Airworthiness Directives; International Aero Engines, AG Engines, 49094-49099 [2024-12594]

Download as PDF 49094 Federal Register / Vol. 89, No. 113 / Tuesday, June 11, 2024 / Rules and Regulations or lacking a principal inspector, the manager of the local Flight Standards District Office/ certificate holding district office. (i) Additional Information For more information about this AD, contact Doug Rudolph, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (816) 329– 4059; email: doug.rudolph@faa.gov. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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) GippsAero Service Bulletin SB–GA8– 2023–216, Issue 1, dated February 24, 2023. Note 1 to paragraph (j)(2)(i): The date on the first page of this document is February 24, 2023, and the date on the subsequent pages is February 25, 2023. (ii) [Reserved] (3) For service information identified in this AD, contact GA8 Airvan (Pty) Ltd, GippsAero Technical Services, P.O. Box 881, Morwell, Victoria 3840, Australia; phone: +61 (0)3 5172 1200; email: TECHPUBS@ gippsaero.com.au; website: gippsaero.com.au. (4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. 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, isit www.archives.gov/federal-register/cfr/ibrlocations or email fr.inspection@nara.gov. Issued on May 22, 2024. James D. Foltz, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024–12588 Filed 6–10–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–0041; Project Identifier AD–2024–00032–E; Amendment 39–22764; AD 2024–11–03] khammond on DSKJM1Z7X2PROD with RULES RIN 2120–AA64 Airworthiness Directives; International Aero Engines, AG Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain SUMMARY: VerDate Sep<11>2014 15:56 Jun 10, 2024 Jkt 262001 International Aero Engines, AG (IAE AG) Model V2500 engines. This AD was prompted by an analysis of an event involving an International Aero Engines, LLC (IAE LLC) Model PW1127GA–JM engine, which experienced a highpressure compressor (HPC) 7th-stage integrally bladed rotor (IBR–7) separation that resulted in an aborted takeoff. This AD requires performing an angled ultrasonic inspection (AUSI) of certain high-pressure turbine (HPT) 1ststage hubs and HPT 2nd-stage hubs for cracks and replacing if necessary. This AD also requires accelerated replacement of certain HPT 1st-stage hubs and HPT 2nd-stage hubs. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 26, 2024. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 26, 2024. ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2024–0041; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. Material Incorporated by Reference: • For 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. • 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. FOR FURTHER INFORMATION CONTACT: Carol Nguyen, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238– 7655; email: carol.nguyen@faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain IAE AG Model V2500 engines. The NPRM published in the Federal Register on February 5, 2024 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 (89 FR 7636). The NPRM was prompted by an event on December 24, 2022, when an Airbus Model A320neo airplane, powered by IAE LLC Model PW1127GA–JM engines, experienced a failure of the HPC IBR–7 that resulted in an engine shutdown and aborted takeoff. Following this event, the manufacturer conducted a records review of production and field-returned parts and re-evaluated their engineering analysis methodology. The new analysis found that the failure of the HPC IBR– 7 was caused by a nickel powdered metal anomaly, similar in nature to an anomaly previously observed on March 18, 2020, when an Airbus Model A321– 231 airplane, powered by IAE AG Model V2533–A5 engines, experienced an uncontained HPT 1st-stage hub failure that resulted in high-energy debris penetrating the engine cowling. The analysis also concluded that there is an increased risk of failure for a subpopulation of HPT 1st-stage hubs and HPT 2nd-stage hubs that were manufactured from the same production campaign (a batch of nickel powdered metal) as the HPT 1st-stage hub that failed on March 18, 2020; these parts have a higher likelihood of containing the nickel powdered metal anomaly and are susceptible to failure much earlier than previously determined. In the NPRM, the FAA proposed to require performing an AUSI of certain HPT 1ststage hubs and HPT 2nd-stage hubs and, depending on the results of the inspections, replacing the HPT 1st-stage hubs or HPT 2nd-stage hubs. The FAA also proposed to require accelerated replacement of certain HPT 1st-stage hubs and HPT 2nd-stage hubs. The FAA is issuing this AD to address the unsafe condition on these products. Discussion of Final Airworthiness Directive Comments The FAA received comments from 14 commenters, including the Air Line Pilots Association, International (ALPA); JetBlue Airways (JetBlue); Lufthansa Technik AG (Lufthansa); MTU Maintenance Hannover GmbH; MTU Maintenance Zhuhai Co. Ltd; Pratt & Whitney (PW); Turkish Engine Center (TEC); United Airlines; five anonymous commenters; and an individual commenter. ALPA, United Airlines, the individual commenter, and one anonymous commenter supported the proposed AD without change. Ten commenters requested changes to the proposed AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. E:\FR\FM\11JNR1.SGM 11JNR1 Federal Register / Vol. 89, No. 113 / Tuesday, June 11, 2024 / Rules and Regulations Request To Clarify Affected Parts Two anonymous commenters requested that the FAA clarify if HPT hubs that were produced before 2020 are part of the affected subpopulation if they were installed in January of 2019 or February of 2019 and had not accumulated more than 1,200 flight cycles (FCs). The FAA clarifies that the affected population was manufactured from the same production campaign (a batch of nickel powdered metal) as the HPT 1ststage hub that failed on March 18, 2020. The FAA notes that those affected parts are defined by serial number within the service information documents that are incorporated by reference in this AD. The FAA did not change this AD as a result of these comments. Request To Clarify AUSI for Parts Removed From Service An anonymous commenter requested that the FAA change the proposed AD to clarify if removal of the affected part from service and replacement with a part eligible for installation is an acceptable alternative to performing the AUSI required by paragraph (g)(1) of the proposed AD. The commenter noted that affected parts may be proactively replaced or found unserviceable before the AUSI is required. The FAA disagrees with the request to change the AD because the AUSI required by paragraph (g)(1) of the proposed AD only applies to ‘‘affected parts.’’ If the part has been replaced with a part ‘‘eligible for installation,’’ then it is not an ‘‘affected part’’ and the AUSI is not required. The FAA did not change this AD as a result of this comment. khammond on DSKJM1Z7X2PROD with RULES Request To Clarify Start Date for FC Accumulation An anonymous commenter requested that the FAA clarify the point or date from which FCs should be counted in order to remain compliant with the proposed AD. The commenter noted that in Table 1 to Paragraph (g)(1) of the proposed AD, the AUSI compliance times are specified in terms of FCs, and for the HPT 1st-stage hub with Part Number (P/N) 2A5001, the compliance requirement is based on 100 FCs from a specific reference point. The FAA clarifies that the FC count for AUSI compliance times begins on the effective date of this AD. The FAA has also changed the fourth column header of Table 1 to Paragraph (g)(1), Table 2 to Paragraph (g)(4), and Table 3 to Paragraph (g)(5) of this AD to read as follows: ‘‘Flight cycle (FC) limit from the effective date of this AD.’’ VerDate Sep<11>2014 15:56 Jun 10, 2024 Jkt 262001 Request To Account for Inability To Obtain Special Instruction JetBlue requested that the FAA do one of the following: (1) remove the reference to PW Special Instruction No. 189F–23, dated November 20, 2023 (PW SI No. 189F– 23), from the effectivity of the affected parts listed in Table 1 to Paragraph (g)(1) and Table 2 to Paragraph (g)(4) of this AD; or (2) have IAE LLC revise IAE AG NonModification Service Bulletin (NMSB) V2500–ENG–72–0720, dated November 20, 2023 (V2500–ENG–72–0720) to provide the list of the affected P/Ns and serial numbers of the hubs mentioned in PW SI No. 189F–23; or (3) list all affected hubs within the AD. JetBlue noted that they were unable to obtain PW SI No. 189F–23 from IAE LLC because it relates to a military program and there are concerns about the inadvertent release of data. The FAA disagrees with the request because PW SI No. 189F–23 applies to the V2531–E5 engine model only, and therefore IAE only provides PW SI No. 189F–23 to those owning or operating the product. The FAA notes that material that is incorporated by reference in airworthiness directives can be accessed by the means identified in the ADDRESSES section. For clarity, the FAA added the phrase ‘‘which only applies to the IAE AG V2531–E5 Model engine’’ at the end of each reference to the service bulletin, except for paragraph (l), Material Incorporated by Reference, of the final rule. Request To Adjust Compliance Times JetBlue requested that the FAA adjust the compliance times for Table 1 to Paragraph (g)(1), Table 2 to Paragraph (g)(4), and Table 3 to Paragraph (g)(5) of this AD to match the drawdown period of IAE AG NMSB V2500–ENG–72–0720. JetBlue noted that IAE AG NMSB V2500–ENG–72–0720 provides an additional 200 FCs and is based on an effective date of January 1, 2024, while the proposed AD provides 200 FCs less and is based on the effective date of the AD. JetBlue also noted that it planned the engine removal schedule based on the drawdown of IAE AG NMSB V2500– ENG–72–0720, including working with the engine shops for induction slots and spare engines (including obtaining lease engines). The FAA disagrees with the request because the drawdown times for IAE AG NMSB V2500–ENG–72–0720 started on January 1, 2024, and the FAA reduced the compliance time for the AUSIs required by this AD in order to better PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 49095 align with the control program. The FAA did not change this AD as a result of this comment. Comment Regarding Low Cost Estimate JetBlue commented that the estimated cost of compliance provided in the proposed AD is not realistic and would be only achievable for a new engine or engine just returning to the shop. JetBlue also noted that the estimated cost would have great financial impact on operators, and the manufacturer is not providing a support program to address this. The FAA disagrees that the estimated cost in the AD is unrealistic. The FAA based its estimated cost of compliance on the work-hours and parts costs from the manufacturer to perform the required actions. The commenter did not provide specifics on which cost estimates were incorrect and what would be considered realistic. The FAA did not change this AD as a result of this comment. Comment Regarding Parts Eligible for Installation Lufthansa commented that parts considered eligible for installation should not be limited to the disk S/Ns that are not listed in V2500–ENG–72– 0720 or PW SI No. 189F–23. Lufthansa noted that disk S/Ns listed in those documents that have passed AUSI are also eligible for installation and need to be removed within 4,000 FCs from accomplishment of the AUSI or at the next HPT module removal after the AUSI. The FAA agrees to change paragraph (h)(1) of this AD to include parts that were not removed from service as a result of the required actions of this AD as ‘‘parts eligible for installation.’’ Request To Redefine AUSI Inspected Part Installation Date TEC requested that the FAA change the definition of the date that an AUSI inspected part was installed in paragraph (h)(5) of the proposed AD from ‘‘the date of the authorized release certification for the shop visit at which the part was first installed after the AUSI was performed’’ to ‘‘the HPT hub release certificate date.’’ TEC noted that it is possible for two HPT hubs to be inspected on the same date and be installed on different engines. Since release dates of these engines can differ, it is possible for different replacement compliance times to apply to parts that were inspected on the same day. The FAA disagrees with the request to change the definition of the date that an AUSI inspected part was installed. The FAA acknowledges that AUSI E:\FR\FM\11JNR1.SGM 11JNR1 49096 Federal Register / Vol. 89, No. 113 / Tuesday, June 11, 2024 / Rules and Regulations compliance times will vary depending on when the AUSI inspected part was installed, and this was taken into consideration in order to manage shop visit capacity. The FAA did not change this AD as a result of this comment. Request To Revise Paragraph (g)(1) of the Proposed AD MTU Maintenance Hannover GmbH and PW requested that the FAA revise paragraph (g)(1) of the proposed AD to remove mention of AUSI inspected parts installed on or after November 1, 2023. MTU Maintenance Hannover GmbH requested that the phrase ‘‘or the AUSI inspected part was installed on or after November 1, 2023’’ be removed from paragraph (g)(1) of the proposed AD entirely, and PW requested that the FAA change the language from ‘‘or the AUSI inspected part was installed on or after November 1, 2023’’ to ‘‘before November 1, 2023.’’ JetBlue, MTU Maintenance Hannover GmbH, and PW all noted that the current language in paragraph (g)(1) of the proposed AD could cause an early engine removal by requiring a second AUSI inspection on hubs that had been previously AUSI inspected. The FAA agrees to revise paragraph (g)(1) of this AD to prevent the potential requirement of performing a second AUSI on hubs that had an AUSI performed on or after November 1, 2023. khammond on DSKJM1Z7X2PROD with RULES Request To Revise Paragraph (g)(2) of the AD MTU Maintenance Hannover GmbH and PW requested that the FAA revise paragraph (g)(2) of the proposed AD to clarify the required actions for engines with AUSI inspected parts that were installed on or after November 1, 2023. MTU Maintenance Hannover GmbH requested that the FAA revise paragraph (g)(2) to read as follows: ‘‘For engines with an AUSI inspected part installed on or after November 1, 2023 or for parts inspected in accordance with paragraph (g)(1) of this AD, within 4,000 FCs from accomplishment of the AUSI required by paragraph (g)(1) of this AD or at the next HPT module removal after the AUSI required by paragraph (g)(1) of this AD, whichever occurs first, remove the part from service and replace with a part eligible for installation.’’ PW requested that the FAA revise paragraph (g)(2) of the proposed AD to read as follows: ‘‘For parts inspected in accordance with paragraph (g)(1) of this AD, or for parts previously AUSI inspected and installed on or after November 1, 2023, within 4,000 FCs from accomplishment of the AUSI VerDate Sep<11>2014 15:56 Jun 10, 2024 Jkt 262001 required by paragraph (g)(1) of this AD or at the next HPT module removal after the AUSI required by paragraph (g)(1) of this AD, whichever occurs first, remove the part from service and replace with a part eligible for installation.’’ PW noted that the intent is to inspect everything, and any part inspected after November 1, 2023 will be removed at 4,000 FCs. The FAA agrees to revise paragraph (g)(2) of this AD to clarify the required actions for engines with AUSI inspected parts that were installed on or after November 1, 2023. Request To Clarify Compliance Time for High-Thrust Engines MTU Maintenance Zhuhai Co. Ltd requested that the FAA clarify the part replacement compliance time in Table 2 to Paragraph (g)(4) of the proposed AD for a part not previously operated in a high-thrust engine model that has its engine rating changed to a high-thrust rating without any disassembly or removal of the HPT module. The FAA clarifies that after the initial flight in the newly rated high-thrust engine, the part is considered to have previously operated in a high-thrust engine and it will be required to use the lower cycle limits. For example, the HPT 1st-stage hub will need to be removed at 1,800 FCs after the effective date of the AD because it is now operating in a high-thrust engine. The FAA notes that the removal or nonremoval of the HPT module at shop visit would not have an effect on this scenario as these are considered the new replacement cycle limits for the affected parts on the effective date of the AD. The FAA has revised paragraph (h)(3) of this AD by removing the second instance of the word ‘‘previously’’ from the definition in order to avoid potential misinterpretation. Conclusion The FAA reviewed the relevant data, considered any comments received, and determined that air safety requires adopting this AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. Except for minor editorial changes, and any other changes described previously, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. 20, 2023; and PW Special Instruction No. 189F–23, dated November 20, 2023, which only applies to the IAE AG V2531–E5 Model engine. This service information specifies procedures for performing an AUSI for cracks on affected HPT 1st-stage hubs and HPT 2nd-stage hubs. This service information also specifies the list of affected HPT 1st-stage hubs and HPT 2nd-stage hubs, identified by part number and serial number, installed on certain IAE AG engines. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Interim Action The FAA considers this AD to be an interim action. The unsafe condition is still under investigation by the manufacturer and, depending on the results of that investigation, the FAA may consider further rulemaking action. Justification for Determination of the Effective Date Section 553(d) of the Administrative Procedure Act (APA) (5 U.S.C. 551 et seq.) authorizes agencies to make rules effective in less than thirty days, upon a finding of ‘‘good cause.’’ The FAA has found that the risk to the flying public justifies a shortened effective date for this rule due to powdered metal anomalies in HPT 1st-stage hubs and HPT 2nd-stage hubs that could lead to premature fracture and uncontained failure, which could lead to the release of high-energy debris, damage to the engine, damage to the airplane, and loss of the airplane. The longer these parts remain in service, the higher the probability of failure. Accordingly, the FAA finds that good cause exists pursuant to 5 U.S.C. 553(d) for making this amendment effective in less than 30 days. Costs of Compliance Related Service Information Under 1 CFR Part 51 The FAA estimates that this AD affects 116 engines installed on airplanes of U.S. registry. The FAA estimates that 40 engines need an AUSI of the HPT 1st-stage hub; 40 engines need an AUSI of the HPT 2nd-stage hub; 67 engines need replacement of the HPT 1st-stage hub; and 49 engines need replacement of the HPT 2nd-stage hub. The FAA reviewed IAE AG NMSB V2500–ENG–72–0720, dated November The FAA estimates the following costs to comply with this AD: PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\11JNR1.SGM 11JNR1 Federal Register / Vol. 89, No. 113 / Tuesday, June 11, 2024 / Rules and Regulations 49097 ESTIMATED COSTS Action Labor cost AUSI of HPT 1st-stage hub ............................ AUSI of HPT 2nd-stage hub ........................... Replace HPT 1st-stage hub ........................... Replace HPT 2nd-stage hub .......................... 5 work-hours × $85 per hour = $425 ............. 5 work-hours × $85 per hour = $8,500 .......... 100 work-hours × $85 per hour = $8,500 ...... 100 work-hours × $85 per hour = $8,500 ...... The FAA has included all known costs in its cost estimate. According to the manufacturer, however, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings khammond on DSKJM1Z7X2PROD with RULES This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: VerDate Sep<11>2014 15:56 Jun 10, 2024 Jkt 262001 Parts cost (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 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). PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 Cost per product $0 0 460,000 360,000 $425 425 468,500 368,500 Cost on U.S. operators $17,000 17,000 31,389,500 18,056,500 (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. E:\FR\FM\11JNR1.SGM 11JNR1 49098 Federal Register / Vol. 89, No. 113 / Tuesday, June 11, 2024 / Rules and Regulations TABLE 1 TO PARAGRAPH (g)(1)—AUSI COMPLIANCE TIMES 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) Yes ................. 100 FCs ....................... Accomplishment Instructions, paragraph 5., of IAE AG NMSB V2500–ENG–72–0720. 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 Non-Modification Service Bulletin V2500–ENG–72– 0720, dated November 20, 2023 (IAE AG NMSB V2500–ENG–72– 0720). 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. Table 1 of IAE AG NMSB V2500– ENG–72–0720. No .................. 700 FCs ....................... HPT 2nd-stage hub P/N 2A4802. Table 2 of IAE AG NMSB V2500– ENG–72–0720. Yes ................. 800 FCs ....................... 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 ....................... HPT 2nd-stage hub P/N 2A4802. Table 2 of IAE AG NMSB V2500– ENG–72–0720. No .................. 1100 FCs ..................... Accomplishment Instructions, paragraph 5., of IAE AG NMSB V2500–ENG–72–0720. Accomplishment Instructions, paragraph 6., of IAE AG NMSB V2500–ENG–72–0720. Accomplishment Instructions, paragraph 6., of PW SI No. 189F–23, which only applies to the IAE AG V2531–E5 Model engine. Accomplishment Instructions, paragraph 6., of IAE AG NMSB V2500–ENG–72–0720. Part Table S/N is listed in HPT 1st-stage hub P/N 2A5001. HPT 1st-stage hub P/N 2A5001. (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 khammond on DSKJM1Z7X2PROD with RULES HPT 1st-stage hub P/N 2A5001. HPT 1st-stage hub P/N 2A5001. HPT 1st-stage hub P/N 2A5001. HPT 2nd-stage hub P/N 2A4802. HPT 2nd-stage hub P/N 2A4802. HPT 2nd-stage hub P/N 2A4802. Previously operated in highthrust model engine Table 1 of IAE AG NMSB V2500–ENG–72–0720 ................. Yes ......................................... 1,800 FCs. Table 1 of PW SI No. 189F–23, which only applies to the IAE AG V2531–E5 Model engine. Table 1 of IAE AG NMSB V2500–ENG–72–0720 ................. Yes ......................................... 1,800 FCs. No .......................................... 2,800 FCs. Table 2 of IAE AG NMSB V2500–ENG–72–0720 ................. Yes ......................................... 3,400 FCs. Table 2 of PW SI No. 189F–23, which only applies to the IAE AG V2531–E5 Model engine. Table 2 of IAE AG NMSB V2500–ENG–72–0720 ................. Yes ......................................... 3,400 FCs. 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 VerDate Sep<11>2014 15:56 Jun 10, 2024 Flight cycle limit from the effective date of this AD Table S/N is listed in Part Jkt 262001 this AD, but before exceeding the applicable cycle limit specified in Table 3 to paragraph (g)(5) of this AD, remove the affected part PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 from service and replace with a part eligible for installation. E:\FR\FM\11JNR1.SGM 11JNR1 49099 Federal Register / Vol. 89, No. 113 / Tuesday, June 11, 2024 / Rules and Regulations TABLE 3 TO PARAGRAPH (g)(5)—PART REPLACEMENT COMPLIANCE TIMES HPT 1st-stage hub P/N 2A5001. HPT 1st-stage hub P/N 2A5001. HPT 2nd-stage hub P/N 2A4802. HPT 2nd-stage hub P/N 2A4802. Previously operated in highthrust model engine Table 3 of IAE AG NMSB V2500–ENG–72–0720 ................. Yes ......................................... 1,800 FCs. Table 3 of IAE AG NMSB V2500–ENG–72–0720 ................. No .......................................... 2,800 FCs. Table 4 of IAE AG NMSB V2500–ENG–72–0720 ................. Yes ......................................... 3,400 FCs. 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. khammond on DSKJM1Z7X2PROD with RULES (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. VerDate Sep<11>2014 15:56 Jun 10, 2024 Flight cycle limit from the effective date of this AD Table S/N is listed in Part Jkt 262001 (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. DEPARTMENT OF HOUSING AND URBAN DEVELOPMENT (k) Additional Information [Docket No. FR–6439–C–02] 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. 24 CFR Part 236 RIN 2502–AJ74 Removal of Obsolete Regulations for Section 236 of the National Housing Act; Correction (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 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 Office of the Assistant Secretary for Housing—Federal Housing Commissioner, U.S. Department of Housing and Urban Development (HUD). AGENCY: ACTION: Final rule; correction. HUD is correcting a final rule entitled, ‘‘Removal of Obsolete Regulations for Section 236 of the National Housing Act’’ that published on June 4, 2024, to include the rule’s Regulation Identifier Number (RIN). SUMMARY: DATES: Effective July 5, 2024. FOR FURTHER INFORMATION CONTACT: Aaron Santa Anna, Associate General Counsel for Legislation and Regulations, Department of Housing and Urban Development, 451 7th Street SW, Room 10238, Washington, DC 20410; telephone number 202–708–1793 (this is not a toll-free number). HUD welcomes and is prepared to receive calls from individuals who are deaf or hard of hearing, as well as individuals with speech and communication disabilities. To learn more about how to make an accessible telephone call, please visit https://www.fcc.gov/ consumers/guides/telecommunicationsrelay-service-trs. On June 4, 2024 (89 FR 47849), HUD published a final rule titled ‘‘Removal of Obsolete Regulations for Section 236 of the National Housing Act.’’ The rule did not contain a RIN. This document corrects the final rule to include the RIN. SUPPLEMENTARY INFORMATION: E:\FR\FM\11JNR1.SGM 11JNR1

