Summary
On April 11, 1998, a Mcdonnell Douglas MD82 (N951U) was involved in an incident near Washington, DC. All 84 people aboard were uninjured.
The National Transportation Safety Board determined the probable cause of this incident to be: The failure of the Dual Axis Accelerometer.
On April 11, 1998, at 0645 est, N951U, a McDonnell Douglas MD82, being operated as Trans World Airlines flight number 235, from Washington National Airport to Saint Louis, Missouri, experienced a flight control malfunction after takeoff and diverted to Dulles International Airport. There was no damage to the aircraft and there were no injuries to the crew of 5 or 79 passengers. The flight was on an IFR flight plan and visual meteorological conditions prevailed.
The crew reported that they lost the autopilot, there were inflight kicks on the rudder and the rudder tab was moving uncommanded on the ground. The aircraft was an MD-82, S/N 49245. The Yaw Damper Actuator, Digital Flight Guidance Computer, and Dual Axis Accelerometer were removed for further testing.
This incident is documented in NTSB report CHI98IA167. AviatorDB cross-references NTSB investigation data with FAA registry records to provide comprehensive safety information for aircraft N951U.
Accident Details
Probable Cause and Findings
The failure of the Dual Axis Accelerometer.
Aircraft Information
Registered Owner (Historical)
Analysis
On April 11, 1998, at 0645 est, N951U, a McDonnell Douglas MD82, being operated as Trans World Airlines flight number 235, from Washington National Airport to Saint Louis, Missouri, experienced a flight control malfunction after takeoff and diverted to Dulles International Airport. There was no damage to the aircraft and there were no injuries to the crew of 5 or 79 passengers. The flight was on an IFR flight plan and visual meteorological conditions prevailed.
The crew reported that they lost the autopilot, there were inflight kicks on the rudder and the rudder tab was moving uncommanded on the ground. The aircraft was an MD-82, S/N 49245. The Yaw Damper Actuator, Digital Flight Guidance Computer, and Dual Axis Accelerometer were removed for further testing. The Yaw Damper Actuator and the Digital Flight Guidance Computer passed testing.
The Dual Axis Accelerometer from the aircraft, PN 4034239-901, SN 8303033, was taken to the Honeywell Support Center in Dallas, Texas for further investigation. The part was bench tested using test manual #22-19-01, Rev 1 at the avionics test center. The unit failed an original test and failed a second test after a metal sliver imbedded in the pins was removed. See attached test report of the inspection conducted July 8, 1998.
Data Source
Data provided by the National Transportation Safety Board (NTSB). For more information on this event, visit the NTSB Records Search website. NTSB# CHI98IA167