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 17 December 2006 |
| Time: | 19:07 LT |
| Type: |  Cessna 560 Citation V |
| Owner/operator: | Mid-ohio Aviaiton Inc |
| Registration: | N49NS |
| MSN: | 560-0116 |
| Year of manufacture: | 1991 |
| Total airframe hrs: | 8359 hours |
| Engine model: | Pratt & Whitney JT15D-5A |
| Fatalities: | Fatalities: 0 / Occupants: 4 |
| Aircraft damage: | Substantial |
| Category: | Accident |
| Location: | North Canton, Ohio -
 United States of America
|
| Phase: | Unknown |
| Nature: | Unknown |
| Departure airport: | Teterboro Airport, NJ (TEB/KTEB) |
| Akron/Canton Regional Airport, OH (CAK/KCAK) | |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
The airplane was on approach to the destination airport when the low hydraulic level and flow cockpit warnings annunciated in the cockpit. The flight crew was unable to extend the right main landing gear after conducting the normal and emergency landing gear extension procedures and by performing g-loading maneuvers. The airplane landed with the right wing main landing gear retracted causing substantial damage to the right wing and fuselage structures. The total loss of hydraulic power to the airplane flaps, spoilers, thrust reversers, and landing gear was caused by a ruptured hydraulic pressure hose assembly. The examinations of the accident and exemplar hoses revealed internal wear between the fiberglass within the hose's fire sleeve and the stainless steel braid. The accident hose and two of the three exemplar hoses did not show any markings or damage to the exterior of the sleeve to indicate the existence of the internal wear abrading the stainless steel braiding. Functional testing of the landing gear system revealed that the extension sequence varied during eight actuations, and, in one actuation, the left main landing gear remained retracted. Following the accident, the airplane manufacturer was in the process of amending the airplane maintenance manual rigging procedures for the landing gear system, and placing service time limits on hydraulic hoses.
Probable Cause: The rupture of the hydraulic pressure hose assembly, which was caused by internal wear between the hose's fire sleeve and stainless steel braid, and the failure of the emergency landing gear assembly to deploy the right main landing gear during approach. Contributing to the accident were inadequate hydraulic hose assembly maintenance inspection procedures, the lack of a hydraulic hose life limit by the airplane manufacturer, and the inadequate landing gear rigging procedures.
Accident investigation:
 |
|
Sources:
NTSB CHI07LA043
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 07-Oct-2022 16:10 | 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