AD 2026-14-06

42649 Federal Register / Vol. 91, No. 131 / Friday, July 10, 2026 / Rules and Regulations (b) Affected ADs This AD replaces AD 2025–10–12, Amendment 39–23046 (90 FR 22457, May 28, 2025) (AD 2025–10–12). (c) Applicability This AD applies to all Airbus SAS airplanes specified in paragraphs (c)(1) through (6) of this AD, certificated in any category. (1) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (2) Model A320–211, –212, –214, –216, –231, –232, –233, –251N, –252N, –253N, –271N, –272N, and –273N airplanes. (3) Model A321–211, –212, –213, –231, –232, –251N, –251NX, –252N, –252NX, –253N, –253NX, –253NY, –271N, –271NX, –271NY, –272N, and –272NX airplanes. (4) Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, –343, –841, and –941 airplanes. (5) Model A350–941 and –1041 airplanes. (6) Model A380–841, –842, and –861 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a report that found corrosion and cracks on the broadband antenna adapter plate during an inspection. The FAA is issuing this AD to address the corrosion and cracks on the broadband antenna adapter plate and skirt assembly- adapter. The unsafe condition, if not addressed, could lead to in-flight detachment of the radome, antenna, and affected parts, which could impact the tail section of the airplane, possibly resulting in damage and reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (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, European Union Aviation Safety Agency (EASA) AD 2025–0120, dated May 26, 2025 (EASA AD 2025–0120). (h) Exceptions to EASA AD 2025–0120 (1) Where Appendix A in ‘‘the applicable SB’’ identified in EASA AD 2025–0120 specifies a compliance time ‘‘from SB publication date’’ or ‘‘from 14 June 2024 [the effective date of the EASA AD 2024–0106],’’ this AD requires using July 2, 2025 (the effective date of AD 2025–10–12), except for Model A321–271NY airplanes this AD requires using the effective date of this AD. (2) Where EASA AD 2025–0120 specifies ‘‘14 June 2024 [the effective date of EASA AD 2024–0106],’’ this AD requires using July 2, 2025 (the effective date of AD 2025–10–12), except for Model A321–271NY airplanes this AD requires using the effective date of this AD. (3) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2025–0120. (4) Where paragraph (2) of EASA AD 2025– 0120 specifies ‘‘any crack and/or corrosion are detected on an affected part’’, this AD requires replacing that text with ‘‘any crack or corrosion is detected on an affected part’’. (5) Paragraph (4) of EASA AD 2025–0120 specifies to report inspection results to Airbus within a certain compliance time. For this AD, report inspection results at the applicable time specified in paragraph (h)(5)(i) or (ii) of this AD. (i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (ii) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (i) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): 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 responsible Flight Standards Office, as appropriate. If sending information directly to the manager of AIR–520, Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (j) of this AD and email to: AMOC@faa.gov . 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, AIR–520, Continued Operational Safety Branch, FAA; or EASA; or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA- authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (i)(2) of this AD, if any material contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (j) Additional Information For more information about this AD, contact Bill Ashforth, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206–231–3520; email: Bill.Ashforth@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2025–0120, dated May 26, 2025. (ii) [Reserved]. (3) For EASA material identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu. You may find this material on the EASA website at ad.easa.europa.eu. (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 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 July 6, 2026. Brian Knaup, Acting Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2026–13982 Filed 7–9–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–7214; Project Identifier