AD 2026-10-15

31880 Federal Register / Vol. 91, No. 103 / Friday, May 29, 2026 / Rules and Regulations Approval (DOA). If approved by the DOA, the approval must include the DOA- authorized signature.’’ (2) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2025–0071. (i) No Reporting Requirement Although the material referenced in EASA AD 2025–0071 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) 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 the Operational Safety Branch, send it to the attention of the person identified in paragraph (k) 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 DOA. If approved by the DOA, the approval must include the DOA- authorized signature. (3) Required for Compliance (RC): Except as required by paragraphs (i) and (j)(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. (k) Additional Information For more information about this AD, contact Nicholas Benson, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206–231–3647; email: nicholas.h.benson@faa.gov. (l) 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 2025–0071, dated March 31, 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 May 11, 2026. Lona C. Saccomando, Acting Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2026–10802 Filed 5–28–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2025–2544; Project Identifier MCAI–2025–00531–T; Amendment 39–23355; AD 2026–10–15] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318–111, –112, and –122 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –216, –232, –233, –251N, –252N, –253N, –271N, –272N, and –273N airplanes; and Model A321–211, –212, –213, –231, –232, –251N, –252N, –253N, –271N, –272N, –251NX, –252NX, –253NX, –271NX, and –272NX airplanes. This AD was prompted by the detection of a deviation from the manufacturing process during a review of the cold working process in the assembly line. This AD requires repetitive special detailed inspections (SDIs) and rototest or high frequency eddy current (HFEC) and rototest inspections of the affected fasteners and fastener holes, and applicable on- condition actions. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective July 6, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 6, 2026. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2025–2544; 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 European Union Aviation Safety Agency (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. • 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–2025–2544. FOR FURTHER INFORMATION CONTACT : Dan Rodina, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206–231–3225; email: Dan.Rodina@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 Airbus SAS Model A318–111, –112, and –122 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –215, –216, –232, –233, –251N, –252N, –253N, –271N, –272N, and –273N airplanes; and Model A321–211, –212, –213, –231, –232, –251N, –252N, –253N, –271N, –272N, –251NX, –252NX, –253NX, –271NX, and –272NX airplanes. The NPRM was published in the Federal Register on September 15, 2025 (90 FR 44350). The NPRM was prompted by AD 2025–0078, dated April 9, 2025 (EASA AD 2025–0078) (also referred to as the MCAI), issued by EASA, which is the Technical Agent for the Member States of the European VerDate Sep<11>2014 16:25 May 28, 2026 Jkt 268001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\29MYR1.SGM 29MYR1 khammond on DSK9W7S144PROD with RULES

31881 Federal Register / Vol. 91, No. 103 / Friday, May 29, 2026 / Rules and Regulations Union. The MCAI states that a deviation from the manufacturing process was detected during a review of the cold working process in the assembly line, which could adversely affect the fatigue life of the affected areas (forward pressure bulkhead connection to frame (FR) 35 for Airbus A319 and A320 airplanes and FR35.8 for Airbus A321 airplanes, between stringer (STR) 28 and STR 31, both left-hand (LH) and right- hand (RH) sides; and fuselage skin at FR35 for Airbus A318, A319 and A320 airplanes and FR35.8 for Airbus A321 airplanes, at STR30, both LH and RH sides). This condition, if not detected and corrected, could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the airplane. In the NPRM, the FAA proposed to require repetitive SDIs around the fastener holes at FR35, STR 28 to STR 31 to check if the fasteners and fastener holes are in nominal design condition, repetitive rototest or HFEC and rototest inspections around the fasteners and fastener holes for cracks, and applicable corrective actions, as specified in EASA AD 2025–0078. 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–2025–2544. Discussion of Final Airworthiness Directive Comments The FAA received comments from three commenters, including American Airlines (American), the Citizens Rulemaking Alliance, and JetBlue. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Correct a Typographical Error American requested that the FAA correct a typographical error in Airbus Service Bulletin A320–53–1520, dated November 18, 2024. American noted the instructions in that material, for Option 2, Configuration 002, specify to remove 12 fasteners whereas only 9 fasteners are shown in the corresponding figure. American stated Airbus confirmed via Repair and Design Approval Form (RDAF) 81664262/004/2025#A that only 9 fasteners are to be removed. The FAA agrees and has added a new exception to paragraph (h)(4) of this AD, accordingly. Request To Revise Fastener Removal Procedure JetBlue requested that the FAA allow removal of the fasteners and inspection of all affected fasteners holes at the same time with any applicable repair to follow, instead of removal of one fastener at a time followed by inspection and repair of one fastener hole at a time, as specified in paragraph C(4)(b) of Airbus Service Bulletin A320–53–1519, dated November 18, 2024, and Airbus Service Bulletin A320–53–1520 dated November 18, 2024. JetBlue stated that Airbus confirmed via Tech Request 8159376 that 100% of the fasteners can be removed from the affected holes prior to performing non-destructive tests and corrective actions, if needed. JetBlue also stated this approach is intended to prevent work stoppages and improve efficiency during the inspection process. The FAA agrees and has added a new exception to paragraph (h)(5) of this AD, accordingly. Request To Justify Forgoing Notice and Comment or Issue an NPRM The Citizens Rulemaking Alliance requested that the FAA either provide its justification for finding good cause to bypass notice and comment procedures, or convert this action to an NPRM to extend the comment period and delay compliance enforcement. The commenter also requested that the FAA add to the AD docket the chronology of the underlying events and the quantitative risk assessment that justifies use of the good cause exemption. The FAA notes the comment was submitted in response to an NPRM for which the FAA provided a 45-day comment period. This final rule is effective 35 days after its publication in the Federal Register . Therefore, no change to this AD is necessary. Request To Make Incorporation by Reference (IBR) Materials Reasonably Available The Citizens Rulemaking Alliance requested that the FAA make IBR material available and free to the public during the comment period. The commenter asserted that this AD incorporates by reference manufacturer service information. The FAA notes that this AD incorporates by reference EASA AD 2025–0078, not the manufacturer service information referenced in that EASA AD. The FAA posted EASA AD 2025–0078 to the AD docket when the NPRM was published in the Federal Register . The material referenced in EASA AD 2025–0078 may only be posted before the final rule’s publication if it is already publicly available or if there is written consent from the owner of that material. Additionally, the FAA provided notice in the NPRM that the material referenced in EASA AD 2025– 0078 will be available in the AD docket after this AD is published. Therefore, the FAA did not change this AD as a result of this comment. Request To Comply With the Paperwork Reduction Act (PRA) The Citizens Rulemaking Alliance requested that the FAA revise the AD to comply with the PRA if reporting is required or remove any reporting provisions until PRA requirements are satisfied. If reporting is not required, the commenter requested the FAA clarify that in the AD. The FAA notes paragraph (i) of this AD specifies that reporting is not required. If an AD were to require reporting, the preamble of the AD would include a paragraph titled ‘‘Paperwork Reduction Act’’ that would provide the applicable OMB control number, required PRA statements, and the estimated time to collect the required information (burden). Any costs associated with the reporting requirement would be included in the Costs of Compliance section in the preamble of the AD. Therefore, the FAA did not change this AD as a result of this comment. Request To Consider Impact on Small Entities The Citizens Rulemaking Alliance requested that the FAA either provide the factual basis for its Regulatory Flexibility Act (RFA) certification that the AD will not have a significant economic impact on a substantial number of small entities, including the number of small entities operating affected airplanes, or prepare an initial regulatory flexibility analysis that identifies alternatives to minimize impact if the cost analysis shows the impact on small entities is not de minimis. The FAA provides the following clarification. The RFA of 1980 (5 U.S.C. 601–612), as amended by the Small Business Regulatory Enforcement Fairness Act of 1996 (Pub. L. 104–121) and the Small Business Jobs Act of 2010 (Pub. L. 111–240), requires Federal agencies to consider the effects of the regulatory action on small business and other small entities and to minimize any significant economic impact. The term ‘‘small entities’’ comprises small businesses and not-for-profit organizations that are independently owned and operated and are not dominant in their fields, and governmental jurisdictions with populations of less than 50,000. This AD will affect 23 domestic entities, of which 8 are small entities. VerDate Sep<11>2014 16:25 May 28, 2026 Jkt 268001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\29MYR1.SGM 29MYR1 khammond on DSK9W7S144PROD with RULES

31882 Federal Register / Vol. 91, No. 103 / Friday, May 29, 2026 / Rules and Regulations The table below displays the industries of the small entities, their average annual revenue, and the AD’s estimated cost burden relative to average annual revenue. N UMBER OF S MALL E NTITIES A FFECTED BY I NDUSTRY AND C OST SIGNIFICANCE 1 NAICS code Description Affected small entities Average annual revenue Number of aircraft Cost per AD/annual revenue (%) 336412 ............. Aircraft Engine and Engine Parts Manufacturing .......................... 1 $5,200,000 5 0.52 336413 ............. Other Aircraft Part and Auxiliary Equipment Manufacturing ......... 1 3,960,000 1 0.14 336413 ............. Other Aircraft Part and Auxiliary Equipment Manufacturing ......... 1 215,930 1 2.48 336413 ............. Other Aircraft Part and Auxiliary Equipment Manufacturing ......... 1 520,000 1 1.03 481211 ............. Nonscheduled Chartered Passenger Air Transportation .............. 