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ASN Wikibase Occurrence # 178176
Last updated: 8 November 2019
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Date:03-JUN-2004
Time:12:15
Type:Silhouette image of generic BE35 model; specific model in this crash may look slightly different
Beechcraft M35 Bonanza
Owner/operator:Private
Registration: N693V
C/n / msn: D-6444
Fatalities:Fatalities: 0 / Occupants: 2
Other fatalities:0
Aircraft damage: Substantial
Category:Accident
Location:Strafford, MO -   United States of America
Phase: Landing
Nature:Private
Departure airport:Tell City, IN (TEL)
Destination airport:Tulsa, OK (TUL)
Investigating agency: NTSB
Narrative:
The airplane collided with a fence and a guy wire during a forced landing following a loss of engine power. The pilot reported he was flying at 8,500 feet mean sea level when the number 2 cylinder departed the engine resulting in a total loss of engine power. He reported that with no airports within gliding distance, he elected to land in a farmer's field where the airplane contacted a fence and a guy wire. The number 2 cylinder and the left magneto were not located after the accident. Half of the crankcase, two fractured cylinder through-bolts, two cylinder through-bolt nuts with pieces of bolts inside, four cylinder hold down nuts with pieces of studs inside, a connecting rod cap with the connecting rod cap bolt, and a connecting rod nut were submitted for a metallurgical examination. The studs and through-bolts were arbitrarily numbered clockwise starting at the upper forward stud. All of the studs and through-bolts that were examined exhibited fatigue cracking with stud 3 exhibiting the largest fatigue region. A lip was observed on the surface of the crankcase which corresponded to the forward edge of the cylinder barrel flange, adjacent to the through-bolts. Linear marks aligned with the axis of the cylinder were observed at the aft side of the cylinder hole corresponding to sliding contact with the cylinder barrel skirt. Sectioning of studs 3 and 4 revealed cracks and/or rolling laps at the thread roots. On stud 4, many of the cracks extended radially then turned. Two studs were removed from cylinder #4 and one of them also displayed sharp thread radii and cracking. This cylinder did not fail. The engine was overhauled on July 6, 2000, at a tach time of 2440.33 hours. The engine had accumulated 194.03 hours since the overhaul.



Probable Cause: The improper installation of the cylinder during the engine overhaul which resulted in the fatigue failure of the cylinder studs and through-bolts and the subsequent separation of the cylinder. Factors associated with the accident were the fence and the guy wire which the airplane contacted during the forced landing.

Sources:

NTSB: https://www.ntsb.gov/_layouts/ntsb.aviation/brief.aspx?ev_id=20040608X00744&key=1


Revision history:

Date/timeContributorUpdates
01-Aug-2015 12:54 Noro Added
21-Dec-2016 19:30 ASN Update Bot Updated [Time, Damage, Category, Investigating agency]
07-Dec-2017 18:06 ASN Update Bot Updated [Other fatalities, Departure airport, Destination airport, Source, Narrative]

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