2024-11-03: Turbine Engine

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: 2024-11-03 International Aero Engines, AG: Amendment 39-22764; Docket No. FAA-2024-0041; Project Identifier AD-2024-00032-E. (a) Effective Date This airworthiness directive (AD) is effective June 26, 2024. (b) Affected ADs This AD is related to AD 2022-02-09, Amendment 39-21906 (87 FR 7029, February 8, 2022) (AD 2022-02-09). (c) Applicability This AD applies to International Aero Engines, AG (IAE AG) Model V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, V2531-E5, and V2533-A5 engines. (d) Subject Joint Aircraft System Component (JASC) Code 7230, Turbine Engine. (e) Unsafe Condition This AD was prompted by an analysis of an event involving an International Aero Engines, LLC Model PW1127GA-JM engine, which experienced failure of a high-pressure compressor 7th-stage integrally bladed rotor that resulted in an engine shutdown and aborted takeoff. The FAA is issuing this AD to prevent failure of the high-pressure turbine (HPT) 1st-stage hub and HPT 2nd-stage hub. The unsafe condition, if not addressed, could result in uncontained hub failure, release of high-energy debris, damage to the engine, damage to the airplane, and loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For engines with an installed part, part number (P/N), and serial number (S/N) listed in Table 1 to paragraph (g)(1) of this AD, with no angled ultrasonic inspection (AUSI) performed, at the next engine shop visit after the effective date of this AD before exceeding the applicable cycle limit specified in Table 1 to paragraph (g)(1) of this AD, perform an AUSI of the affected parts for cracks in accordance with the applicable service information listed in Table 1 to paragraph (g)(1) of this AD. Table 1 to Paragraph ( g )(1)-AUSI Compliance Times Part Table S/N is listed in Previously operated in high-thrust model engine Flight cycle (FC) limit from the effective date of this AD Applicable service information (see paragraph (l)(2) of this AD) HPT 1st-stage hub P/N 2A5001 Table 1 of IAE AG Non-Modification Service Bulletin V2500-ENG-72-0720, dated November 20, 2023 (IAE AG NMSB V2500-ENG-72-0720) Yes 100 FCs Accomplishment Instructions, paragraph 5., of IAE AG NMSB V2500-ENG-72-0720. HPT 1st-stage hub P/N 2A5001 Table 1 of Pratt & Whitney (PW) Special Instruction No. 189F-23, dated November 20, 2023 (PW SI No. 189F-23), which only applies to the IAE AG V2531-E5 Model engine Yes 100 FCs Accomplishment Instructions, paragraph 5., of PW SI No. 189F-23, which only applies to the IAE AG V2531-E5 Model engine. HPT 1st-stage hub P/N 2A5001 Table 1 of IAE AG NMSB V2500-ENG-72-0720 No 700 FCs Accomplishment Instructions, paragraph 5., of IAE AG NMSB V2500-ENG-72-0720. HPT 2nd-stage hub P/N 2A4802 Table 2 of IAE AG NMSB V2500-ENG-72-0720 Yes 800 FCs Accomplishment Instructions, paragraph 6., of IAE AG NMSB V2500-ENG-72-0720. HPT 2nd-stage hub P/N 2A4802 Table 2 PW SI No. 189F-23, which only applies to the IAE AG V2531-E5 Model engine Yes 800 FCs Accomplishment Instructions, paragraph 6., of PW SI No. 189F-23, which only applies to the IAE AG V2531-E5 Model engine. HPT 2nd-stage hub P/N 2A4802 Table 2 of IAE AG NMSB V2500-ENG-72-0720 No 1100 FCs Accomplishment Instructions, paragraph 6., of IAE AG NMSB V2500-ENG-72-0720. (2) For parts inspected in accordance with paragraph (g)(1) of this AD, or for AUSI inspected parts installed on or after November 1, 2023, within 4,000 FCs from accomplishment of the AUSI or at the next HPT module removal after the AUSI, whichever occurs first, remove the part from service and replace with a part eligible for installation. (3) If any crack is found during the inspections required by paragraphs (g)(1) of this AD, before further flight, remove the affected part from service and replace with a part eligible for installation. (4) For engines with an AUSI inspected part installed prior to November 1, 2023, having a P/N and S/N listed in Table 2 to paragraph (g)(4) of this AD, at the next HPT module removal after the effective date of this AD, but before exceeding the applicable cycle limit specified in Table 2 to paragraph (g)(4) of this AD, remove the affected