CEN11IA108

During the airplane's descent, the yaw damper disengaged while the autopilot remained on. When the flightcrew checked the flight controls for freedom of control, the ailerons, elevator, and rudder were found to be frozen in place. The flightcrew exerted enough pressure until the controls broke free with a “snap.” The flight controls remained stiff for the remainder of the flight. The temperature was -9 degrees C at the destination. Following a normal approach and landing, the flight controls and nosewheel steering became inoperative. The flightcrew used differential power and braking to taxi to the ramp. A postflight examination by maintenance personnel revealed ice in the area of frame 36 and around the primary flight control cables and pulleys in that area. An examination of the fuselage drain holes showed no obstructions and the airplane was returned to service. An emergency airworthiness directive was subsequently issued that advised of three incidents and that required inspection of the fuselage belly and testing of the fuselage drain holes.

On December 13, 2010, about 0830 eastern standard time, a Piaggio P180, N140SL, operated by Avantair Inc., sustained no damage when the airplane’s flight controls bound during approach to the Port Columbus International Airport (CMH), near Columbus, Ohio. The two pilots and two passengers were not injured. Marginal visual meteorological conditions prevailed. The flight was operating on an activated instrument flight rules flight plan. The business flight was conducted under 14 Code of Federal Regulations Part 91K. The flight departed from the Westchester County Airport (HPN), near White Plains, New York, about 0700, and was destined for CMH. According to the operator, the flight departed HPN and initially leveled off at a pressure altitude of 26,000 feet. An indicated airspeed caution light illuminated. The flighcrew performed the abnormal checklist for the number two air data computer failure and selected the number one computer to continue with for the remainder of the flight. During the descent in to CMH at about 15,000 feet the yaw damper disengaged while the autopilot remained on. The captain instructed the first officer who was the pilot flying to check the freedom of the flight controls. The first officer found the ailerons, elevator, and rudder to be "frozen" in place. The flightcrew exerted enough pressure until the controls broke free with a “snap.” The flight controls remained "stiff and sticky" for the remainder of the flight. The flightcrew performed a normal approach and landing on runway 28L. Once on the ground the flight controls and nose wheel steering became inoperative. The flightcrew used differential power and braking to taxi to the ramp. A post flight inspection by maintenance personnel revealed ice in the fuselage belly area of frame 36 and around the primary flight control cables and pulleys in that area. The ice was warmed by heaters and removed from the fuselage belly. The fuselage drain holes were inspected for obstructions and general condition. No anomalies were detected. The fuselage belly was towel dried and the airplane was returned to service. At 0851, the recorded weather at CMH was: Wind 310 degrees at 8 knots; visibility 4 statute miles; present weather light snow and mist; sky condition overcast 2,200 feet; temperature -9 degrees C; dew point -12; altimeter 29.73 inches of mercury. On December 20, 2010, the Federal Aviation Administration issued emergency airworthiness directive (AD) 2011-01-53 to all known U.S. owners/operators of Piaggio P180s. The AD, in part, stated: Unsafe Condition ... (e) This emergency AD was prompted by three incidents of the flight controls jamming on Piaggio Model P-180 airplanes. Water or fluid accumulating and freezing when the aircraft reaches and holds altitudes where the temperature is below the freezing point may cause the flight controls to jam with consequent loss of control. ... Inspection and Corrective Actions (g) Unless already done in compliance with emergency AD2011-01-51, before further flight, do the following actions using the instructions in Appendix 1 of this AD. (1) Remove the central floor panels in the cabin and inspect the fuselage belly; and (2) Functional test the fuselage drain holes.