Airworthiness Directive · Amendment 39-22909 · Turbine engine compressor section
General Electric Company Engines
This AD applies to General Electric Company (GE) 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, GEnx-2B67, GEnx-2B67B, and GEnx-2B67/P engines with an installed:
(1) Stages 6-10 compressor rotor spool (stages 6-10 spool) having a part number (P/N) and serial number (S/N) listed in paragraph 4, Appendix—A, Table 1 of GE GEnx-1B Service Bulletin 72-0525, R01, dated June 10, 2024 (GEnx-1B SB 72-0525, R01); or
(2) Stages 6-10 spool having a P/N and S/N listed in paragraph 4, Appendix—A, Table 1 of GE GEnx-2B Service Bulletin 72-0460, R01, dated June 10, 2024 (GEnx-2B SB 72-0460, R01).
The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) 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, GEnx-2B67, GEnx-2B67B, and GEnx-2B67/P engines. This AD was prompted by a manufacturer evaluation that determined a lower life limit may be necessary for certain stages 6-10 compressor rotor spools than allowed by the engine shop manual (ESM). This AD requires a one- time inspection of the stages 6-10 spools for previously accomplished blend repairs, a one-time inspection of the blend repairs on the stages 6-10 spools for compliance with the updated allowable limits, and replacement if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
At the next piece-part exposure after the effective date of this AD or before the affected stages 6-10 spool reaches the cyclic removal threshold specified in paragraph 4., Appendix—A, Table 1 of GEnx-1B 72-0525, R01 or GEnx-2B SB 72-0460, R01, as applicable, whichever occurs first, do the following actions:
(1) Inspect the stages 6-10 spool for previously accomplished blend repairs in accordance with the Accomplishment Instructions, paragraph 3.B.(1) of GEnx-1B SB 72-0525, R01 or GEnx-2B SB 72-0460, R01, as applicable.
(2) If during any inspection required by paragraph (g)(1) of this AD, any stages 6-10 spool is found to have a previously accomplished blend repair, before further flight, inspect the blend repair for compliance with the allowable limits in accordance with the Accomplishment Instructions, paragraph 3.B.(2) of GEnx-1B SB 72-0525, R01 or GEnx-2B SB 72-0460, R01, as applicable.
(3) If during any inspection required by paragraph (g)(2) of this AD, any stages 6-10 spool is found to have a previously accomplished blend repair that is not within the allowable limits, before further flight, remove the stages 6-10 spool from service and replace with a part eligible for installation in accordance with the Accomplishment Instructions, paragraph 3.B.(2)(a)1 or 3.B.(2)(b)1 of GEnx-1B SB 72-0525, R01 or GEnx-2B SB 72-0460, R01, as applicable.
For the purposes of this AD:
(1) A “piece-part exposure” is when the stages 6-10 spool is disassembled from the high-pressure compressor rotor assembly.
(2) A “part eligible for installation” is either a stages 6-10 spool that does not have a P/N and S/N identified in paragraph 4, Appendix—A, Table 1 of GEnx-1B 72-0525, R01 or GEnx-2B 72-0460, R01, or a stages 6-10 spool that does have a P/N and S/N identified in paragraph 4, Appendix—A, Table 1 of GEnx-1B 72-0525, R01 or GEnx-2B 72-0460, R01, provided that the affected part is not removed in accordance with paragraph (g)(3) of this AD.
