Airworthiness Directives; International Aero Engines AG Turbofan Engines, 7029-7033 [2022-02574]

Download as PDF Federal Register / Vol. 87, No. 26 / Tuesday, February 8, 2022 / Rules and Regulations § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2022–02–07 Airbus Canada Limited Partnership (Type Certificate Previously Held by C Series Aircraft Limited Partnership (CSALP); Bombardier, Inc.): Amendment 39–21904; Docket No. FAA–2021–0444; Project Identifier MCAI–2020–01601–T. (a) Effective Date This airworthiness directive (AD) is effective March 15, 2022. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Canada Limited Partnership (type certificate previously held by C Series Aircraft Limited Partnership (CSALP); Bombardier, Inc.) Model BD–500– 1A10 and BD–500–1A11 airplanes, certificated in any category, as identified in Transport Canada Civil Aviation (TCCA) AD CF–2019–19R1, issued November 1, 2019 (TCCA AD CF–2019–19R1). (d) Subject Air Transport Association (ATA) of America Code 28, Fuel. (e) Reason This AD was prompted by reports of wear damage found between the bonding clamps and the fuel feed tubes inside the left- and right-hand fuel tanks. In one incident, the wear damage resulted in a hole in the main engine fuel feed tube located in the collector tank, and subsequent fuel imbalance during flight. The FAA is issuing this AD to address failure of certain fuel feed tubes, which could lead to a severe fuel imbalance or fuel starvation of one engine, or in the event of the failure of multiple fuel tubes feeding both engines, could result in an in-flight shutdown of both engines. (f) Compliance Comply with this AD within the compliance times specified, unless already done. khammond on DSKJM1Z7X2PROD with RULES (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, TCCA AD CF–2019–19R1. (h) Exceptions to TCCA AD CF–2019–19R1 (1) Where TCCA AD CF–2019–19R1 refers to the effective date of TCCA AD CF–2019– 19 (May 27, 2019), this AD requires using the effective date of this AD. (2) Where TCCA AD CF–2019–19R1 refers to its effective date, this AD requires using the effective date of this AD. (3) Where TCCA AD CF–2019–19R1 refers to hours air time, this AD requires using flight hours. (4) Where TCCA AD CF–2019–19R1 specifies rectifying ‘‘any noted discrepancy,’’ for this AD discrepancies are ‘‘damage, cracks, scores, scratches, nicks, and gouges.’’ VerDate Sep<11>2014 15:33 Feb 07, 2022 Jkt 256001 7029 (i) No Reporting Requirement Although the service information referenced in TCCA AD CF–2019–19R1 specifies to submit certain information to the manufacturer, this AD does not include that requirement. Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fr.inspection@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. (j) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO 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 responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 516– 228–7300; fax: 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, New York ACO Branch, FAA; or TCCA; or Airbus Canada Limited Partnership’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAOauthorized signature. Issued on January 7, 2022. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. (k) Related Information For more information about this AD, contact Joseph Catanzaro, Aviation Safety Engineer, Airframe & Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7366; fax 516–794–5531; email 9-avs-nyaco-cos@faa.gov. (l) 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 this AD specifies otherwise. (i) Transport Canada Civil Aviation (TCCA) AD CF–2019–19R1, issued November 1, 2019. (ii) [Reserved] (3) For TCCA AD CF–2019–19R1, contact TCCA, Transport Canada National Aircraft Certification, 159 Cleopatra Drive, Nepean, Ontario K1A 0N5, Canada; telephone 888– 663–3639; email AD-CN@tc.gc.ca; internet https://tc.canada.ca/en/aviation. (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) You may view this material that is incorporated by reference at the National PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 [FR Doc. 2022–02546 Filed 2–7–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0835; Project Identifier AD–2021–00971–E; Amendment 39–21906; AD 2022–02–09] RIN 2120–AA64 Airworthiness Directives; International Aero Engines AG Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2021–11– 15 for certain International Aero Engines AG (IAE) V2500 model turbofan engines. AD 2021–11–15 required performance of an ultrasonic inspection (USI) of the high-pressure turbine (HPT) 1st-stage disk and HPT 2nd-stage disk and, depending on the results of the inspections, replacement of the HPT 1ststage disk or HPT 2nd-stage disk. Since the FAA issued AD 2021–11–15, the FAA determined the need to clarify the compliance time for inspection of any HPT 1st-stage disk or HPT 2nd-stage disk that is installed on a low-thrust model engine but had been previously operated on a high-thrust model engine. This AD requires performance of a USI of the HPT 1st-stage disk and HPT 2ndstage disk and, depending on the results of the inspections, replacement of the HPT 1st-stage disk or HPT 2nd-stage disk. The FAA is issuing this AD to address the unsafe condition on these products. SUMMARY: This AD is effective March 15, 2022. