AD 2021-11-07
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric | Company | Airworthiness Directives; General Electric Company Turbofan Engines |
Unsafe Condition
Two stages 6-10 compressor rotor spools in the high-pressure compressor (HPC) assembly were damaged at similar locations, and certain stages 6-10 compressor rotor spool webs did not undergo a required fluorescent penetrant inspection (FPI) during production.
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Required Actions
Inspect the stages 6-10 compressor rotor spool, and depending on the results of the inspection, replace the stages 6-10 compressor rotor spool with a part eligible for installation.
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Compliance Time
Before the next engine shop visit, or before 6,500 cycles since new, whichever occurs first.
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Affected Aircraft
General Electric Company GEnx-1B64, 1B64/P1, -1B64/P2, -1B67, -1B67/P1, -1B67/P2, -1B70, -1B70/75/P1, -1B70/75/P2, -1B70/P1, -1B70/P2, -1B70C/P1, -1B70C/P2, -1B74/75/P1, -1B74/75/P2, -1B76/P2, -1B76A/P2, -2B67, -2B67/P, and -2B67B model turbofan engines.
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Source: Official FAA Source ↗
Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
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