1 246,350,000 22 0.05 532411 ............. Commercial Air, Rail, and Water Transportation Equipment Rental and Leasing. 1 1,020,000 1 0.53 532411 ............. Commercial Air, Rail, and Water Transportation Equipment Rental and Leasing. 1 1,070,000 2 1.00 532411 ............. Commercial Air, Rail, and Water Transportation Equipment Rental and Leasing. 1 218,330 2 4.91 1 Source: SBA (2023). NAICS (North American Industrial Classification System). Dun & Bradstreet. D&B Hoovers. Retrieved April 12, 2024. https://app.hoovers.dnb.com/. While the FAA has determined that this AD affects a substantial number of small entities, the compliance cost of the AD relative to small entities’ annual revenue is minimal. The estimated cost per affected airplane is $5,355 (63 work- hours × $85 per work-hour). Based on the number of airplanes per small entity, the total cost burden is less than 3 percent of average annual revenue for all but one small entity. Therefore, as provided in section 605(b), the FAA certifies this AD will not result in a significant economic impact on a substantial number of small entities. The FAA did not change this AD as a result of this comment. Request To Provide Additional Cost Information The Citizens Rulemaking Alliance requested that the FAA add to the AD docket the cost per small entity, including downtime and recordkeeping. The FAA recognizes that, in doing the actions required by an AD, operators might incur indirect costs (such as loss of revenue due to airplane downtime, recordkeeping to document AD compliance, etc.) in addition to the direct costs. The cost analysis in an AD typically describes only the direct costs of the specific actions required by an AD, which does not include indirect costs, since the FAA lacks data on those costs and they may vary significantly among operators. However, the FAA considered the impact that this AD will have on affected operators and determined this AD will not trigger any downtime costs because the requirements of this AD can be performed during regularly scheduled maintenance. In the Costs of Compliance section of the proposed AD, the FAA disclosed the estimated cost per airplane on the U.S. registry. Since the FAA has assessed and disclosed the total known costs of the AD requirements in the Costs of Compliance section of the proposed AD, and the commenter did not provide additional cost data for the FAA to consider in its cost analysis, it is not necessary to provide additional information in the AD docket. The FAA did not change this AD as a result of this comment. 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, 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. Material Incorporated by Reference Under 1 CFR Part 51 EASA AD 2025–0078 specifies procedures for repetitive SDIs around the fastener holes at FR35, STR 28 to STR 31 to check if the fasteners and fastener holes are in nominal design condition, repetitive rototest or HFEC and rototest inspections around the fasteners and fastener holes for cracks, and applicable corrective actions. Corrective actions include repair. 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. Costs of Compliance The FAA estimates that this AD affects 1,474 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: E STIMATED C OSTS FOR R EQUIRED A CTIONS Labor cost Parts cost Cost per product Cost on U.S. operators Up to 63 work-hours × $85 per hour = $5,355 ........................ $0 Up to $5,355 ........................... Up to $7,893,270. 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31883 Federal Register / Vol. 91, No. 103 / Friday, May 29, 2026 / Rules and Regulations The FAA has received no definitive data on which to base the cost estimates for the on-condition repairs specified in this AD. 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 ■ 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: 2026–10–15 Airbus SAS: Amendment 39– 23355; Docket No. FAA–2025–2544; Project Identifier MCAI–2025–00531–T. (a) Effective Date This airworthiness directive (AD) is effective July 6, 2026. (b) Affected ADs None. (c) Applicability This AD applies to Airbus SAS airplanes specified in paragraphs (c)(1) through (4), certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2025–0078, dated April 9, 2025 (EASA AD 2025–0078). (1) Model A318–111, –112, and –122 airplanes. (2) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Model A320–211, –212, –214, –216, –232, –233, –251N, –252N, –253N, –271N, –272N, and –273N airplanes. (4) Model A321–211, –212, –213, –231, –232, –251N, 252N, –253N, –271N, –272N, –251NX, –252NX, –253NX, –271NX, and –272NX airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by the detection of a deviation from the manufacturing process during a review of the cold working process in the assembly line. The FAA is issuing this AD to address reduced fatigue life of the affected areas of the forward pressure bulkhead connection to, and fuselage skin at, certain frames. The unsafe condition, if not addressed, could result in reduced structural integrity 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, EASA AD 2025–0078. (h) Exceptions to EASA AD 2025–0078 (1) Where EASA AD 2025–0078 refers to its effective date, this AD requires using the effective date of this AD. (2) Where paragraphs (2) and (3) of EASA AD 2025–0078 specify ‘‘discrepancy’’, this AD requires replacing that text with ‘‘fastener or fastener hole that is not in a nominal design condition’’. (3) Where paragraph (6) of EASA AD 2025– 0078 specifies ‘‘If, during inspection as required by paragraph (3), (4) or (5) of this AD, any crack is found, as defined in the SB, before next flight, contact Airbus for approved repair instructions and, within the compliance time specified therein, accomplish those instructions accordingly.’’, this AD requires replacing that text with ‘‘If, during any inspection required by paragraph (3), (4), or (5) of this AD, any cracking is found, the cracking must be repaired before further flight 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.’’ (4) Where Airbus Service Bulletin A320– 53–1520 referenced in EASA AD 2025–0078 to remove ‘‘12 FASTENERS’’, this AD requires replacing that text with ‘‘9 FASTENERS’’. (5) Where Airbus Service Bulletin A320– 53–1519 and Airbus Service Bulletin A320– 53–1520 referenced in EASA AD 2025–0078 contain Notes that specify to ‘‘Remove only one fastener and follow the Service Bulletin process from the inspection to the installation and repeat the same process for other fasteners,’’ and Cautions that specify ‘‘Only one fastener to be removed at a time from the affected holes’’ and ‘‘The rototest inspection has to be performed hole by hole with only one fastener removed at a time from the affected holes,’’ this AD allows all fasteners to be removed from the affected fastener holes at the same time prior to performing non-destructive tests and corrective actions. (6) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2025–0078. (i) No Reporting Requirement Although the material referenced EASA AD 2025–0078 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) 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 the Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (k) of this AD and email to: AMOC@faa.gov . 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 DOA. If approved by the DOA, the approval must include the DOA- authorized signature. (3) Required for Compliance (RC): Except as required by paragraphs (h)(4) and (5), (i), and (j)(2) of this AD, if any material contains procedures or tests that are identified as RC, VerDate Sep<11>2014 16:25 May 28, 2026 Jkt 268001 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\29MYR1.SGM 29MYR1 khammond on DSK9W7S144PROD with RULES

31884 Federal Register / Vol. 91, No. 103 / Friday, May 29, 2026 / Rules and Regulations 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. (k) Additional Information For more information about this AD, contact Dan Rodina, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206–231–3225; email: Dan.Rodina@faa.gov. (l) 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 2025–0078, dated April 9, 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 May 13, 2026. Lona C. Saccomando, Acting Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2026–10799 Filed 5–28–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2025–3422; Project Identifier AD–2025–00763–T; Amendment 39–23354; AD 2026–10–14] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747–100, –100B, –100B SUD, –200B, –200C, –200F, –300, –400, –400D, –400F, 747SP, and 747SR series airplanes. This AD was prompted by reports of corrosion damage found on a certain satellite communications (SATCOM) high gain antenna adapter plate. This AD requires repetitive detailed inspections (DETs) of the SATCOM high gain antenna adapter plate for corrosion and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective July 6, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 6, 2026. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2025–3422; 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 Boeing material identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; website myboeingfleet.com. • 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–2025–3422. FOR FURTHER INFORMATION CONTACT : Camille Seay, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 817–222–5149; email: camille.l.seay@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 The Boeing Company Model 747–100, –100B, –100B SUD, –200B, –200C, –200F, –300, –400, –400D, –400F, 747SP, and 747SR series airplanes. The NPRM was published in the Federal Register on September 30, 2025 (90 FR 46771). The NPRM was prompted by reports of corrosion damage found on a certain SATCOM high gain antenna adapter plate. In the NPRM, the FAA proposed to require repetitive DETs of the SATCOM high gain antenna adapter plate for corrosion and applicable on-condition actions. The FAA is issuing this AD to prevent corrosion damage of the SATCOM high gain antenna adapter plates. The unsafe condition, if not addressed, could result in the SATCOM high gain antenna system parts departing and impacting the airplane, which can cause damage that results in loss of continued safe flight and landing. Discussion of Final Airworthiness Directive Comments The FAA received comments from the Air Line Pilots Association, International, (ALPA), Boeing, and a commenter who supported the NPRM without change. The FAA received additional comments from Cathay Pacific Airways Limited (Cathay) and the Citizens Rulemaking Alliance. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Revise the Applicability Cathay requested that the FAA revise the applicability of the proposed AD to exclude airplanes that have been modified in accordance with a certain supplemental type certificate (STC) to remove the Inmarsat Antenna and the related adapter plates (part numbers (P/ Ns) 100–602074–000 and 100–602549– 000). The FAA disagrees. The FAA does not have sufficient information regarding that STC to determine if the modification removes all components associated with the unsafe condition. Operators may request approval of an alternative method of compliance VerDate Sep<11>2014 16:25 May 28, 2026 Jkt 268001 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 E:\FR\FM\29MYR1.SGM 29MYR1 khammond on DSK9W7S144PROD with RULES