part from service and replace with a part eligible for installation. Table 2 to Paragraph ( g )(4)-Part Replacement Compliance Times Part Table S/N is listed in Previously operated in high-thrust model engine Flight cycle limit from the effective date of this AD HPT 1st-stage hub P/N 2A5001 Table 1 of IAE AG NMSB V2500-ENG-72-0720 Yes 1,800 FCs. HPT 1st-stage hub P/N 2A5001 Table 1 of PW SI No. 189F-23, which only applies to the IAE AG V2531-E5 Model engine Yes 1,800 FCs. HPT 1st-stage hub P/N 2A5001 Table 1 of IAE AG NMSB V2500-ENG-72-0720 No 2,800 FCs. HPT 2nd-stage hub P/N 2A4802 Table 2 of IAE AG NMSB V2500-ENG-72-0720 Yes 3,400 FCs. HPT 2nd-stage hub P/N 2A4802 Table 2 of PW SI No. 189F-23, which only applies to the IAE AG V2531-E5 Model engine Yes 3,400 FCs. HPT 2nd-stage hub P/N 2A4802 Table 2 of IAE AG NMSB V2500-ENG-72-0720 No 3,800 FCs. (5) For engines with an installed part that has a P/N and S/N listed in Table 3 to paragraph (g)(5) of this AD, at the next HPT module removal after the effective date of this AD, but before exceeding the applicable cycle limit specified in Table 3 to paragraph (g)(5) of this AD, remove the affected part from service and replace with a part eligible for installation. Table 3 to Paragraph ( g )(5)-Part Replacement Compliance Times Part Table S/N is listed in Previously operated in high-thrust model engine Flight cycle limit from the effective date of this AD HPT 1st-stage hub P/N 2A5001 Table 3 of IAE AG NMSB V2500-ENG-72-0720 Yes 1,800 FCs. HPT 1st-stage hub P/N 2A5001 Table 3 of IAE AG NMSB V2500-ENG-72-0720 No 2,800 FCs. HPT 2nd-stage hub P/N 2A4802 Table 4 of IAE AG NMSB V2500-ENG-72-0720 Yes 3,400 FCs. HPT 2nd-stage hub P/N 2A4802 Table 4 of IAE AG NMSB V2500-ENG-72-0720 No 3,800 FCs. (h) Definitions (1) For the purposes of this AD, a "part eligible for installation" is an HPT 1st-stage disk or HPT 2nd-stage disk having an S/N that is not listed in IAE AG NMSB V2500-ENG-72-0720 or PW SI No. 189F-23, or an HPT 1st-stage disk or HPT 2nd-stage disk that was not removed from service per the requirements of this AD. (2) For the purposes of this AD, an "HPT module removal" is when the HPT rotor and stator assembly are removed from the engine. (3) For the purposes of this AD, "Previously operated in high-thrust model engine" refers to HPT 1st-stage hubs or HPT 2nd-stage hubs that have operated in an IAE AG Model V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, V2531-E5, or V2533-A5 engine for any duration. (4) For the purposes of this AD, 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, H-P, except for the following situations, which do not constitute an engine shop visit: (i) Separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance. (ii) Engine removal for the purpose of performing field maintenance activities at a maintenance facility in lieu of performing them on-wing. (5) For the purposes of this AD, the date that an AUSI inspected part was installed is the date of the authorized release certification for the shop visit at which the part was first installed after the AUSI was performed. (i) Terminating Action to AD 2022-02-09 Compliance with paragraph (g)(1) of this AD satisfies the requirements of AD 2022-02-09. (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. (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 Carol Nguyen, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238-7655; email: carol.nguyen@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) International Aero Engines AG (IAE AG) Non-Modification Service Bulletin V2500-ENG-72-0720, dated November 20, 2023. (ii) Pratt & Whitney (PW) Special Instruction No. 189F-23, dated November 20, 2023. (3) For IAE AG and PW service information, contact International Aero Engines, AG, 400 Main Street, East Hartford, CT 06118; phone: (860) 565-0140; email: help24@pw.utc.com; website: connect.prattwhitney.com. (4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (817) 222-5110. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email fr.inspection@nara.gov . Issued on May 31, 2024. Suzanne Masterson, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2024-12594 Filed 6-10-24; 8:45 am]BILLING CODE 4910-13-P