Agencies

[Federal Register Volume 89, Number 113 (Tuesday, June 11, 2024)]
[Rules and Regulations]
[Pages 49094-49099]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-12594]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-0041; Project Identifier AD-2024-00032-E; 
Amendment 39-22764; AD 2024-11-03]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines, AG Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain International Aero Engines, AG (IAE AG) Model V2500 engines. 
This AD was prompted by an analysis of an event involving an 
International Aero Engines, LLC (IAE LLC) Model PW1127GA-JM engine, 
which experienced a high-pressure compressor (HPC) 7th-stage integrally 
bladed rotor (IBR-7) separation that resulted in an aborted takeoff. 
This AD requires performing an angled ultrasonic inspection (AUSI) of 
certain high-pressure turbine (HPT) 1st-stage hubs and HPT 2nd-stage 
hubs for cracks and replacing if necessary. This AD also requires 
accelerated replacement of certain HPT 1st-stage hubs and HPT 2nd-stage 
hubs. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective June 26, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 26, 
2024.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2024-0041; or in person at Docket Operations between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this final rule, any comments received, and other 
information. The address for Docket Operations is U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
    Material Incorporated by Reference:
     For service information, contact International Aero 
Engines, AG, 400 Main Street, East Hartford, CT 06118; phone: (860) 
565-0140; email: [email protected]; website: connect.prattwhitney.com.
     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.

FOR FURTHER INFORMATION CONTACT: Carol Nguyen, Aviation Safety 
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: 
(781) 238-7655; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to certain IAE AG Model 
V2500 engines. The NPRM published in the Federal Register on February 
5, 2024 (89 FR 7636). The NPRM was prompted by an event on December 24, 
2022, when an Airbus Model A320neo airplane, powered by IAE LLC Model 
PW1127GA-JM engines, experienced a failure of the HPC IBR-7 that 
resulted in an engine shutdown and aborted take-off. Following this 
event, the manufacturer conducted a records review of production and 
field-returned parts and re-evaluated their engineering analysis 
methodology. The new analysis found that the failure of the HPC IBR-7 
was caused by a nickel powdered metal anomaly, similar in nature to an 
anomaly previously observed on March 18, 2020, when an Airbus Model 
A321-231 airplane, powered by IAE AG Model V2533-A5 engines, 
experienced an uncontained HPT 1st-stage hub failure that resulted in 
high-energy debris penetrating the engine cowling. The analysis also 
concluded that there is an increased risk of failure for a 
subpopulation of HPT 1st-stage hubs and HPT 2nd-stage hubs that were 
manufactured from the same production campaign (a batch of nickel 
powdered metal) as the HPT 1st-stage hub that failed on March 18, 2020; 
these parts have a higher likelihood of containing the nickel powdered 
metal anomaly and are susceptible to failure much earlier than 
previously determined. In the NPRM, the FAA proposed to require 
performing an AUSI of certain HPT 1st-stage hubs and HPT 2nd-stage hubs 
and, depending on the results of the inspections, replacing the HPT 
1st-stage hubs or HPT 2nd-stage hubs. The FAA also proposed to require 
accelerated replacement of certain HPT 1st-stage hubs and HPT 2nd-stage 
hubs. The FAA is issuing this AD to address the unsafe condition on 
these products.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from 14 commenters, including the Air 
Line Pilots Association, International (ALPA); JetBlue Airways 
(JetBlue); Lufthansa Technik AG (Lufthansa); MTU Maintenance Hannover 
GmbH; MTU Maintenance Zhuhai Co. Ltd; Pratt & Whitney (PW); Turkish 
Engine Center (TEC); United Airlines; five anonymous commenters; and an 
individual commenter. ALPA, United Airlines, the individual commenter, 
and one anonymous commenter supported the proposed AD without change. 
Ten commenters requested changes to the proposed AD. The following 
presents the comments received on the NPRM and the FAA's response to 
each comment.

[[Page 49095]]

Request To Clarify Affected Parts

    Two anonymous commenters requested that the FAA clarify if HPT hubs 
that were produced before 2020 are part of the affected subpopulation 
if they were installed in January of 2019 or February of 2019 and had 
not accumulated more than 1,200 flight cycles (FCs).
    The FAA clarifies that the affected population was manufactured 
from the same production campaign (a batch of nickel powdered metal) as 
the HPT 1st-stage hub that failed on March 18, 2020. The FAA notes that 
those affected parts are defined by serial number within the service 
information documents that are incorporated by reference in this AD. 
The FAA did not change this AD as a result of these comments.

Request To Clarify AUSI for Parts Removed From Service

    An anonymous commenter requested that the FAA change the proposed 
AD to clarify if removal of the affected part from service and 
replacement with a part eligible for installation is an acceptable 
alternative to performing the AUSI required by paragraph (g)(1) of the 
proposed AD. The commenter noted that affected parts may be proactively 
replaced or found unserviceable before the AUSI is required.
    The FAA disagrees with the request to change the AD because the 
AUSI required by paragraph (g)(1) of the proposed AD only applies to 
``affected parts.'' If the part has been replaced with a part 
``eligible for installation,'' then it is not an ``affected part'' and 
the AUSI is not required. The FAA did not change this AD as a result of 
this comment.

