in 1997 and had accrued approximately 900 hours at the time of the accident.
Probable Cause: The catastrophic separation of the canopy as result of the failure of the forward canopy hinge while performing aerobatics and the subsequent incapacitation of the pilot.
Accident investigation:
 |
|
Sources:
NTSB: https://www.ntsb.gov/_layouts/ntsb.aviation/brief.aspx?ev_id=20050930X01555&key=1
Location
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 28-Oct-2008 00:45 | ASN archive | Added |
| 21-Dec-2016 19:24 | ASN Update Bot | Updated [Time, Damage, Category, Investigating agency] |
| 06-Dec-2017 10:58 | ASN Update Bot | Updated [Operator, 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