CEN10IA453

Factual narrative

On August 1, 2010, about 1200 central daylight time, a Piper PA-32R-301T airplane, N4184X, experienced a total loss of aileron control prior to landing at the Mount Pleasant Municipal Airport (OSA), Mount Pleasant, Texas. The airplane was not damaged and the commercial pilot was not injured. The positioning flight originated at Gilmer Municipal Airport (JXI), Gilmer, Texas, with OSA as the intended destination. The flight was being conducted under the provisions of 14 Code of Federal Regulations Part 91. Visual meteorological conditions prevailed at the time of the incident. The pilot reported he was level at 2,000 feet mean sea level, about 10 miles from OSA, when the airplane started an un-commanded left roll. He disengaged the autopilot and discovered the ailerons were not responding. The pilot landed successfully at OSA using the rudder to control the airplane. The airplane aileron control system included two control cables routed to each wing; the primary cable and the balance cable. A postaccident examination by the operator revealed the right wing (RW) primary cable was completely severed 13 inches from the threaded end of the cable, roughly located adjacent to an idler pulley. The pulley could not be rotated when manipulated. Additional wear spots, indicated by polishing and/or fraying were annotated at additional locations on the RW primary cable, the RW balance cable, and left wing (LW) primary and balance cables. The RW primary cable had a dark grease like material covering the failure area. A similar substance was found on the idler pulley. An additional idler pulley for the RW balance cable was found that initially did not rotate when manipulated. The person manipulating the idler pulley twisted it firmly and heard a “click.” The pulley turned freely following the click. Inspectors from the Federal Aviation Administration examined the airplane and components on August 5, 2010. They stated the idler pulley at the location of the cable failure appeared to have a manufacturing flaw, in that it was not machined completely through, which created a “lip” that did not allow the bushing to go completely through the idler pulley. The suspect RW primary cable idler pulley and portions of the broken RW primary cable were sent to the manufacturer for examination. The inside diameter of the idler pulley outer bearing was found to measure .0065 inches less than the service limit for the component. The submitted portion of the primary cable was found to be manufactured from galvanized steel. Piper Aircraft, Inc. issued Service Letter No. 1135 as a maintenance alert on October 19, 2010. The alert emphasized the critical nature of control cable and pulley inspections, and highlighted the recurring inspection requirements. It included instructions for inspections of control cables and pulleys. The pilot reported that he was in level flight with the autopilot engaged when the airplane began an uncommanded roll. The pilot disengaged the autopilot and found that the airplane’s ailerons were inoperative. The pilot made a successful landing using the rudder for directional and roll control. A postaccident examination of the airplane revealed that the right aileron primary control cable was severed where it contacted an idler pulley. That pulley would not rotate due to an out-of-tolerance idler pulley outer bearing that restricted the rotation of the pulley. It is likely that the control cable sliding against the seized pulley caused the cable to wear through. The airplane manufacturer issued a maintenance alert following this incident that highlighted the importance of proper and recurring inspections of the flight control cables and pulleys. Source: NTSB Aviation Accident Database Retrieved: 2026-02-12

NTSB Findings

FAA avdata. C = Cause, F = Factor.

• C Aircraft-Aircraft systems-Flight control system-Aileron control system-Failure - C
• C Aircraft-Aircraft systems-Flight control system-Aileron control system-Fatigue/wear/corrosion - C