Request To Clarify Start Date for FC Accumulation

    An anonymous commenter requested that the FAA clarify the point or 
date from which FCs should be counted in order to remain compliant with 
the proposed AD. The commenter noted that in Table 1 to Paragraph 
(g)(1) of the proposed AD, the AUSI compliance times are specified in 
terms of FCs, and for the HPT 1st-stage hub with Part Number (P/N) 
2A5001, the compliance requirement is based on 100 FCs from a specific 
reference point.
    The FAA clarifies that the FC count for AUSI compliance times 
begins on the effective date of this AD. The FAA has also changed the 
fourth column header of Table 1 to Paragraph (g)(1), Table 2 to 
Paragraph (g)(4), and Table 3 to Paragraph (g)(5) of this AD to read as 
follows: ``Flight cycle (FC) limit from the effective date of this 
AD.''

Request To Account for Inability To Obtain Special Instruction

    JetBlue requested that the FAA do one of the following:
    (1) remove the reference to PW Special Instruction No. 189F-23, 
dated November 20, 2023 (PW SI No. 189F-23), from the effectivity of 
the affected parts listed in Table 1 to Paragraph (g)(1) and Table 2 to 
Paragraph (g)(4) of this AD; or
    (2) have IAE LLC revise IAE AG Non-Modification Service Bulletin 
(NMSB) V2500-ENG-72-0720, dated November 20, 2023 (V2500-ENG-72-0720) 
to provide the list of the affected P/Ns and serial numbers of the hubs 
mentioned in PW SI No. 189F-23; or
    (3) list all affected hubs within the AD.
    JetBlue noted that they were unable to obtain PW SI No. 189F-23 
from IAE LLC because it relates to a military program and there are 
concerns about the inadvertent release of data.
    The FAA disagrees with the request because PW SI No. 189F-23 
applies to the V2531-E5 engine model only, and therefore IAE only 
provides PW SI No. 189F-23 to those owning or operating the product. 
The FAA notes that material that is incorporated by reference in 
airworthiness directives can be accessed by the means identified in the 
ADDRESSES section. For clarity, the FAA added the phrase ``which only 
applies to the IAE AG V2531-E5 Model engine'' at the end of each 
reference to the service bulletin, except for paragraph (l), Material 
Incorporated by Reference, of the final rule.

Request To Adjust Compliance Times

    JetBlue requested that the FAA adjust the compliance times for 
Table 1 to Paragraph (g)(1), Table 2 to Paragraph (g)(4), and Table 3 
to Paragraph (g)(5) of this AD to match the drawdown period of IAE AG 
NMSB V2500-ENG-72-0720. JetBlue noted that IAE AG NMSB V2500-ENG-72-
0720 provides an additional 200 FCs and is based on an effective date 
of January 1, 2024, while the proposed AD provides 200 FCs less and is 
based on the effective date of the AD. JetBlue also noted that it 
planned the engine removal schedule based on the drawdown of IAE AG 
NMSB V2500-ENG-72-0720, including working with the engine shops for 
induction slots and spare engines (including obtaining lease engines).
    The FAA disagrees with the request because the drawdown times for 
IAE AG NMSB V2500-ENG-72-0720 started on January 1, 2024, and the FAA 
reduced the compliance time for the AUSIs required by this AD in order 
to better align with the control program. The FAA did not change this 
AD as a result of this comment.

Comment Regarding Low Cost Estimate

    JetBlue commented that the estimated cost of compliance provided in 
the proposed AD is not realistic and would be only achievable for a new 
engine or engine just returning to the shop. JetBlue also noted that 
the estimated cost would have great financial impact on operators, and 
the manufacturer is not providing a support program to address this.
    The FAA disagrees that the estimated cost in the AD is unrealistic. 
The FAA based its estimated cost of compliance on the work-hours and 
parts costs from the manufacturer to perform the required actions. The 
commenter did not provide specifics on which cost estimates were 
incorrect and what would be considered realistic. The FAA did not 
change this AD as a result of this comment.

Comment Regarding Parts Eligible for Installation

    Lufthansa commented that parts considered eligible for installation 
should not be limited to the disk S/Ns that are not listed in V2500-
ENG-72-0720 or PW SI No. 189F-23. Lufthansa noted that disk S/Ns listed 
in those documents that have passed AUSI are also eligible for 
installation and need to be removed within 4,000 FCs from 
accomplishment of the AUSI or at the next HPT module removal after the 
AUSI.
    The FAA agrees to change paragraph (h)(1) of this AD to include 
parts that were not removed from service as a result of the required 
actions of this AD as ``parts eligible for installation.''

Request To Redefine AUSI Inspected Part Installation Date

    TEC requested that the FAA change the definition of the date that 
an AUSI inspected part was installed in paragraph (h)(5) of the 
proposed AD from ``the date of the authorized release certification for 
the shop visit at which the part was first installed after the AUSI was 
performed'' to ``the HPT hub release certificate date.'' TEC noted that 
it is possible for two HPT hubs to be inspected on the same date and be 
installed on different engines. Since release dates of these engines 
can differ, it is possible for different replacement compliance times 
to apply to parts that were inspected on the same day.
    The FAA disagrees with the request to change the definition of the 
date that an AUSI inspected part was installed. The FAA acknowledges 
that AUSI

[[Page 49096]]

compliance times will vary depending on when the AUSI inspected part 
was installed, and this was taken into consideration in order to manage 
shop visit capacity. The FAA did not change this AD as a result of this 
comment.