AD–2026–00225–E; Amendment 39–23407; AD 2026–14–06] RIN 2120–AA64 Airworthiness Directives; CFM International, S.A. Engines AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule; request for comments. SUMMARY : The FAA is superseding Airworthiness Directive (AD) 2025–21– 03, which applied to certain CFM International, S.A. (CFM) Model LEAP– 1A23, LEAP–1A24, LEAP–1A24E1, LEAP–1A26, LEAP–1A26CJ, LEAP– 1A26E1, LEAP–1A29, LEAP–1A29CJ, LEAP–1A30, LEAP–1A32, LEAP–1A33, LEAP–1A33B2, and LEAP–1A35A engines. AD 2025–21–03 required initial and repetitive borescope inspections (BSIs) of the high-pressure turbine (HPT) rotor stage 1 blades. Depending on the results of the BSIs, AD 2025–21– 03 required either additional BSIs at VerDate Sep<11>2014 15:47 Jul 09, 2026 Jkt 268001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\10JYR1.SGM 10JYR1 khammond on DSK9W7S144PROD with RULES

42650 Federal Register / Vol. 91, No. 131 / Friday, July 10, 2026 / Rules and Regulations reduced intervals or replacement of the HPT rotor stage 1 blades. Since the FAA issued AD 2025–21–03, the manufacturer published updated service material and determined that engines operating in the South Asia region are susceptible to accelerated HPT rotor stage 1 blade deterioration and airfoil distress. This AD requires initial and repetitive BSIs of the HPT rotor stage 1 blades and, depending on the results of the inspections, additional BSIs at reduced intervals or replacement of the HPT rotor stage 1 blades. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective July 27, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 27, 2026. The FAA must receive comments on this AD by August 24, 2026. ADDRESSES : You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2026–7214; 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 street address for Docket Operations is listed above. Material Incorporated by Reference • For CFM material identified in this AD, contact CFM, GE Aviation Fleet Support, 1 Neumann Way, M/D Room 285, Cincinnati, OH 45215; phone: (877) 432–3272; email: aviation.fleetsupport@ ge.com. • You may view this material 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 regulations.gov under Docket No. FAA– 2026–7214. FOR FURTHER INFORMATION CONTACT : Mehdi Lamnyi, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238–7743; email: mehdi.lamnyi@ faa.gov . SUPPLEMENTARY INFORMATION : Comments Invited The FAA invites you to send any written data, views, or arguments about this final rule. Send your comments using a method listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2026–7214; Project Identifier AD– 2026–00225–E’’ at the beginning of your comments. The most helpful comments reference a specific portion of the final rule, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this final rule because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this final rule. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this AD contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this AD, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this AD. Submissions containing CBI should be sent to Mehdi Lamnyi, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background The FAA issued AD 2025–21–03, Amendment 39–23175 (90 FR 57675, December 12, 2025), (AD 2025–21–03), for certain CFM Model LEAP–1A23, LEAP–1A24, LEAP–1A24E1, LEAP– 1A26, LEAP–1A26CJ, LEAP–1A26E1, LEAP–1A29, LEAP–1A29CJ, LEAP– 1A30, LEAP–1A32, LEAP–1A33, LEAP– 1A33B2, and LEAP–1A35A engines. AD 2025–21–03 required initial and repetitive BSIs of the HPT rotor stage 1 blades and, depending on the results of the inspections, additional BSIs at reduced intervals or replacement of the HPT rotor stage 1 blades. AD 2025–21– 03 also required a BSI of the HPT rotor stage 1 blades installed on the sister engine of the same airplane if certain criteria are met. AD 2025–21–03 was prompted by reports of two in-flight shutdowns and subsequent investigation by the manufacturer that revealed cracks in the HPT rotor stage 1 blades. The FAA issued AD 2025–21– 03 to prevent failure of the HPT rotor stage 1 blades. Actions Since AD 2025–21–03 Was Issued Since the FAA issued AD 2025–21– 03, the manufacturer determined that engines operating