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 15, 2022. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of July 13, 2021 (86 FR 30380, June 8, 2021). DATES: E:\FR\FM\08FER1.SGM 08FER1 7030 Federal Register / Vol. 87, No. 26 / Tuesday, February 8, 2022 / Rules and Regulations For service information identified in this final rule, contact International Aero Engines AG, 400 Main Street, East Hartford, CT 06118; phone: (800) 565–0140; email: help24@ prattwhitney.com; website: https:// connect.prattwhitney.com. You may view this referenced 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. It is also available at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0835. ADDRESSES: Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0835; 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. FOR FURTHER INFORMATION CONTACT: Alberto Hernandez, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7329; fax: (781) 238– 7199; email: Alberto.J.Hernandez@ faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2021–11–15, Amendment 39–21577 (86 FR 30380, June 8, 2021), (AD 2021–11–15). AD 2021–11–15 applied to all IAE V2522– A5, V2524–A5, V2525–D5, V2527–A5, V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, V2531–E5, and V2533–A5 model turbofan engines with a certain HPT 1st-stage disk or HPT 2nd stage disk installed. The NPRM published in the Federal Register on October 28, 2021 (86 FR 59658). The NPRM was prompted by the FAA determining the need to clarify the compliance time for inspection of any HPT 1st-stage disk or HPT 2nd-stage disk that is installed on a V2500 low-thrust model engine but that had been previously operated on a V2500 high-thrust model engine. The manufacturer categorizes V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, and V2533–A5 model turbofan engines as high-thrust model engines and V2522–A5, V2524–A5, V2525–D5, and V2527–A model turbofan engines as low-thrust model engines. The FAA determined that any HPT 1st-stage disk and HPT 2nd-stage disk that was operated on a high-thrust model engine must follow shortened compliance thresholds. In the NPRM, the FAA proposed to require the performance of a USI of the HPT 1st-stage disk and HPT 2nd-stage disk and, depending on the results of the inspections, replacement of the HPT 1st-stage disk or HPT 2ndstage disk. Discussion of Final Airworthiness Directive Comments The FAA received comments from two commenters. Commenters included Air Line Pilots Association, International and United Airlines Engineering. All commenters supported the NPRM without change. Conclusion The FAA reviewed the relevant data, considered the comments received, and determined that air safety requires adopting the AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. Except for minor editorial changes, this AD is adopted as proposed in the NPRM. Related Service Information Under 1 CFR Part 51 The FAA reviewed IAE NonModification Service Bulletin (NMSB) No. V2500–ENG–72–0713, Revision 1, dated January 26, 2021. This NMSB identifies the affected HPT 1st-stage disks and HPT 2nd-stage disks on IAE V2522–A5, V2524–A5, V2525–D5, V2527–A5, V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, and V2533–A5 model turbofan engines and specifies procedures for a USI of the HPT 1ststage disk and HPT 2nd-stage disk. The Director of the Federal Register approved IAE NMSB V2500–ENG–72– 0713, Revision 1, dated January 26, 2021 for incorporation by reference as of July 13, 2021 (86 FR 30380, June 8, 2021). The FAA also reviewed IAE NMSB No. V2500–E5–72–0015, Revision 1, dated August 10, 2021. This NMSB identifies the affected HPT 1st-stage disks and HPT 2nd-stage disks on IAE V2531–E5 model turbofan engines and specifies procedures for a USI of the HPT 1st-stage disk and HPT 2nd-stage disk. 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 ADDRESSES. Costs of Compliance The FAA estimates that this AD affects 1,100 engines installed on airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost USI the HPT 1st-stage disk and HPT 2ndstage disk. 20 work-hours × $85 per hour = $1,700 ........ khammond on DSKJM1Z7X2PROD with RULES The FAA estimates the following costs to do any necessary replacement Cost per product Parts cost that is required based on the results of the inspection. The agency has no way $0 $1,700 Cost on U.S. operators $1,870,000 of determining the number of aircraft that might need this replacement: ON-CONDITION COSTS Action Labor cost Replace the HPT 1st-stage disk or HPT 2nd-stage disk. 0 work-hours × $85 per hour = $0 ............................... VerDate Sep<11>2014 15:33 Feb 07, 2022 Jkt 256001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\08FER1.SGM Parts cost 08FER1 $300,000 Cost per product $300,000 Federal Register / Vol. 87, No. 26 / Tuesday, February 8, 2022 / Rules and Regulations 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 individuals. (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. Authority for This Rulemaking Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 List of Subjects in 14 CFR Part 39 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: a. Removing Airworthiness Directive 2021–11–15, Amendment 39–21577 (86 FR 30380, June 8, 2021); and ■ b. Adding the following new airworthiness directive: ■ ■ 2022–02–09 International Aero Engines AG: Amendment 39–21906; Docket No. FAA–2021–0835; Project Identifier AD– 2021–00971–E. (a) Effective Date This airworthiness directive (AD) is effective March 15, 2022. (b) Affected ADs This AD replaces AD 2021–11–15, Amendment 39–21577 (86 FR 30380, June 8, 2021) (AD 2021–11–15). (c) Applicability This AD applies to International Aero Engines AG (IAE) V2522–A5, V2524–A5, V2525–D5, V2527–A5, V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, V2531– 7031 E5, and V2533–A5 model turbofan engines with an installed: (1) High-pressure turbine (HPT) 1st-stage disk, part number (P/N) 2A5001, with a serial number (S/N) listed in Appendix A, Table 1, of IAE Non-Modification Service Bulletin (NMSB) No. V2500–ENG–72–0713, Revision 1, dated January 26, 2021 (IAE NMSB V2500– ENG–72–0713, Revision 1) or IAE NMSB No. V2500–E5–72–0015, Revision 1, dated August 10, 2021 (IAE NMSB V2500–E5–72– 0015, Revision 1); or (2) HPT 2nd-stage disk, P/N 2A4802, with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500–ENG–72–0713, Revision 1, or IAE NMSB V2500–E5–72–0015, Revision 1. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by an analysis performed by the manufacturer after an event involving an uncontained failure of a HPT 1st-stage disk that resulted in high-energy debris penetrating the engine cowling. The FAA is issuing this AD to prevent failure of the HPT 1st-stage disk and HPT 2nd-stage disk. The unsafe condition, if not addressed, could result in uncontained HPT disk failure, 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 IAE V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, and V2533–A5 model turbofan engines with an HPT 1st-stage disk, P/N 2A5001, with an S/N listed in Appendix A, Table 1, of IAE NMSB V2500–ENG–72– 0713, Revision 1, within the compliance time specified in Figure 1 to paragraph (g)(1) of this AD, or within 10 flight cycles (FCs) after the effective date of this AD, whichever occurs later, perform an ultrasonic inspection (USI) of the HPT 1st-stage disk using the Accomplishment Instructions, paragraph 6, of IAE NMSB V2500–ENG–72–0713, Revision 1. Figure 1 to Paragraph (g)(l)-Inspection threshold A At the next engine shop visit after July 13, 2021 (the effective date of AD 2021-11-15) B Before the HPT 1st-stage disk or HPT 2nd-stage disk has accumulated 3,200 FCs since July 13, 2021 Note 1 to paragraph (g)(1): The USI required by paragraphs (g)(1) through (6) of this AD requires the HPT 1st-stage disk and HPT 2nd-stage disks to be removed from the engine allowing piece-part opportunity VerDate Sep<11>2014 15:33 Feb 07, 2022 Jkt 256001 inspections. Per the Airworthiness Limitations Section of the manufacturer’s Instructions for Continued Airworthiness, the additional inspections are not required unless the part has more than 100 FCs since PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 the last piece-part opportunity inspection, is damaged, or is the cause for the removal of the engine. Engine removal for the purposes of complying with this AD is not ‘‘cause’’ for E:\FR\FM\08FER1.SGM 08FER1 ER08FE22.048</GPH> khammond on DSKJM1Z7X2PROD with RULES Compliance time: Whichever occurs first, Row A or B 7032 Federal Register / Vol. 87, No. 26 / Tuesday, February 8, 2022 / Rules and Regulations removal as stated in the Airworthiness Limitations Section. (2) For IAE V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, and V2533–A5 model turbofan engines with an HPT 2nd-stage disk, P/N 2A4802, with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500–ENG–72– 0713, Revision 1, within the compliance time specified in Figure 1 to paragraph (g)(1) of this AD, or within 10 FCs after the effective date of this AD, whichever occurs later, perform a USI of the HPT 2nd-stage disk using the Accomplishment Instructions, paragraph 7, of IAE NMSB V2500–ENG–72– 0713, Revision 1. (3) For IAE V2522–A5, V2524–A5, V2525– D5, and V2527–A5 model turbofan engines with an HPT 1st-stage disk, P/N 2A5001, with an S/N listed in Appendix A, Table 1, of IAE NMSB V2500–ENG–72–0713, Revision 1, within the following compliance times, perform a USI of the HPT 1st-stage disk using the Accomplishment Instructions, paragraph 6, of IAE NMSB V2500–ENG–72– 0713, Revision 1: (i) If the affected HPT 