Accident Overview
On October 29, 2010, about 1515 Central Daylight time, a Piper PA-32R-301T, registration N8370L, sustained substantial damage when it overran the end of the runway during an aborted takeoff. The airplane traveled through a ditch and struck a road embankment. The private pilot and his passenger were not injured. The airplane was owned and operated by the pilot under 14 Code of Federal Regulations Part 91 as a personal flight. The flight was conducted in visual meteorological conditions without a flight plan. The flight was originating at the time, with an intended destination of Olwein Municipal Airport, Olwein, Iowa.
Flight Details
The pilot reported performing a pre-flight examination of the airplane prior to the flight. During the takeoff roll, he applied back pressure to the yoke but the airplane did not rotate. He reduced the throttle and attempted to stop the airplane. During the attempted aborted takeoff, the airplane traveled off the end of the runway and struck a road embankment.
Examination Findings
A postaccident examination of the airplane revealed that the "up" stabilator control cable had fractured at the threaded portion of the turnbuckle. The National Transportation Safety Board Materials Laboratory examined that portion of the cable and found that the turnbuckle fractured in the shank region about 0.15 inch from the wrench flats. Areas of the turnbuckle, including the shank, were covered with salt crystals, and the shank exhibited areas of corrosion. Examination of the fractured region with a 5X to 50X binocular zoom stereomicroscope revealed that the fracture was highly branched, consistent with stress corrosion cracking. The turnbuckle fitting was constructed using SAE-AISI 303 SE stainless steel.
Maintenance History
The most recent annual inspection had been completed on November 1, 2009. The airplane had accumulated about 1 hour of flight time since that inspection. The airplane manufacturer had previously issued a maintenance alert service letter (dated March 31, 2003) noting that corrosion may be found on control cable attachment fittings, especially in aircraft in service for 15 years or more. The service letter recommended inspection of cable terminals, turnbuckles, and fittings for corrosion or cracking within the next 100 hours time in service or to coincide with the next scheduled maintenance event. For airplanes in service for 15 years or more, the letter suggested the use of a 10X magnifier. Any evidence of corrosion or cracking was cause for replacement according to the service letter. The current revision of the airplane service manual (dated July 15, 2006) included the special control cable fitting inspection for airplanes in service 15 years or more, as outlined in the prior service letter.
The FAA issued Special Airworthiness Information Bulletins (SAIB) related to corrosion and subsequent failure of control cables. The first SAIB, released in November 2001, advised operators of corrosion and cracking experienced with control cable terminals fabricated from 303SE stainless steel. The bulletin recommended inspection of flight control cables and replacement of any cables showing signs of corrosion or cracking. A revision to that SAIB was released in January 2004 to include the use of a magnifying glass for corrosion inspections. An additional FAA SAIB, dated October 4, 2010, advised operators of specific failures related to the horizontal stabilator turnbuckle/control cable assembly on Piper airplanes. This SAIB recommended that operators incorporate the previously issued Piper service letter into their inspection procedures and noted that any evidence of corrosion or cracking is cause for replacement of the cable assembly.
The NTSB issued safety recommendations A-01-6 through A-01-8 in April 2001. These recommendations noted previous failures of control cable turnbuckles and recommended issuance of an airworthiness directive to require inspections of affected aircraft. In response, the FAA issued the November 2001 SAIB recommending inspections in all aircraft with 303SE stainless steel turnbuckles installed. The recommendations were subsequently closed, noting acceptable alternate action.
Regulatory Context
FAA regulations (91.409) require that an annual inspection be completed within the preceding 12 calendar months. Accordingly, the annual inspection completed in November 2009 was valid through the last day of November 2010.