in the South Asia region are susceptible to accelerated HPT rotor stage 1 blade deterioration and airfoil distress due to the build-up of dust. As a result, the manufacturer published updated service material expanding the list of regions affected by the unsafe condition. The FAA also received a comment from Airbus India requesting clarification on BSI requirements for the sister engine if a non-affected HPT blade is installed, or if the sister engine has an engine configuration that is below the applicability threshold listed in CFM Service Bulletin (SB) LEAP–1A–72–00– 0485–01A–930A–D, Issue 003–00, dated July 30, 2025. As a result, the FAA has updated the regulatory text of this AD to require certain actions be performed in accordance with CFM SB LEAP–1A– 72–00–0485–01A–930A–D, Issue 004– 00, dated May 19, 2026 (CFM SB LEAP– 1A–72–00–0485–01A–930A–D, Issue 004–00), and to clarify that the conditional inspection of the sister engine is not required if the sister engine has an affected part installed and has already met certain inspection conditions. The FAA is issuing this AD to address the unsafe condition on these products. FAA’s Determination The FAA is issuing this AD because the agency determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. VerDate Sep<11>2014 15:47 Jul 09, 2026 Jkt 268001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\10JYR1.SGM 10JYR1 khammond on DSK9W7S144PROD with RULES

42651 Federal Register / Vol. 91, No. 131 / Friday, July 10, 2026 / Rules and Regulations Material Incorporated by Reference Under 1 CFR Part 51 The FAA reviewed CFM SB LEAP– 1A–72–00–0485–01A–930A–D, Issue 004–00, which specifies procedures for performing repetitive BSIs of the HPT rotor stage 1 blades on LEAP–1A engines operating in the South Asia region, and depending on the inspection results, inspecting the sister engine’s HPT rotor stage 1 blades, or removing unserviceable HPT rotor stage 1 blades from service. This material 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. AD Requirements This AD requires initial and repetitive BSIs of the HPT rotor stage 1 blades and, depending on the results of the inspections, additional BSIs at reduced intervals or replacement of the HPT rotor stage 1 blades. This AD also requires a BSI of the HPT rotor stage 1 blades installed on the sister engine of the same airplane if certain criteria are met. Interim Action The FAA considers this AD to be an interim action. The manufacturer is currently developing a terminating action that will address the unsafe condition identified in this AD. Once this terminating action is developed and available, the FAA might consider further rulemaking. Justification for Immediate Adoption and Determination of the Effective Date Section 553(b) of the Administrative Procedure Act (APA) (5 U.S.C. 551 et seq. ) authorizes agencies to dispense with notice and comment procedures for rules when the agency, for ‘‘good cause,’’ finds that those procedures are ‘‘impracticable, unnecessary, or contrary to the public interest.’’ Under this section, an agency, upon finding good cause, may issue a final rule without providing notice and seeking comment prior to issuance. Further, section 553(d) of the APA authorizes agencies to make rules effective in less than thirty days, upon a finding of good cause. The FAA justifies waiving notice and comment prior to adoption of this rule because no domestic operators use this product. It is unlikely that the FAA will receive any adverse comments or useful information about this AD from any U.S. operator. Accordingly, notice and opportunity for prior public comment are unnecessary, pursuant to 5 U.S.C. 553(b). In addition, for the foregoing reason(s), 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. Regulatory Flexibility Act The requirements of the Regulatory Flexibility Act (RFA) do not apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and comment. Because FAA has determined that it has good cause to adopt this rule without prior notice and comment, RFA analysis is not required. Costs of Compliance The FAA estimates that this AD affects 0 operators of engines installed on airplanes of U.S. registry with the criteria identified in the Applicability section of the AD. The FAA estimates the following costs to comply with this AD: E STIMATED C OSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators BSI of the HPT rotor stage 1 blades ................ 