1st-stage disk has not operated at any time in an IAE V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, or V2533–A5 model turbofan engine, perform the inspection within the compliance time specified in Figure 2 to paragraph (g)(3)(i) of this AD, or within 10 FCs after the effective date of this AD, whichever occurs later; or Figure 2 to Paragraph (g)(3)(i) - Inspection threshold A At the next HPT rotor and stator assembly (HPT module) removal after July 13, 2021 (the effective date of AD 2021-11-15) B Before the HPT 1st-stage disk or HPT 2nd-stage disk has accumulated 6,700 FCs since July 13, 2021 (ii) If the affected HPT 1st-stage disk has operated at any time in an IAE V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, or V2533–A5 model turbofan engine, perform the inspection within the compliance time specified in Figure 1 to paragraph (g)(1) of this AD, or within 10 FCs after the effective date of this AD, whichever occurs later. (4) For IAE V2522–A5, V2524–A5, V2525– D5, and V2527–A5 model turbofan engines with an HPT 2nd-stage disk, P/N 2A4802, with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500–ENG–72–0713, Revision 1, within the following compliance times, perform a USI of the HPT 2nd-stage disk using the Accomplishment Instructions, paragraph 7, of IAE NMSB V2500–ENG–72– 0713, Revision 1: (i) If the affected HPT 2nd-stage disk has not operated at any time in an IAE V2527E– A5, V2527M–A5, V2528–D5, V2530–A5, or V2533–A5 model turbofan engine, perform the inspection within the compliance time specified in Figure 2 to paragraph (g)(3)(i) of this AD, or within 10 FCs after the effective date of this AD, whichever occurs later; or (ii) If the affected HPT 2nd-stage disk has operated at any time in an IAE V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, or V2533–A5 model turbofan engine, perform the inspection within the compliance time specified in Figure 1 to paragraph (g)(1) of this AD, or within 10 FCs after the effective date of this AD, whichever occurs later. (5) For IAE V2531–E5 model turbofan engines with an HPT 1st-stage disk, P/N 2A5001, with an S/N listed in Appendix A, Table 1, of IAE NMSB V2500–E5–72–0015, Revision 1, within the compliance time specified in Figure 1 to paragraph (g)(1) of this AD, or within 10 FCs after the effective date of this AD, whichever occurs later, perform a USI of the HPT 1st-stage disk using the Accomplishment Instructions, paragraph 6, of IAE NMSB V2500–E5–72–0015, Revision 1. (6) For IAE V2531–E5 model turbofan engines with an HPT 2nd-stage disk, P/N VerDate Sep<11>2014 15:33 Feb 07, 2022 Jkt 256001 2A4802, with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500–E5–72–0015, Revision 1, within the compliance time specified in Figure 1 to paragraph (g)(1) of this AD, or within 10 FCs after the effective date of this AD, whichever occurs later, perform a USI of the HPT 2nd-stage disk using the Accomplishment Instructions, paragraph 7, of IAE NMSB V2500–E5–72– 0015, Revision 1. (7) If, during the USI required by paragraphs (g)(1) through (6) of this AD, an HPT 1st-stage disk or HPT 2nd-stage disk does not pass the inspection as specified in the Accomplishment Instructions, paragraph 8, of IAE NMSB V2500–ENG–72–0713, Revision 1, or IAE NMSB V2500–E5–72– 0015, Revision 1, as applicable, before further flight, remove the HPT 1st-stage disk or HPT 2nd-stage disk, as applicable, from service and replace with a part eligible for installation. (h) Definitions (1) For the purpose 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. (2) For the purpose of this AD, a ‘‘part eligible for installation’’ is: (i) An HPT 1st-stage disk or HPT 2nd-stage disk listed in Appendix A, Tables 1 and 2, of IAE NMSB V2500–ENG–72–0713, Revision 1, or Appendix A, Tables 1 and 2, of IAE NMSB V2500–E5–72–0015, Revision 1, that passed the USI required by paragraphs (g)(1) through (6) of this AD; or (ii) An HPT 1st-stage disk or HPT 2nd-stage disk that is not listed in Appendix A, Tables PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 1 and 2, of IAE NMSB V2500–ENG–72–0713, Revision 1, or Appendix A, Tables 1 and 2, of IAE NMSB V2500–E5–72–0015, Revision 1. (i) Credit for Previous Actions You may take credit for the USI of the HPT 1st-stage disk and HPT 2nd-stage disk required by paragraphs (g)(5) and (6) of this AD and the replacement of the HPT 1st-stage disk and HPT 2nd-stage disk required by paragraph (g)(7) of this AD, if you performed these actions before the effective date of this AD in accordance with IAE NMSB No. V2500–E5–72–0015, original issue, dated December 15, 2020. