2025-12-08: Turbine Engine Combustion 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: 2025-12-08 General Electric Company: Amendment 39-23066; Docket No. FAA-2024-2712; Project Identifier AD-2024-00145-E. (a) Effective Date This airworthiness directive (AD) is effective July 23, 2025. (b) Affected ADs None. (c) Applicability This AD applies to the following General Electric Company (GE) Model engines: (1) CF34-8C1, CF34-8C5, CF34-8C5A1, CF34-8C5A2, CF34-8C5A3, and CF34-8C5B1 engines with an installed combustion chamber assembly (CCA) having part number (P/N) 4145T11G08, 4145T11G10, 4180T27G02, 4180T27G04, or 4923T82G02; and (2) CF34-8E2, CF34-8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6, and CF34-8E6A1 engines with an installed CCA having P/N 4145T11G08, 4145T11G09, 4180T27G01, or 4180T27G03. (d) Subject Joint Aircraft System Component (JASC) Code 7240, Turbine Engine Combustion Section. (e) Unsafe Condition This AD was prompted by a predicted reduction in the cyclic life of the CCA forward flange. The FAA is issuing this AD to prevent failure of the CCA. The unsafe condition, if not addressed, could result in failure of the CCA before reaching the published life limit, uncontained release of the CCA, 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) For affected Group 1 engines with an installed CCA having less than 15,000 part cycles since new (PCSN) as of the effective date of this AD, before the accumulation of 28,500 PCSN, remove the CCA from service and replace with P/N 4180T27G08 or a later approved P/N. (2) For affected Group 2 engines with an installed CCA having less than 15,000 PCSN as of the effective date of this AD, before the accumulation of 25,500 PCSN, remove the CCA from service and replace with P/N 4180T27G07 or a later approved P/N. (3) For affected Group 1 and 2 engines with an installed CCA having between 15,000 PCSN and 24,999 PCSN as of the effective date of this AD, before the accumulation of 25,000 PCSN, perform a fluorescent penetrant inspection (FPI) on the forward flange of the CCA for any indications. (4) If no indications are found during the FPI required by paragraph (g)(3) of this AD, within 15,000 part cycles from the date of the FPI, remove the CCA from service and replace with P/N 4180T27G07, 4180T27G08, or a later approved P/N, as applicable. Multiple FPIs of the forward flange prior to the 25,000 PCSN threshold are permitted. However, the affected CCA must be removed from service and replaced no later than 15,000 cycles from the last inspection performed before the 25,000 PCSN threshold. (5) For affected Group 1 and 2 engines with an installed CCA having more than 25,000 PCSN as of the effective date of this AD, at the next engine shop visit after the effective date of this AD, perform an FPI on the forward flange of the CCA for any indications. (6) If no indications are found during the FPI required by paragraph (g)(5) of this AD, within 15,000 part cycles from the date of the FPI and not to exceed 41,100 PCSN, remove the CCA from service and replace with P/N 4180T27G07, 4180T27G08, or a later approved P/N, as applicable. (7) If an indication is found during any FPI required by paragraph (g)(3) or (5) of this AD, before further flight, remove the CCA from service and replace with P/N 4180T27G07, P/N 4180T27G08, or a later approved P/N, as applicable. (h) Definitions For the purpose of this AD: (1) "Group 1 engines" are GE Model CF34-8C1, CF34-8C5, CF34-8C5A1, CF34-8C5A2, CF34-8C5A3, and CF34-8C5B1 engines. (2) "Group 2 engines" are GE Model CF34-8E2, CF34-8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6, and CF34-8E6A1 engines. (3) An "engine shop visit" is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges. (i) Installation Prohibition After the effective date of this AD, do not reinstall any CCAs that were removed as a result of paragraphs (g)(1), (2), (4), (6), and (7) of this AD in any engine. (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 the 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 June 13, 2025. Peter A. White, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2025-11206 Filed 6-17-25; 8:45 am]BILLING CODE 4910-13-P