ASN Wikibase Occurrence # 41279
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 23 March 1999 |
| Time: | 14:28 LT |
| Type: |  Cirrus SR20 |
| Owner/operator: | Cirrus Design Corporation |
| Registration: | N115CD |
| MSN: | 1001 |
| Year of manufacture: | 1999 |
| Total airframe hrs: | 6 hours |
| Engine model: | Continental IO-360-ES |
| Fatalities: | Fatalities: 1 / Occupants: 1 |
| Aircraft damage: | Destroyed |
| Category: | Accident |
| Location: | Duluth, MN -
 United States of America
|
| Phase: | Manoeuvring (airshow, firefighting, ag.ops.) |
| Nature: | Unknown |
| Departure airport: | , MN (KDLH) |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
The experimental airplane was on a test flight when it impacted terrain following an emergency landing attempt. The airplane was certified as an experimental airplane for crew training. The airplane's aileron spring cartridge and rudder-aileron interconnect had been removed for the test flight. The airplane was loaded with ballast to provide an aft center of gravity with stall tufts attached to both wings. During the test flight, the company test pilot declared an emergency and reported a flight control problem while maneuvering. Radar data indicates that 10 seconds prior to the declaration of an emergency by the test pilot, the aircraft was in a stall phase of flight. Postaccident inspection revealed that the right aileron exhibited evidence of jamming with its wing cove/skin. In postaccident testing of a similar SR20, a manual input pilot force was applied to the side yoke control by a Cirrus Design Corporation (CDC) test pilot. A maximum load of 85 pounds was achieved by the test pilot by leaning forward and applying both hands on the side yoke control. The control input could not be held indefinitely due to muscle fatigue. During the control input, the right aileron was deflected 11 degrees with the left aileron clamped at the inboard rib. CDC test pilots were not graduates of civilian or military flight test schools. The test pilot was not equipped with a personal parachute. A gusting crosswind of approximately 16 knots was present on the selected landing runway. The airplane's maximum demonstrated crosswind component was 19 knots. All runways were available at the time of the accident. CDC was not monitoring radio communications with the accident pilot during the test flight.
Probable Cause: the lack of sufficient aileron-to-wing gap clearance design. Contributing factors were the inadequate oversight of the Federal Aviation Administration of the design and manufacturing and flight test process of Cirrus Design Corporation, the location of the control yoke, the inadequate surveillance of the test flight and the test flight procedures by the Cirrus Design Corporation. The destabilizing crosswind condition that existed on the landing runway was an additional factor.
Accident investigation:
 |
|
Sources:
NTSB CHI99FA112
Location
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 24-Oct-2008 10:30 | ASN archive | Added |
| 21-Dec-2016 19:23 | ASN Update Bot | Updated [Time, Damage, Category, Investigating agency] |
| 26-Nov-2017 10:53 | ASN Update Bot | Updated [Departure airport, Source, Narrative] |
| 08-Apr-2024 08:15 | ASN Update Bot | Updated [Time, Other fatalities, Departure airport, Source, Narrative, Category, Accident report] |
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