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO 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 certification office, send it to the attention of the person identified in paragraph (k) of this AD. You may email your request to: ANE-AD-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) Related Information For more information about this AD, contact Alberto Hernandez, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7329; fax: (781) 238–7199; email: Alberto.J.Hernandez@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 E:\FR\FM\08FER1.SGM 08FER1 ER08FE22.049</GPH> khammond on DSKJM1Z7X2PROD with RULES Compliance time: Whichever occurs first, Row A or B Federal Register / Vol. 87, No. 26 / Tuesday, February 8, 2022 / Rules and Regulations 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. (3) The following service information was approved for IBR on March 15, 2022. (i) International Aero Engines AG (IAE) Non-Modification Service Bulletin (NMSB) No. V2500–E5–72–0015, Revision 1, dated August 10, 2021. (ii) [Reserved] (4) The following service information was approved for IBR on July 13, 2021 (86 FR 30380, June 8, 2021). (i) IAE NMSB No. V2500–ENG–72–0713, Revision 1, dated January 26, 2021. (ii) [Reserved] (5) For service information identified in this AD, contact International Aero Engines AG, 400 Main Street, East Hartford, CT 06118; phone: (800) 565–0140; email: help24@prattwhitney.com; website: https:// connect.prattwhitney.com. (6) You may view this referenced 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fr.inspection@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on January 10, 2022. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–02574 Filed 2–7–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0501; Project Identifier MCAI–2021–00168–T; Amendment 39–21908; AD 2022–02–11] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. khammond on DSKJM1Z7X2PROD with RULES AGENCY: The FAA is superseding Airworthiness Directive (AD) 2019–20– 10, which applied to certain Airbus SAS Model A318 series airplanes; Model A319–111, –112,–113, –114, –115, –131, –132, and –133 airplanes; Model A320– 211, –212, –214, –216, –231, –232, and –233 airplanes; and Model A321–111, SUMMARY: VerDate Sep<11>2014 15:33 Feb 07, 2022 Jkt 256001 –112, –131, –211, –212, –213, –231, and –232 airplanes. AD 2019–20–10 required repetitive rototest inspections of the holes at the door stop fittings for any cracking, and corrective actions if necessary. Since the FAA issued AD 2019–20–10, a clarification of a certain compliance time for the rototest inspection was added. This AD clarifies a certain compliance time and continues to require repetitive rototest inspections of the holes at the door stop fittings for any cracking, and repair if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 15, 2022. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 15, 2022. ADDRESSES: For material incorporated by reference (IBR) in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0501. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0501; 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, the mandatory continuing airworthiness information (MCAI), 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. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223; email Sanjay.Ralhan@faa.gov. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 7033 Background EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018– 0289R1, dated February 10, 2021 (EASA AD 2018–0289R1) (also referred to as the MCAI), to correct an unsafe condition for certain Airbus SAS Model A318 series airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –215, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. EASA AD 2018–0289R1 supersedes EASA AD 2018–0289 (which corresponds to FAA AD 2019–20–10, Amendment 39–19763 (84 FR 61526, November 13, 2019) (AD 2019–20–10). Model A320–215 airplanes are not certificated by the FAA and are not included on the U.S. type certificate data sheet; this AD therefore does not include those airplanes in the applicability. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2019–20–10. AD 2019–20–10 applied to certain Airbus SAS Model A318 series airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The NPRM published in the Federal Register on June 16, 2021 (86 FR 31989). The NPRM was prompted by a report that cracks were detected on frame (FR)16 and FR20 web holes and passenger door intercostal fitting holes at the door stop fitting locations, and a determination that a certain compliance time needs to be clarified. The NPRM proposed to clarify a certain compliance time and continue to require repetitive rototest inspections of the holes at the door stop fittings for any cracking, and repair if necessary as specified in EASA AD 2018–0289R1. The FAA is issuing this AD to address cracking of the web holes at the door stop fittings, which could affect the structural integrity of the airplane. See the MCAI for additional background information. Discussion of Final Airworthiness Directive Comments The FAA received comments from two commenters, including Delta Airlines (DAL) and United Airlines (UAL). The following presents the comments received on the NPRM and the FAA’s response to each comment. E:\FR\FM\08FER1.SGM 08FER1

