ASN Wikibase Occurrence # 293811
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: | Thursday 12 May 2005 |
| Time: | 16:50 LT |
| Type: |  Beechcraft C35 |
| Owner/operator: | Private |
| Registration: | N709D |
| MSN: | D-2981 |
| Year of manufacture: | 1951 |
| Total airframe hrs: | 5864 hours |
| Engine model: | Teledyne Continental E-225-8 |
| Fatalities: | Fatalities: 0 / Occupants: 1 |
| Aircraft damage: | Substantial |
| Category: | Accident |
| Location: | Rancho Santa Fe, California -
 United States of America
|
| Phase: | Unknown |
| Nature: | Private |
| Departure airport: | San Diego-Montgomery-Gibbs Executive Airport, CA (MYF/KMYF) |
| Anza, CA (54CL) | |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
Following a loss of engine power, the pilot made a forced landing in an open field and collided with two fences. The FAA inspector who responded to the accident site reported that fuel was in the fuel tanks. A visual inspection of the engine revealed no obvious mechanical failures. Investigators made unsuccessful attempts to run the engine; it would start, but would not remain running. The engine driven fuel pump was removed and investigators noted that the mating splines in the drive shaft were severely worn. A review of the engine logbook revealed that a field overhauled engine and an overhauled fuel pump had been installed on the airframe about a year prior to the accident; an annual inspection had been completed at the time of the engine installation. The owner reported a total of 149.38 hours of operation since the annual inspection. An FAA approved repair station had overhauled the fuel pump. The fuel pump was submitted to the Safety Board Materials Laboratory for further examination. A senior metallurgist observed wear and metal flow on the square key portion of the fuel pump shaft. There was no evidence of cracking or wear of the drive gear splined teeth. The metallurgist manually rotated the fuel pump and was able to achieve only intermittent engagement between the square key and corresponding slot. A Rockwell Hardness Test (C-scale; HRC) of the gear was conducted. The hardness specification for the gear was between 50-52 HRC. Initially the gear results for the HRC were below acceptable limits and a Rockwell B (B-scale; HRB) test was performed with an average hardness of 94.5 HRB. Laboratory personnel determined that the gear had a cadmium coat, and conducted another test after removal of the cadmium coat. The HRC tests were performed with an average gear hardness of 40 HRC. The FAA issued a suspected unapproved part notification (UPN No. 2004-00053) regarding the overhaul/repair procedure of the accident fuel pump. Teledyne Continental Motors issued a Service Instruction Letter (SIL) SIL06-2 notifying owners and operators of the FAA's issuance of UPN No. 2004-00053.
Probable Cause: failure of the engine driven fuel pump due to the improper overhaul procedure of the fuel pump by an overhaul facility, and the use of parts that did not meet hardness specification.
Accident investigation:
 |
|
Sources:
NTSB LAX05LA166
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 10-Oct-2022 13:50 | 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