On February 17, 1984, a Mcdonnell Douglas DC-9-82 (registration N203AA) was involved in an aviation accident near Santa Ana, CA. Investigators recorded the probable cause as: High cycle fatigue fracture of a stage 8 compressor blade root, originating along the edge of the disk, leading to blade failure and subsequent compressor damage and power loss. This summary draws on records from the U.S. National Transportation Safety Board (NTSB) historical archive.
Shortly after takeoff, the number 1 engine experienced a total power loss. Examination revealed substantial compressor damage, with 40 stage 8 blades ejected and 17 others missing airfoils. Metallurgical analysis identified a high cycle fatigue fracture in the root of one blade.
Incident Overview
Shortly after takeoff, the aircraft experienced a total power loss on its number 1 engine. The event prompted an immediate examination to determine the cause of the failure.
Examination Findings
Inspection of the engine revealed substantial damage in the compressor section, affecting stages from stage 6 rearward. Specifically, 40 stage 8 compressor blades were forced completely out of their disk dovetail slots. Of the 18 remaining blades in that stage, 17 had lost their airfoils due to fractures occurring just above the platform. The 18th blade was fractured through the root area just below the platform.
Metallurgical Analysis
A metallurgical examination of the 18th blade disclosed that it sustained a diagonal and transverse fracture through the root of the blade. The fracture propagated in high cycle fatigue from its origin along the edge of the disk.
Probable cause
High cycle fatigue fracture of a stage 8 compressor blade root, originating along the edge of the disk, leading to blade failure and subsequent compressor damage and power loss.
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