Agencies

[Federal Register Volume 87, Number 26 (Tuesday, February 8, 2022)]
[Rules and Regulations]
[Pages 7029-7033]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-02574]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0835; Project Identifier AD-2021-00971-E; 
Amendment 39-21906; AD 2022-02-09]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines AG Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2021-11-15 
for certain International Aero Engines AG (IAE) V2500 model turbofan 
engines. AD 2021-11-15 required performance of an ultrasonic inspection 
(USI) of the high-pressure turbine (HPT) 1st-stage disk and HPT 2nd-
stage disk and, depending on the results of the inspections, 
replacement of the HPT 1st-stage disk or HPT 2nd-stage disk. Since the 
FAA issued AD 2021-11-15, the FAA determined the need to clarify the 
compliance time for inspection of any HPT 1st-stage disk or HPT 2nd-
stage disk that is installed on a low-thrust model engine but had been 
previously operated on a high-thrust model engine. This AD requires 
performance of a USI of the HPT 1st-stage disk and HPT 2nd-stage disk 
and, depending on the results of the inspections, replacement of the 
HPT 1st-stage disk or HPT 2nd-stage disk. The FAA is issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective March 15, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 15, 
2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of July 
13, 2021 (86 FR 30380, June 8, 2021).

[[Page 7030]]


ADDRESSES: For service information identified in this final rule, 
contact International Aero Engines AG, 400 Main Street, East Hartford, 
CT 06118; phone: (800) 565-0140; email: [email protected]; 
website: https://connect.prattwhitney.com. You may view this referenced 
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. It is also available at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0835.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0835; 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.

FOR FURTHER INFORMATION CONTACT: Alberto Hernandez, Aviation Safety 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
phone: (781) 238-7329; fax: (781) 238-7199; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2021-11-15, Amendment 39-21577 (86 FR 
30380, June 8, 2021), (AD 2021-11-15). AD 2021-11-15 applied to all IAE 
V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, 
V2530-A5, V2531-E5, and V2533-A5 model turbofan engines with a certain 
HPT 1st-stage disk or HPT 2nd stage disk installed. The NPRM published 
in the Federal Register on October 28, 2021 (86 FR 59658). The NPRM was 
prompted by the FAA determining the need to clarify the compliance time 
for inspection of any HPT 1st-stage disk or HPT 2nd-stage disk that is 
installed on a V2500 low-thrust model engine but that had been 
previously operated on a V2500 high-thrust model engine. The 
manufacturer categorizes V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and 
V2533-A5 model turbofan engines as high-thrust model engines and V2522-
A5, V2524-A5, V2525-D5, and V2527-A model turbofan engines as low-
thrust model engines. The FAA determined that any HPT 1st-stage disk 
and HPT 2nd-stage disk that was operated on a high-thrust model engine 
must follow shortened compliance thresholds. In the NPRM, the FAA 
proposed to require the performance of a USI of the HPT 1st-stage disk 
and HPT 2nd-stage disk and, depending on the results of the 
inspections, replacement of the HPT 1st-stage disk or HPT 2nd-stage 
disk.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from two commenters. Commenters included 
Air Line Pilots Association, International and United Airlines 
Engineering. All commenters supported the NPRM without change.

Conclusion

    The FAA reviewed the relevant data, considered the comments 
received, and determined that air safety requires adopting the AD as 
proposed. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these products. Except for minor editorial changes, this 
AD is adopted as proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed IAE Non-Modification Service Bulletin (NMSB) No. 
V2500-ENG-72-0713, Revision 1, dated January 26, 2021. This NMSB 
identifies the affected HPT 1st-stage disks and HPT 2nd-stage disks on 
IAE V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, 
V2528-D5, V2530-A5, and V2533-A5 model turbofan engines and specifies 
procedures for a USI of the HPT 1st-stage disk and HPT 2nd-stage disk. 
The Director of the Federal Register approved IAE NMSB V2500-ENG-72-
0713, Revision 1, dated January 26, 2021 for incorporation by reference 
as of July 13, 2021 (86 FR 30380, June 8, 2021).
    The FAA also reviewed IAE NMSB No. V2500-E5-72-0015, Revision 1, 
dated August 10, 2021. This NMSB identifies the affected HPT 1st-stage 
disks and HPT 2nd-stage disks on IAE V2531-E5 model turbofan engines 
and specifies procedures for a USI of the HPT 1st-stage disk and HPT 
2nd-stage disk.
    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 ADDRESSES.

Costs of Compliance

    The FAA estimates that this AD affects 1,100 engines installed on 
airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
USI the HPT 1st-stage disk and HPT 2nd- 20 work-hours x $85 per               $0          $1,700      $1,870,000
 stage disk.                             hour = $1,700.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
replacement that is required based on the results of the inspection. 
The agency has no way of determining the number of aircraft that might 
need this replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace the HPT 1st-stage disk or HPT 2nd-      0 work-hours x $85 per hour = $0        $300,000        $300,000
 stage disk.
----------------------------------------------------------------------------------------------------------------


[[Page 7031]]

    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 individuals.

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:
0
a. Removing Airworthiness Directive 2021-11-15, Amendment 39-21577 (86 
FR 30380, June 8, 2021); and
0
b. Adding the following new airworthiness directive:

2022-02-09 International Aero Engines AG: Amendment 39-21906; Docket 
No. FAA-2021-0835; Project Identifier AD-2021-00971-E.

(a) Effective Date

    This airworthiness directive (AD) is effective March 15, 2022.

(b) Affected ADs

    This AD replaces AD 2021-11-15, Amendment 39-21577 (86 FR 30380, 
June 8, 2021) (AD 2021-11-15).

