NTSB CAROL · Event
Event DCA96MA068
Aircraft involved
Probable cause & findings
the fracture of the left engine's front compressor fan hub, which resulted from the failure of Delta Air Lines' fluorescent penetrant inspection process to detect a detectable fatigue crack initiating from an area of altered microstructure that was created during the drilling process by Volvo for Pratt & Whitney and that went undetected at the time of manufacture. Contributing to the accident was the lack of sufficient redundancy in the in-service inspection program. (NTSB Report AAR-98/01)
Factual narrative
On July 6, 1996, Delta Airlines flight 1288, an MD-88, N927DA, experienced an uncontained failure of the left engine during the beginning of the takeoff roll. The flightcrew stopped the airplane about 1400 feet down the takeoff runway. On board the airplane were 137 passengers, 2 flightcrew members, 3 cabincrew, and 2 non-revenue Delta employees occupying the cockpit and aft jumpseats. Engine parts entered the left side of the aft cabin resulting in 2 passengers sustaining fatal injuries and 2 sustained major injuries. Three other passengers received minor injuries during the evacuation. The captain stopped the evacuation from the emergency exits, and an airstair was brought to the airplane to evacuate the remaining passengers and the crew. The fan hub for the left engine was found fractured. During the initial part of its takeoff roll, the airplane experienced an engine failure. Uncontained engine debris from the front compressor front hub (fan hub) of the #1 (left) engine penetrated the left aft fuselage. Two passengers were killed and two others were seriously injured. The takeoff was rejected, and the airplane was stopped on the runway. The fan hub had fractured through a tierod hole and blade slot. Some form of drill breakage or drill breakdown, combined with localized loss of coolant and chip packing, had occurred during the drilling process, creating an altered microstructure and ladder cracking in the fan hub. Drilling damage extended much deeper into hole sidewall material than previously anticipated by P & W. Fatigue cracks initiated from the ladder cracking in the tierod hole and began propagating almost immediately after the hub was put into service in 1990. The crack was large enough to have been detectable during the last fluorescent penetrant inspection at Delta. Delta's nondetection of the crack was caused either by a failure of the cleaning and fluorescent penetrant inspection processing, a failure of the inspector to detect the crack, or some combination of these factors. Source: NTSB Aviation Accident Database (Pre-2008 Archive) Retrieved: 2026-02-12
Verbatim from NTSB's published report. Source file
NTSB_1996_DCA96MA068.txt.
Findings + structured fields enriched from FAA avall.mdb.
Full investigation docket on
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Related research
What the literature says.
Academic papers and agency reports matching this event's aircraft type or causal vocabulary (engine failure). Sourced from NASA NTRS, NTSB Safety Studies, FAA CAMI, AOPA Air Safety Institute, Embry-Riddle Scholarly Commons, arXiv, and the Semantic Scholar academic graph.
- arXiv 2022 · arXiv preprint
Multi-level Adaptation for Automatic Landing with Engine Failure under Turbulent Weather
This paper addresses efficient feasibility evaluation of possible emergency landing sites, online navigation, and path following for automatic landing under engine-out failure subject to turbulent wea…
- NASA NTRS 2019 · Conference Paper
Simulation of Liquid Rocket Engine Failure Propagation Using Self-Evolving Scenarios
Traditional probabilistic risk assessment approaches often require failure scenarios to be explicitly defined through event sequences that are then quantified as part of the integrated analysis.
- NASA NTRS 2019 · Conference Paper
Rocket engine failure detection using system identification techiques
The theoretical foundation and application of two univariate failure detection algorithms to Space Shuttle Main Engine (SSME) test firing data is presented.
- NASA NTRS 2019 · Conference Paper
Rocket engine failure detection using system identification techniques
The theoretical foundation and application of two univariate failure detection algorithms to Space Shuttle Main Engine (SSME) test firing data is presented.
- NASA NTRS 2019 · Technical Memorandum (TM)
A simulator investigation of engine failure compensation for powered-lift STOL aircraft
A piloted simulator investigation of various engine failure compensation concepts for powered-lift STOL aircraft was carried out at the Ames Research Center.
- Semantic Scholar 2019 · Article (AIAA Scitech 2019 Forum)
Impact of Engine Failure Constraints on the Initial Sizing of Hybrid-Electric GA Aircraft
Potential advantages of hybrid-electric aircraft are fuel savings, lower emissions, and reduced noise. Since these aircraft generally apply multiple power sources, they can also be designed to sustain…
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