4 work-hours × $85 per hour = $340 ............... $0 $340 $0 The FAA estimates the following costs to do any necessary further corrective actions and replacements that would be required based on the results of the inspection. The agency has no way of determining the number of engines that might need these additional inspections or replacements. O N -C ONDITION C OSTS Action Labor cost Parts cost Cost per product Replacement of the HPT rotor stage 1 blades ................. 150 work-hours × $85 per hour = $12,750 ...................... $988,200 $1,000,950 BSI of the HPT rotor stage 1 blades (on the sister en- gine). 4 work-hours × $85 per hour = $340 ............................... 0 340 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, and (2) Will not affect intrastate aviation in Alaska. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. VerDate Sep<11>2014 15:47 Jul 09, 2026 Jkt 268001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\10JYR1.SGM 10JYR1 khammond on DSK9W7S144PROD with RULES

42652 Federal Register / Vol. 91, No. 131 / Friday, July 10, 2026 / Rules and Regulations 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 2025–21–03, Amendment 39–23175 (90 FR 57675, December 12, 2025); and ■ b. Adding the following new airworthiness directive: 2026–14–06 CFM International, S.A.: Amendment 39–23407; Docket No. FAA–2026–7214; Project Identifier AD– 2026–00225–E. (a) Effective Date This airworthiness directive (AD) is effective July 27, 2026. (b) Affected ADs This AD replaces AD 2025–21–03, Amendment 39–23175 (90 FR 57675, December 12, 2025) (AD 2025–21–03). (c) Applicability This AD applies to CFM International, S.A. Model LEAP–1A23, LEAP–1A24, LEAP– 1A24E1, LEAP–1A26, LEAP–1A26CJ, LEAP– 1A26E1, LEAP–1A29, LEAP–1A29CJ, LEAP– 1A30, LEAP–1A32, LEAP–1A33, LEAP– 1A33B2, and LEAP–1A35A engines with an installed high-pressure turbine (HPT) rotor stage 1 blade, having part number (P/N) 2747M92P01, P/N 2553M91G03, P/N 2553M91G05, P/N 2553M91G06, P/N 2553M91G07, or P/N 2553M91G08 that has accumulated more than 1,100 South Asia takeoffs, and has accumulated 2,500 part cycles since new (PCSN) for Group 1 engines, or 5,100 PCSN for Group 2 engines. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by reports of two in-flight shutdowns due to cracks in the HPT rotor stage 1 blades. The FAA is issuing this AD to prevent failure of the HPT rotor stage 1 blades. The unsafe condition, if not addressed, could result in failure of the engine, in-flight shutdown, loss of thrust control, and consequent loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions For the purpose of this AD, the following definitions apply: (1) Group 1 engines are CFM Model LEAP– 1A29, LEAP–1A29CJ, LEAP–1A30, LEAP– 1A32, LEAP–1A33, LEAP–1A33B2, and LEAP–1A35A engines. (2) Group 2 engines are CFM Model LEAP– 1A23, LEAP–1A24, LEAP–1A24E1, LEAP– 1A26, LEAP–1A26CJ, and LEAP–1A26E1 engines. (3) A ‘‘South Asia takeoff’’ is any takeoff accomplished in the South Asia region, which includes the following countries: Bangladesh, Bhutan, India, Maldives, Nepal, and Sri Lanka. (4) A ‘‘sister engine’’ refers to the other engine installed on the same airplane. (h) Required Actions (1) Group 1 Engines: Borescope Inspection (BSI) of HPT Rotor Stage 1 Blades For Group 1 engines with an affected HPT rotor stage 1 blade installed: (i) Within 100 flight cycles (FCs) after accumulating 1,100 South Asia takeoffs on the HPT rotor stage 1 blade, before the HPT rotor stage 1 blade accumulates 2,500 PCSN or within 100 FCs after the effective date of this AD, whichever occurs later, perform an initial BSI of the HPT rotor stage 1 blades in accordance with the Accomplishment Instructions, paragraph 5.E.(1)(c), of CFM Service Bulletin (SB) LEAP–1A–72–00– 0485–01A–930A–D, Issue 004–00, dated May 19, 2026 (CFM SB LEAP–1A–72–00–0485– 01A–930A–D, Issue 004–00). (ii) Thereafter, at intervals not to exceed 150 FCs since the last BSI, perform a repetitive BSI of the HPT rotor stage 1 blades in accordance with the Accomplishment Instructions, paragraph 5.E.