(c) Applicability

    This AD applies to International Aero Engines AG (IAE) V2522-A5, 
V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-
A5, V2531-E5, and V2533-A5 model turbofan engines with an installed:
    (1) High-pressure turbine (HPT) 1st-stage disk, part number (P/
N) 2A5001, with a serial number (S/N) listed in Appendix A, Table 1, 
of IAE Non-Modification Service Bulletin (NMSB) No. V2500-ENG-72-
0713, Revision 1, dated January 26, 2021 (IAE NMSB V2500-ENG-72-
0713, Revision 1) or IAE NMSB No. V2500-E5-72-0015, Revision 1, 
dated August 10, 2021 (IAE NMSB V2500-E5-72-0015, Revision 1); or
    (2) HPT 2nd-stage disk, P/N 2A4802, with an S/N listed in 
Appendix A, Table 2, of IAE NMSB V2500-ENG-72-0713, Revision 1, or 
IAE NMSB V2500-E5-72-0015, Revision 1.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Unsafe Condition

    This AD was prompted by an analysis performed by the 
manufacturer after an event involving an uncontained failure of a 
HPT 1st-stage disk that resulted in high-energy debris penetrating 
the engine cowling. The FAA is issuing this AD to prevent failure of 
the HPT 1st-stage disk and HPT 2nd-stage disk. The unsafe condition, 
if not addressed, could result in uncontained HPT disk failure, 
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 IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-
A5 model turbofan engines with an HPT 1st-stage disk, P/N 2A5001, 
with an S/N listed in Appendix A, Table 1, of IAE NMSB V2500-ENG-72-
0713, Revision 1, within the compliance time specified in Figure 1 
to paragraph (g)(1) of this AD, or within 10 flight cycles (FCs) 
after the effective date of this AD, whichever occurs later, perform 
an ultrasonic inspection (USI) of the HPT 1st-stage disk using the 
Accomplishment Instructions, paragraph 6, of IAE NMSB V2500-ENG-72-
0713, Revision 1.
[GRAPHIC] [TIFF OMITTED] TR08FE22.048


    Note 1 to paragraph (g)(1): The USI required by paragraphs 
(g)(1) through (6) of this AD requires the HPT 1st-stage disk and 
HPT 2nd-stage disks to be removed from the engine allowing piece-
part opportunity inspections. Per the Airworthiness Limitations 
Section of the manufacturer's Instructions for Continued 
Airworthiness, the additional inspections are not required unless 
the part has more than 100 FCs since the last piece-part opportunity 
inspection, is damaged, or is the cause for the removal of the 
engine. Engine removal for the purposes of complying with this AD is 
not ``cause'' for

[[Page 7032]]

removal as stated in the Airworthiness Limitations Section.

    (2) For IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-
A5 model turbofan engines with an HPT 2nd-stage disk, P/N 2A4802, 
with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500-ENG-72-
0713, Revision 1, within the compliance time specified in Figure 1 
to paragraph (g)(1) of this AD, or within 10 FCs after the effective 
date of this AD, whichever occurs later, perform a USI of the HPT 
2nd-stage disk using the Accomplishment Instructions, paragraph 7, 
of IAE NMSB V2500-ENG-72-0713, Revision 1.
    (3) For IAE V2522-A5, V2524-A5, V2525-D5, and V2527-A5 model 
turbofan engines with an HPT 1st-stage disk, P/N 2A5001, with an S/N 
listed in Appendix A, Table 1, of IAE NMSB V2500-ENG-72-0713, 
Revision 1, within the following compliance times, perform a USI of 
the HPT 1st-stage disk using the Accomplishment Instructions, 
paragraph 6, of IAE NMSB V2500-ENG-72-0713, Revision 1:
    (i) If the affected HPT 1st-stage disk has not operated at any 
time in an IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, or V2533-A5 
model turbofan engine, perform the inspection within the compliance 
time specified in Figure 2 to paragraph (g)(3)(i) of this AD, or 
within 10 FCs after the effective date of this AD, whichever occurs 
later; or
[GRAPHIC] [TIFF OMITTED] TR08FE22.049

