Five Boeing 787 Engine Removals After GE Turbine Blade Damage Near 1,000 Cycles
Key Facts
A report published by the South China Morning Post on November 2, 2026, said Chinese aviation expert Xia Xiaofeng had identified early damage to some high-pressure turbine blades in GE Aerospace engines used on Boeing 787 aircraft. In the study, Xia wrote that the airline’s fleet recorded five engine removals from service because of defects in Phase 2/2+ blades. He said cracks may develop in some blades after about 1,000 flight cycles and could lead to metal fragments breaking off. The operational concern is that the damage could require an engine inspection or replacement before it completes its service cycle. The findings leave airlines to choose between taking additional engines out of service or continuing to operate them under stringent inspection requirements.
The report described the defect as material loss between cooling holes on the blades’ convex surfaces. This description points to the location of the damage addressed by the study, but does not establish that all cases began with cracks; the study said cracks could appear in some blades. The study cited an explanation for the damage from an analysis by GE, attributing it to thermal fatigue in the material between the cooling holes. But the report did not present an independent statement from GE Aerospace confirming this explanation, so it remains attributed to the analysis cited by the study. This detail has operational importance because the location of the defect and how it develops determine what airlines need to monitor when inspecting the blades.
The direct finding reported by the study was five engine removals from service, a total for the airline fleet cited in it, not evidence of a failure rate among all GEnx-1B operators. According to the report, the removals were due to defects in Phase 2/2+ high-pressure turbine blades. The available text did not specify how many cycles the five engines had completed before removal, nor did it link each individual case to the appearance of a crack. These limits make it important to distinguish the described damage from the possibility of cracking when assessing the scale of the problem. For airlines, the impact is the choice cited in the report between replacing the engines and continuing to operate them under strict inspection requirements.
GEnx-1B engines are in broad use: GE Aerospace says the GEnx family serves more than 50 operators worldwide, averaging more than 600,000 flight hours a month. These figures indicate the scale of the fleet that may be affected by changes to inspection procedures, but they do not measure a failure rate or establish how widespread the defect examined in the study is. The company also said an AI-powered blade inspection tool had been used on a widebody GEnx engine for about three years. It added that the tool cut blade inspection time in half compared with conventional borescope inspections. The tool provides context on available inspection methods, although the report did not say it was used in the five cases presented by the study.
In a separate development involving the GEnx engine, the U.S. National Transportation Safety Board concluded that a failure in 2024 was caused by a fracture in a rear retaining ring for first-stage high-pressure turbine blades. The board said the fracture resulted from the growth of a stress crack that began at a particle cluster in the material, explaining that the ring is a different component from the blades examined in the Chinese study. Corrective actions cited in the report included inspecting and removing suspected retaining rings, as well as continuous monitoring of baseline vibration changes across the GEnx fleet. As the report neared completion, at least 477 retaining rings had been removed for inspection, and at least 55 turbine units had undergone ultrasonic testing, with no cracks found in those inspections up to that point. But a data analysis tool alerted GE in February 2025 to an engine that was in operation, and ultrasonic testing after its removal indicated a crack.
The board said GE is seeking to recertify the Rene 88 alloy retaining-ring configuration as the primary configuration. The Rene 65 version will remain approved for use but will not be available as a spare part, according to the report. These steps concern the first-stage retaining ring, not the turbine blades examined in the Chinese study. For operators, the decision cited in the study’s report remains tied to engines with blade defects: replace them or continue operating them under strict inspection requirements. The report did not specify a subsequent date for regulatory action or a GE decision on the study’s findings.