Airworthiness directives › 2025-11-03
AD 2025-11-03 Airworthiness Directives; General Electric Company Engines
Applicability*9
This AD applies to General Electric Company Model GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-1B70, GEnx-1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/P2, GEnx-1B70C/P1, GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2, GEnx-1B76/P2, GEnx-1B76A/P2, and GEnx-2B67/P engines with at least one of the following installed: (1) High Pressure Turbine (HPT) stage 1 disk having part number (P/N) 2383M83G03 and a serial number (S/N) listed in Table 1 of GE GEnx-1B Service Bulletin 72-0542 R00, dated April 15, 2024 (GE GEnx-1B SB 72-0542 R00); (2) HPT stage 2 disk having P/N 2300M84P02 and a S/N listed in Table 2 of GE GEnx-1B SB 72-0542 R00; (3) HPT stage 1 disk having P/N 2383M83G03 and a S/N listed in Table 1 of GE GEnx-2B Service Bulletin 72-0471 R00, dated April 15, 2024 (GE GEnx-2B SB 72-0471 R00); or (4) HPT stage 2 disk having P/N 2300M84P02 and a S/N listed in Table 2 of GE GEnx-2B SB 72-0471 R00.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
At the applicable time specified in paragraphs (g)(1) through (4) of this AD, remove each affected HPT stage 1 disk and HPT stage 2 disk from service and replace with a part eligible for installation. (1) For engines identified in paragraph (c)(1) of this AD, at the next piece-part exposure after the effective date of this AD or before the affected HPT stage 1 disk exceeds the cyclic removal threshold listed in Table 1 of GE GEnx-1B SB 72-0542 R00, whichever occurs first. (2) For engines identified in paragraph (c)(2) of this AD, at the next piece-part exposure after the effective date of this AD or before the affected HPT stage 2 disk exceeds the cyclic removal threshold listed in Table 2 of GE GEnx-1B SB 72-0542 R00, whichever occurs first. (3) For engines identified in paragraph (c)(3) of this AD, at the next piece-part exposure after the effective date of this AD or before the affected HPT stage 1 disk exceeds the cyclic removal threshold listed in Table 1 of GE GEnx-2B SB 72-0471 R00, whichever occurs first. (4) For engines identified in paragraph (c)(4) of this AD, at the next piece-part exposure after the effective date of this AD or before the affected HPT stage 2 disk exceeds the cyclic removal threshold listed in Table 2 of GE GEnx-2B SB 72-0471 R00, whichever occurs first.
Unsafe condition
This AD was prompted by a manufacturer investigation that revealed certain HPT stage 1 disks and HPT stage 2 disks were manufactured from powder metal material suspected to contain iron inclusion. The FAA is issuing this AD to prevent premature fracture and uncontained failure. The unsafe condition, if not addressed, could result in uncontained debris release, damage to the engine, and damage to the airplane.
Affected ADs
None.
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