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Alaska Airlines Flight 261 was an Alaska Airlines flight of a McDonnell Douglas MD-80 series aircraft that crashed into the Pacific Ocean on January 31, 2000, roughly 2.7 miles (4.3 km; 2.3 nmi) north of Anacapa Island, California, following a catastrophic loss of pitch control, killing all 88 on board: 5 crew and 83 passengers.
The reconstruction of the accident sequence begins with the Alaska Airlines Flight 261 horizontal stabilizer takeoff setting of 7.0 degrees ANU in Puerto Vallarta, Mexico. Subsequent airplane nose down stabilizer trim motion from 7.0 degress ANU to 2.0 degrees ANU was due to the use of primary trim.
Alaska Airlines Flight 261: Pacific Ocean near Anacapa Island: McDonnell Douglas MD-83: Maintenance intervals extended beyond safe limit 88 Lack of lubrication causing structural failure of the jackscrew on the horizontal stabiliser resulting in aircraft descending inverted into sea 2001-11-12 American Airlines Flight 587
Engineers Sylvain Alarie and Gilles Primeau, experts on horizontal stabilizers consulted by Radio-Canada, observed anomalies in the data recorded during the Lion Air and Ethiopian Airlines crashes: a progressive shift of the horizontal stabilizer by 0.2°, before the crash. [97]
Alaska Airlines Flight 261, a McDonnell Douglas MD-80, on January 31, 2000. The acme nut/jack screw assembly, which adjusted the pitch of the horizontal stabilizer, failed. As a result, the pilots lost control of aircraft pitch, and the flight crashed into the Pacific Ocean killing all 5 crew and 83 passengers on board.
January 31 – Due to inadequate maintenance, the horizontal stabilizer of Alaska Airlines Flight 261, a McDonnell Douglas MD-83, jams during a flight from Puerto Vallarta, Mexico, to Seattle, Washington, forcing the plane into a dive from 31,500 feet (9,601 m) to between 23,000 (7,010 m) and 24,000 feet (7,315 m) in 80 seconds.
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A Boeing 737 uses an adjustable stabilizer, moved by a jackscrew, to provide the required pitch trim forces. Generic stabilizer illustrated. A horizontal stabilizer is used to maintain the aircraft in longitudinal balance, or trim: [3] it exerts a vertical force at a distance so the summation of pitch moments about the center of gravity is zero. [4]