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ASN Wikibase Occurrence # 17505
Last updated: 31 August 2020
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Type:Silhouette image of generic P28A model; specific model in this crash may look slightly different
Piper PA-28-180
Owner/operator:Robert Waldron PC
Registration: N5300L
C/n / msn: 28-4602
Fatalities:Fatalities: 0 / Occupants: 2
Aircraft damage: Substantial
Location:in a field near Paducah, TX -   United States of America
Phase: En route
Departure airport:Stephenville, TX (SEP)
Destination airport:Dumas, TX (DUX)
Investigating agency: NTSB
The private pilot/owner and the passenger were on a cross country flight at an altitude of 6,500 feet when a section of propeller blade broke off and the airplane began to shake violently. The pilot reduced power, slowed the airplane and stalled the propeller, which reduced the vibrations. He then declared an emergency and made a forced landing to a field. Examination of the airplane revealed that approximately 44-inches of one of the Sensenich fixed-pitch (all metal) propeller blades had separated and was not recovered. The other blade was intact. The top and bottom engine mounts on the right side (as viewed from the cockpit) were severed and the engine was displaced down and to the right. A materials examination of the propeller's fractured surface revealed fatigue cracking through approximately 85 percent of the blade and corrosion pitting at the initiation point of the failure. The remaining portion of the fracture was more jagged, had a matte appearance, and was oriented at a slant angle, which was indicative of a final overstress fracture region. A review of Sensenich's records revealed that in April 1991, this propeller (which was original to the airplane) was sent to Sensenich to be reworked; however, it was rejected due to the fact that it was "out of material chord at the tip." The propeller was returned, and at some point was placed back on the airplane. However, there was no logged entry in the airframe logbook that indicated when this was accomplished or by whom. On June 13, 1996, the FAA issued Airworthiness Directive (AD) 69-09-03, Revision 3, titled, Sensenich Propeller Manufacturing Company Incorporated models M76EMM, M76EMMS, 76EM8, and 76EM8S metal propellers. The directive was issued, "To prevent propeller blade tip fatigue failure, which can result in loss of control of the aircraft..." As a result, this particular propeller was to be removed, inspected, and reworked in accordance with Senseinich Propeller Service Bulletin (SB) number R-14A, dated July 28, 1995. Those propellers that had been inspected in accordance to the Service Bulletin and found satisfactory were to be marked with the suffix letter "K." Examination of the accident propeller revealed there was no "K" marking. In addition, a review of the logbooks revealed that the AD had not been complied with as required per Federal Aviation Regulations.

Probable Cause: Fatigue failure and separation of the propeller during cruise flight. Contributing to the accident was the owner's failure to comply with a long standing Airworthiness Directive.




Revision history:

21-Apr-2008 21:02 Fusko Added
21-Dec-2016 19:14 ASN Update Bot Updated [Time, Damage, Category, Investigating agency]
21-Dec-2016 19:16 ASN Update Bot Updated [Time, Damage, Category, Investigating agency]
21-Dec-2016 19:20 ASN Update Bot Updated [Time, Damage, Category, Investigating agency]
03-Dec-2017 10:42 ASN Update Bot Updated [Operator, Total occupants, Other fatalities, Nature, Departure airport, Destination airport, Source, Narrative]

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