(1)(c), of CFM SB LEAP–1A–72–00–0485–01A–930A–D, Issue 004–00. (2) Group 2 Engines: BSI of HPT Rotor Stage 1 Blades For Group 2 engines with an affected HPT rotor stage 1 blade installed: (i) Within 100 FCs after accumulating 1,100 South Asia takeoffs on the HPT rotor stage 1 blade, before the HPT rotor stage 1 blade accumulates 5,100 PCSN, or within 100 FCs after the effective date of this AD, whichever occurs later, perform an initial BSI of the HPT rotor stage 1 blades in accordance with the Accomplishment Instructions, paragraph 5.E.(1)(c), of CFM SB LEAP–1A– 72–00–0485–01A–930A–D, Issue 004–00. (ii) Thereafter, at intervals not to exceed 300 FCs since the last BSI, perform a repetitive BSI of the HPT rotor stage 1 blades in accordance with the Accomplishment Instructions, paragraph 5.E.(1)(c), of CFM SB LEAP–1A–72–00–0485–01A–930A–D, Issue 004–00. (3) BSI Results Disposition for Group 1 and Group 2 Engines Based on the results of the BSI required by paragraphs (h)(1) or (2) of this AD, as applicable, either re-inspect or replace, as applicable, the HPT rotor stage 1 blades set using the criteria, compliance times, and procedures as described in the Accomplishment Instructions, paragraph 5.E.(1)(e), of CFM SB LEAP–1A–72–00– 0485–01A–930A–D, Issue 004–00. (4) Conditional Inspection of the Sister Engine for Group 1 and Group 2 Engines (i) If the sister engine has accumulated 50 FCs or less since the last BSI of the HPT rotor stage 1 blade for Group 1 engines, or 100 FCs or less since the last BSI of the HPT rotor stage 1 blade for Group 2 engines, no further action is required by paragraph (h)(4) of this AD. (ii) Based on the BSI results disposition required by paragraph (h)(3) of this AD, if re- inspection or replacement of the HPT rotor stage 1 blades is required, within 50 FCs, then within 5 FCs after performing the inspection required by paragraph (h)(1) or (2) of this AD, as applicable, either inspect or replace the affected HPT rotor stage 1 blades on the sister engine using the procedures and compliance times in the Accomplishment Instructions, paragraph 5.E.(1)(f), of CFM SB LEAP–1A–72–00–0485–01A–930A–D, Issue 004–00. Where CFM SB LEAP–1A–72–00– 0485–01A–930A–D, Issue 004–00, specifies to remove the engine, this AD requires replacement of the HPT rotor stage 1 blades. (i) Credit for Previous Actions (1) This paragraph provides credit for the initial BSI required by paragraphs (h)(1)(i) or (2)(i) of this AD if you performed the initial BSI before the effective date of this AD using CFM Service Bulletin LEAP–1A–72–00– 0485–01A–930A–D, Issue 001–00, dated September 27, 2022; or Issue 002–00, dated April 16, 2025; or Issue 003–00, dated July 30, 2025. (2) The inspections and corrective actions as required by paragraphs (h)(1) through (4) of this AD satisfy the requirements of paragraphs (g)(1) through (4) of AD 2022–17– 12, Amendment 39–22150 (87 FR 53651, September 1, 2022) (AD 2022–17–12). (3) The inspections and corrective actions as required by paragraphs (g)(1) through (4) of AD 2022–17–12 satisfy the requirements of paragraphs (h)(1) through (4) of this AD. (j) No Reporting Requirement Where CFM SB LEAP–1A–72–00–0485– 01A–930A–D, Issue 004–00, requires reporting any unserviceable findings, this AD does not require that action. (k) 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 (l)(1) of this AD and email to: AMOC@faa.gov . (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (l) Additional Information (1) For more information about this AD, contact Mehdi Lamnyi, Aviation Safety VerDate Sep<11>2014 15:47 Jul 09, 2026 Jkt 268001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\10JYR1.SGM 10JYR1 khammond on DSK9W7S144PROD with RULES