    (ii) If the affected HPT 1st-stage disk has operated at any time 
in an IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, or V2533-A5 
model turbofan engine, perform the inspection within the compliance 
time specified in Figure 1 to paragraph (g)(1) of this AD, or within 
10 FCs after the effective date of this AD, whichever occurs later.
    (4) For IAE V2522-A5, V2524-A5, V2525-D5, and V2527-A5 model 
turbofan engines with an HPT 2nd-stage disk, P/N 2A4802, with an S/N 
listed in Appendix A, Table 2, of IAE NMSB V2500-ENG-72-0713, 
Revision 1, within the following compliance times, perform a USI of 
the HPT 2nd-stage disk using the Accomplishment Instructions, 
paragraph 7, of IAE NMSB V2500-ENG-72-0713, Revision 1:
    (i) If the affected HPT 2nd-stage disk has not operated at any 
time in an IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, or V2533-A5 
model turbofan engine, perform the inspection within the compliance 
time specified in Figure 2 to paragraph (g)(3)(i) of this AD, or 
within 10 FCs after the effective date of this AD, whichever occurs 
later; or
    (ii) If the affected HPT 2nd-stage disk has operated at any time 
in an IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, or V2533-A5 
model turbofan engine, perform the inspection within the compliance 
time specified in Figure 1 to paragraph (g)(1) of this AD, or within 
10 FCs after the effective date of this AD, whichever occurs later.
    (5) For IAE V2531-E5 model turbofan engines with an HPT 1st-
stage disk, P/N 2A5001, with an S/N listed in Appendix A, Table 1, 
of IAE NMSB V2500-E5-72-0015, Revision 1, within the compliance time 
specified in Figure 1 to paragraph (g)(1) of this AD, or within 10 
FCs after the effective date of this AD, whichever occurs later, 
perform a USI of the HPT 1st-stage disk using the Accomplishment 
Instructions, paragraph 6, of IAE NMSB V2500-E5-72-0015, Revision 1.
    (6) For IAE V2531-E5 model turbofan engines with an HPT 2nd-
stage disk, P/N 2A4802, with an S/N listed in Appendix A, Table 2, 
of IAE NMSB V2500-E5-72-0015, Revision 1, within the compliance time 
specified in Figure 1 to paragraph (g)(1) of this AD, or within 10 
FCs after the effective date of this AD, whichever occurs later, 
perform a USI of the HPT 2nd-stage disk using the Accomplishment 
Instructions, paragraph 7, of IAE NMSB V2500-E5-72-0015, Revision 1.
    (7) If, during the USI required by paragraphs (g)(1) through (6) 
of this AD, an HPT 1st-stage disk or HPT 2nd-stage disk does not 
pass the inspection as specified in the Accomplishment Instructions, 
paragraph 8, of IAE NMSB V2500-ENG-72-0713, Revision 1, or IAE NMSB 
V2500-E5-72-0015, Revision 1, as applicable, before further flight, 
remove the HPT 1st-stage disk or HPT 2nd-stage disk, as applicable, 
from service and replace with a part eligible for installation.

(h) Definitions

    (1) For the purpose 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.
    (2) For the purpose of this AD, a ``part eligible for 
installation'' is:
    (i) An HPT 1st-stage disk or HPT 2nd-stage disk listed in 
Appendix A, Tables 1 and 2, of IAE NMSB V2500-ENG-72-0713, Revision 
1, or Appendix A, Tables 1 and 2, of IAE NMSB V2500-E5-72-0015, 
Revision 1, that passed the USI required by paragraphs (g)(1) 
through (6) of this AD; or
    (ii) An HPT 1st-stage disk or HPT 2nd-stage disk that is not 
listed in Appendix A, Tables 1 and 2, of IAE NMSB V2500-ENG-72-0713, 
Revision 1, or Appendix A, Tables 1 and 2, of IAE NMSB V2500-E5-72-
0015, Revision 1.

(i) Credit for Previous Actions

    You may take credit for the USI of the HPT 1st-stage disk and 
HPT 2nd-stage disk required by paragraphs (g)(5) and (6) of this AD 
and the replacement of the HPT 1st-stage disk and HPT 2nd-stage disk 
required by paragraph (g)(7) of this AD, if you performed these 
actions before the effective date of this AD in accordance with IAE 
NMSB No. V2500-E5-72-0015, original issue, dated December 15, 2020.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO 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 
certification office, send it to the attention of the person 
identified in paragraph (k) of this AD. You may email your request 
to: [email protected].
    (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) Related Information

    For more information about this AD, contact Alberto Hernandez, 
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: (781) 238-7329; fax: (781) 238-7199; 
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

[[Page 7033]]

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.
    (3) The following service information was approved for IBR on 
March 15, 2022.
    (i) International Aero Engines AG (IAE) Non-Modification Service 
Bulletin (NMSB) No. V2500-E5-72-0015, Revision 1, dated August 10, 
2021.
    (ii) [Reserved]
    (4) The following service information was approved for IBR on 
July 13, 2021 (86 FR 30380, June 8, 2021).
    (i) IAE NMSB No. V2500-ENG-72-0713, Revision 1, dated January 
26, 2021.
    (ii) [Reserved]
    (5) For service information identified in this AD, contact 
International Aero Engines AG, 400 Main Street, East Hartford, CT 
06118; phone: (800) 565-0140; email: [email protected]; 
website: https://connect.prattwhitney.com.
    (6) You may view this referenced 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on January 10, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2022-02574 Filed 2-7-22; 8:45 am]
BILLING CODE 4910-13-P

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