Request To Revise Paragraph (g)(1) of the Proposed AD

    MTU Maintenance Hannover GmbH and PW requested that the FAA revise 
paragraph (g)(1) of the proposed AD to remove mention of AUSI inspected 
parts installed on or after November 1, 2023. MTU Maintenance Hannover 
GmbH requested that the phrase ``or the AUSI inspected part was 
installed on or after November 1, 2023'' be removed from paragraph 
(g)(1) of the proposed AD entirely, and PW requested that the FAA 
change the language from ``or the AUSI inspected part was installed on 
or after November 1, 2023'' to ``before November 1, 2023.'' JetBlue, 
MTU Maintenance Hannover GmbH, and PW all noted that the current 
language in paragraph (g)(1) of the proposed AD could cause an early 
engine removal by requiring a second AUSI inspection on hubs that had 
been previously AUSI inspected.
    The FAA agrees to revise paragraph (g)(1) of this AD to prevent the 
potential requirement of performing a second AUSI on hubs that had an 
AUSI performed on or after November 1, 2023.

Request To Revise Paragraph (g)(2) of the AD

    MTU Maintenance Hannover GmbH and PW requested that the FAA revise 
paragraph (g)(2) of the proposed AD to clarify the required actions for 
engines with AUSI inspected parts that were installed on or after 
November 1, 2023. MTU Maintenance Hannover GmbH requested that the FAA 
revise paragraph (g)(2) to read as follows: ``For engines with an AUSI 
inspected part installed on or after November 1, 2023 or for parts 
inspected in accordance with paragraph (g)(1) of this AD, within 4,000 
FCs from accomplishment of the AUSI required by paragraph (g)(1) of 
this AD or at the next HPT module removal after the AUSI required by 
paragraph (g)(1) of this AD, whichever occurs first, remove the part 
from service and replace with a part eligible for installation.'' PW 
requested that the FAA revise paragraph (g)(2) of the proposed AD to 
read as follows: ``For parts inspected in accordance with paragraph 
(g)(1) of this AD, or for parts previously AUSI inspected and installed 
on or after November 1, 2023, within 4,000 FCs from accomplishment of 
the AUSI required by paragraph (g)(1) of this AD or at the next HPT 
module removal after the AUSI required by paragraph (g)(1) of this AD, 
whichever occurs first, remove the part from service and replace with a 
part eligible for installation.'' PW noted that the intent is to 
inspect everything, and any part inspected after November 1, 2023 will 
be removed at 4,000 FCs.
    The FAA agrees to revise paragraph (g)(2) of this AD to clarify the 
required actions for engines with AUSI inspected parts that were 
installed on or after November 1, 2023.

Request To Clarify Compliance Time for High-Thrust Engines

    MTU Maintenance Zhuhai Co. Ltd requested that the FAA clarify the 
part replacement compliance time in Table 2 to Paragraph (g)(4) of the 
proposed AD for a part not previously operated in a high-thrust engine 
model that has its engine rating changed to a high-thrust rating 
without any disassembly or removal of the HPT module.
    The FAA clarifies that after the initial flight in the newly rated 
high-thrust engine, the part is considered to have previously operated 
in a high-thrust engine and it will be required to use the lower cycle 
limits. For example, the HPT 1st-stage hub will need to be removed at 
1,800 FCs after the effective date of the AD because it is now 
operating in a high-thrust engine. The FAA notes that the removal or 
non-removal of the HPT module at shop visit would not have an effect on 
this scenario as these are considered the new replacement cycle limits 
for the affected parts on the effective date of the AD. The FAA has 
revised paragraph (h)(3) of this AD by removing the second instance of 
the word ``previously'' from the definition in order to avoid potential 
misinterpretation.

Conclusion

    The FAA reviewed the relevant data, considered any comments 
received, and determined that air safety requires adopting this AD as 
proposed. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these products. Except for minor editorial changes, and 
any other changes described previously, this AD is adopted as proposed 
in the NPRM. None of the changes will increase the economic burden on 
any operator.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed IAE AG NMSB V2500-ENG-72-0720, dated November 20, 
2023; and PW Special Instruction No. 189F-23, dated November 20, 2023, 
which only applies to the IAE AG V2531-E5 Model engine. This service 
information specifies procedures for performing an AUSI for cracks on 
affected HPT 1st-stage hubs and HPT 2nd-stage hubs. This service 
information also specifies the list of affected HPT 1st-stage hubs and 
HPT 2nd-stage hubs, identified by part number and serial number, 
installed on certain IAE AG engines. This service information is 
reasonably available because the interested parties have access to it 
through their normal course of business or by the means identified in 
the ADDRESSES section.

Interim Action

    The FAA considers this AD to be an interim action. The unsafe 
condition is still under investigation by the manufacturer and, 
depending on the results of that investigation, the FAA may consider 
further rulemaking action.

Justification for Determination of the Effective Date

    Section 553(d) of the Administrative Procedure Act (APA) (5 U.S.C. 
551 et seq.) authorizes agencies to make rules effective in less than 
thirty days, upon a finding of ``good cause.'' The FAA has found that 
the risk to the flying public justifies a shortened effective date for 
this rule due to powdered metal anomalies in HPT 1st-stage hubs and HPT 
2nd-stage hubs that could lead to premature fracture and uncontained 
failure, which could lead to the release of high-energy debris, damage 
to the engine, damage to the airplane, and loss of the airplane. The 
longer these parts remain in service, the higher the probability of 
failure. Accordingly, the FAA finds that good cause exists pursuant to 
5 U.S.C. 553(d) for making this amendment effective in less than 30 
days.

Costs of Compliance

    The FAA estimates that this AD affects 116 engines installed on 
airplanes of U.S. registry. The FAA estimates that 40 engines need an 
AUSI of the HPT 1st-stage hub; 40 engines need an AUSI of the HPT 2nd-
stage hub; 67 engines need replacement of the HPT 1st-stage hub; and 49 
engines need replacement of the HPT 2nd-stage hub.
    The FAA estimates the following costs to comply with this AD:

[[Page 49097]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
AUSI of HPT 1st-stage hub.............  5 work-hours x $85 per                $0            $425         $17,000
                                         hour = $425.
AUSI of HPT 2nd-stage hub.............  5 work-hours x $85 per                 0             425          17,000
                                         hour = $8,500.
Replace HPT 1st-stage hub.............  100 work-hours x $85 per         460,000         468,500      31,389,500
                                         hour = $8,500.
Replace HPT 2nd-stage hub.............  100 work-hours x $85 per         360,000         368,500      18,056,500
                                         hour = $8,500.
----------------------------------------------------------------------------------------------------------------

    The FAA has included all known costs in its cost estimate. 
According to the manufacturer, however, some of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected operators.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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.