42653 Federal Register / Vol. 91, No. 131 / Friday, July 10, 2026 / Rules and Regulations Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238–7743; email: mehdi.lamnyi@faa.gov. (2) Material identified in this AD that is not incorporated by reference is available at the address specified in paragraph (m)(3) of this AD. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) CFM Service Bulletin LEAP–1A–72–00– 0485–01A–930A–D, Issue 004–00, dated May 19, 2026 (ii) [Reserved] (3) For CFM material identified in this AD, contact CFM International, S.A., GE Aviation Fleet Support, 1 Neumann Way, M/D Room 285, Cincinnati, OH 45215; phone: (877) 432–3272; email: aviation.fleetsupport@ ge.com. (4) You may view this material 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 July 6, 2026. Brian Knaup, Acting Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2026–13979 Filed 7–9–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–3872; Project Identifier MCAI–2025–01421–T; Amendment 39–23401; AD 2026–14–01] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD–700–2A12 airplanes. This AD was prompted by reports of missing or under torqued fasteners on the slat 2 cove rib 6 brackets. This AD requires a general visual inspection (GVI) of affected fasteners on slat 2 cove rib 6 brackets to determine if all fasteners are installed and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective August 14, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 14, 2026. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2026–3872; 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. Material Incorporated by Reference: • For Transport Canada material identified in this AD, contact Transport Canada, Transport Canada National Aircraft Certification, 159 Cleopatra Drive, Nepean, Ontario K1A 0N5, Canada; telephone 888–663–3639; email TC.AirworthinessDirectives- Consignesdenavigabilite.TC@tc.gc.ca. You may find this material on the Transport Canada website at tc.canada.ca/en/aviation. • 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 at regulations.gov under Docket No. FAA–2026–3872. FOR FURTHER INFORMATION CONTACT : Brenda Buitrago Perez, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 516–228–7300; email: 9-avs-nyaco-cos@ 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 Bombardier, Inc., Model BD–700–2A12 airplanes. The NPRM was published in the Federal Register on April 29, 2026 (91 FR 23028). The NPRM was prompted by Transport Canada AD CF–2025–46, dated September 2, 2025 (Transport Canada AD CF–2025–46) (also referred to as the MCAI), issued by Transport Canada, which is the aviation authority for Canada. The MCAI states that there have been reports of missing or under torqued fasteners on the slat 2 cove rib 6 bracket, which are common to both the left-hand side (LHS) and right-hand side (RHS). The MCAI also states that if fasteners are missing or under torqued, the bracket may lose some load carrying capabilities. Stress analysis has determined that missing cove rib 6 load path may lead to reduced safety margins and subsequent loss of structural redundancy. In the NPRM, the FAA proposed to require a GVI of affected fasteners on slat 2 cove rib 6 brackets to determine if the fasteners are installed and applicable on-condition actions, as specified in Transport Canada AD CF– 2025–46. The FAA is issuing this AD to address the unsafe condition on these products. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2026–3872. Discussion of Final Airworthiness Directive Comments The FAA received no comments on the NPRM or on the determination of the cost. Conclusion These products have been approved by the civil aviation authority of another country and are approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with this State of Design Authority, that authority has notified the FAA of the unsafe condition described in the MCAI referenced above. 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, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. Material Incorporated by Reference Under 1 CFR Part 51 Transport Canada AD CF–2025–46 specifies procedures for performing a GVI of affected fasteners on slat 2 cove rib 6 brackets to determine if the fasteners are installed and applicable on-condition actions. On-condition actions include making sure that the fasteners are torqued from 20 to 25 lbf in., performing a GVI for signs of damage (damage includes but is not limited to permanent deformation, distortion, cracking, or other visible VerDate Sep<11>2014 15:47 Jul 09, 2026 Jkt 268001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\10JYR1.SGM 10JYR1 khammond on DSK9W7S144PROD with RULES