ASN Wikibase Occurrence # 292866
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| Date: | Saturday 5 November 2005 |
| Time: | 11:30 LT |
| Type: |  Cessna 185 |
| Owner/operator: | Federal Aviation Administration |
| Registration: | N771X |
| MSN: | 185-1336 |
| Total airframe hrs: | 11299 hours |
| Engine model: | Lycoming IO-540K |
| Fatalities: | Fatalities: 0 / Occupants: 3 |
| Aircraft damage: | Substantial |
| Category: | Accident |
| Location: | Cordova, Alaska -
 United States of America
|
| Phase: | Unknown |
| Nature: | Unknown |
| Departure airport: | Cordova-Mudhole Smith Airport, AK (CDV/PACV) |
| Cordova, AK | |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
A commercial certificated pilot in a tundra tire-equipped airplane from a CFR Part 135 operator, under contract to the Federal Aviation Administration (FAA) as a public use flight, was transporting FAA personnel to a navigational facility on a remote island. During the landing roll on a dirt surface runway, the lower end of the left main landing gear strut fractured at the axle bolt holes, where the axle is bolted onto the strut. The fractured end of the left gear strut dug into the ground, the airplane swerved 90 degrees to the left and nosed down, receiving structural damage to the left wingtip and the right main landing gear. The main landing gear is a spring steel strut that is shot peened during manufacture, and is bolted to the fuselage at its upper end. Photographs of the point of separation revealed a vertical fracture, oriented 90 degrees to the span of the gear strut, through the upper axle retaining bolt holes. The fractured surface of the lower end of the strut, containing the axle and brake assembly, had a rough, crystalline appearance with darkening of the metal surface along the outer edges of the strut. The fractured surface of the upper end of the strut, where it dug into the ground, had a smooth polished appearance. Periodic visual inspection of the landing gear is required by 14 CFR Part 43. Neither the manufacturer or the FAA have established service limits (hours or cycles) for the main landing gear strut. Removal of the gear strut for inspection, or the use of nondestructive inspection techniques, is not required by the manufacturer or the FAA. On March 16, 2001, the NTSB recommended that the FAA issue an airworthiness directive (AD) to require an initial and recurring inspection of Cessna main landing gear spring steel struts, using nondestructive inspection techniques. On August 31, 2001, the FAA reported to the NTSB that the current inspection criteria outlined in the Cessna Maintenance Manual are adequate to detect cracks in the main landing gear struts, and that additional airworthiness action is not warranted. On March 25, 2002, the NTSB responded by stating, in part: "The Safety Board continues to believe that a visual inspection alone will not detect cracks in the Cessna main landing gear spring struts. However, the Safety Board acknowledges that the statistical evidence does not warrant issuance of ADs at this time as called for in the Board's recommendation." In the Pilot/Operator Aircraft Accident Report (NTSB Form 6120.1), the pilot indicated that the landing gear strut, Part number 0741001-5, had accrued about 9,000 hours of service. In the optional area of the report: Recommendation (How Could This Accident Have Been Prevented), the pilot wrote: "Put time life [limit] on gear legs."
Probable Cause: A fracture and separation of the main landing gear strut during the landing roll, which resulted in a loss of control, and subsequent nose down. Factors contributing to the accident were the manufacturer's and the FAA's insufficient standards/requirements regarding inspection procedures for the main landing gear struts.
Accident investigation:
 |
|
Sources:
NTSB ANC06TA009
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 09-Oct-2022 10:04 | ASN Update Bot | Added |
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