2025-10-11: Turbine Section

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. 2. The FAA amends § 39.13 by adding the following new airworthiness directive: 2025-10-11 General Electric Company: Amendment 39-23045; Docket No. FAA-2024-2721; Project Identifier AD-2024-00610-E. (a) Effective Date This airworthiness directive (AD) is effective June 24, 2025. (b) Affected ADs None. (c) Applicability This AD applies to General Electric Company (GE) Model CF6-80E1A2, CF6-80E1A3, CF6-80E1A4, and CF6-80E1A4/B engines with an installed high-pressure turbine (HPT) stage 1 disk or HPT stage 2 disk having a part number (P/N) and serial number (S/N) identified in table 1 to paragraph (c) of this AD. Table 1 to Paragraph ( c )-Affected HPT Stage 1 and HPT Stage 2 Disks Part name P/N S/N HPT stage 1 disk 1863M36G06 GWN0GP27. HPT stage 1 disk 1863M36G06 GWN0GPM8. HPT stage 1 disk 1863M36G06 GWN0GP26. HPT stage 1 disk 1863M36G06 TMT5SW61. HPT stage 1 disk 1863M36G06 TMT5SW59. HPT stage 1 disk 1863M36G06 TMT5SW64. HPT stage 1 disk 1863M36G06 TMT5SW82. HPT stage 1 disk 1863M36G06 GWN0GPMG. HPT stage 2 disk 1778M72P05 BTB77100. HPT stage 2 disk 1778M72P05 MUNLD123. HPT stage 2 disk 1778M72P05 MUNLD122. HPT stage 2 disk 1778M72P05 MUN5B794. HPT stage 2 disk 1778M72P05 BTB77102. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by a manufacturer investigation that revealed certain HPT stage 1 and HPT stage 2 disks were subject to iron inclusion introduced during the manufacturing process. The FAA is issuing this AD to prevent fracture and potential uncontained failure of certain HPT stage 1 and HPT stage 2 disks. The unsafe condition, if not addressed, could result in uncontained debris release, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Before further flight after the effective date of this AD, remove any affected HPT stage 1 disk having P/N 1863M36G06 and S/N GWN0GP27 from service and replace with a part eligible for installation. (2) Before further flight after the effective date of this AD, remove any affected HPT stage 2 disk having P/N 1778M72P05 and S/N BTB77100 from service and replace with a part eligible for installation. (3) For affected HPT stage 1 disks identified in table 1 to paragraph (c) of this AD that are not included in paragraph (g)(1) of this AD, at the next piece part exposure or before the affected HPT stage 1 disk exceeds 8,600 cycles since new (CSN), whichever occurs first after the effective date of this AD, remove the affected HPT stage 1 disk from service and replace with a part eligible for installation. (4) For affected HPT stage 2 disks identified in table 1 to paragraph (c) of this AD that are not included in paragraph (g)(2) of this AD, at the next piece part exposure or before the affected HPT stage 2 disk exceeds 12,000 CSN, whichever occurs first after the effective date of this AD, remove the affected HPT stage 2 disk from service and replace with a part eligible for installation. (h) Definitions For the purpose of this AD: (1) A "part eligible for installation" is any HPT stage 1 disk or HPT stage 2 disk that does not have a P/N and S/N identified in table 1 to paragraph (c) of this AD. (2) A "piece part exposure" is when the affected part is removed from the engine and completely disassembled. (i) Grace Period for HPT Stage 1 Disk Replacement For affected HPT stage 1 disks having greater than 8,550 CSN on the effective date of this AD, the replacement required by paragraph (g)(3) of this AD may be deferred up to 50 flight cycles after the effective date of this AD. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, AIR-520 Continued Operational Safety Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of AIR-520 Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (k) of this AD and email to: AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (k) Additional Information For more information about this AD, contact Alexei Marqueen, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238-7178; email: alexei.t.marqueen@faa.gov. (l) Material Incorporated by Reference None. Issued on May 15, 2025. Peter A. White, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2025-09007 Filed 5-19-25; 8:45 am]BILLING CODE 4910-13-P