[[Page 49098]]



                               Table 1 to Paragraph (g)(1)--AUSI Compliance Times
----------------------------------------------------------------------------------------------------------------
                                                                                                   Applicable
                                                      Previously operated   Flight cycle (FC)       service
              Part                  Table S/N is      in high-thrust model    limit from the    information (see
                                      listed in              engine         effective date of   paragraph (l)(2)
                                                                                 this AD          of this AD)
----------------------------------------------------------------------------------------------------------------
HPT 1st-stage hub P/N 2A5001...  Table 1 of IAE AG   Yes..................  100 FCs..........  Accomplishment
                                  Non-Modification                                              Instructions,
                                  Service Bulletin                                              paragraph 5., of
                                  V2500-ENG-72-0720                                             IAE AG NMSB
                                  , dated November                                              V2500-ENG-72-072
                                  20, 2023 (IAE AG                                              0.
                                  NMSB V2500-ENG-72-
                                  0720).
HPT 1st-stage hub P/N 2A5001...  Table 1 of Pratt &  Yes..................  100 FCs..........  Accomplishment
                                  Whitney (PW)                                                  Instructions,
                                  Special                                                       paragraph 5., of
                                  Instruction No.                                               PW SI No. 189F-
                                  189F-23, dated                                                23, which only
                                  November 20, 2023                                             applies to the
                                  (PW SI No. 189F-                                              IAE AG V2531-E5
                                  23), which only                                               Model engine.
                                  applies to the
                                  IAE AG V2531-E5
                                  Model engine.
HPT 1st-stage hub P/N 2A5001...  Table 1 of IAE AG   No...................  700 FCs..........  Accomplishment
                                  NMSB V2500-ENG-72-                                            Instructions,
                                  0720.                                                         paragraph 5., of
                                                                                                IAE AG NMSB
                                                                                                V2500-ENG-72-072
                                                                                                0.
HPT 2nd-stage hub P/N 2A4802...  Table 2 of IAE AG   Yes..................  800 FCs..........  Accomplishment
                                  NMSB V2500-ENG-72-                                            Instructions,
                                  0720.                                                         paragraph 6., of
                                                                                                IAE AG NMSB
                                                                                                V2500-ENG-72-072
                                                                                                0.
HPT 2nd-stage hub P/N 2A4802...  Table 2 PW SI No.   Yes..................  800 FCs..........  Accomplishment
                                  189F-23, which                                                Instructions,
                                  only applies to                                               paragraph 6., of
                                  the IAE AG V2531-                                             PW SI No. 189F-
                                  E5 Model engine.                                              23, which only
                                                                                                applies to the
                                                                                                IAE AG V2531-E5
                                                                                                Model engine.
HPT 2nd-stage hub P/N 2A4802...  Table 2 of IAE AG   No...................  1100 FCs.........  Accomplishment
                                  NMSB V2500-ENG-72-                                            Instructions,
                                  0720.                                                         paragraph 6., of
                                                                                                IAE AG NMSB
                                                                                                V2500-ENG-72-072
                                                                                                0.
----------------------------------------------------------------------------------------------------------------

    (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
----------------------------------------------------------------------------------------------------------------
                                                                 Previously operated    Flight cycle limit from
               Part                   Table S/N is listed in     in high-thrust model    the effective date of
                                                                        engine                  this AD
----------------------------------------------------------------------------------------------------------------
HPT 1st-stage hub P/N 2A5001......  Table 1 of IAE AG NMSB      Yes..................  1,800 FCs.
                                     V2500-ENG-72-0720.
HPT 1st-stage hub P/N 2A5001......  Table 1 of PW SI No. 189F-  Yes..................  1,800 FCs.
                                     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      No...................  2,800 FCs.
                                     V2500-ENG-72-0720.
HPT 2nd-stage hub P/N 2A4802......  Table 2 of IAE AG NMSB      Yes..................  3,400 FCs.
                                     V2500-ENG-72-0720.
HPT 2nd-stage hub P/N 2A4802......  Table 2 of PW SI No. 189F-  Yes..................  3,400 FCs.
                                     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      No...................  3,800 FCs.
                                     V2500-ENG-72-0720.
----------------------------------------------------------------------------------------------------------------

    (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.

[[Page 49099]]



                         Table 3 to Paragraph (g)(5)--Part Replacement Compliance Times
----------------------------------------------------------------------------------------------------------------
                                                                 Previously operated    Flight cycle limit from
               Part                   Table S/N is listed in     in high-thrust model    the effective date of
                                                                        engine                  this AD
----------------------------------------------------------------------------------------------------------------
HPT 1st-stage hub P/N 2A5001......  Table 3 of IAE AG NMSB      Yes..................  1,800 FCs.
                                     V2500-ENG-72-0720.
HPT 1st-stage hub P/N 2A5001......  Table 3 of IAE AG NMSB      No...................  2,800 FCs.
                                     V2500-ENG-72-0720.
HPT 2nd-stage hub P/N 2A4802......  Table 4 of IAE AG NMSB      Yes..................  3,400 FCs.
                                     V2500-ENG-72-0720.
HPT 2nd-stage hub P/N 2A4802......  Table 4 of IAE AG NMSB      No...................  3,800 FCs.
                                     V2500-ENG-72-0720.
----------------------------------------------------------------------------------------------------------------

(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: [email protected].

(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: [email protected]; 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 [email protected].

    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


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