AD 2026-16-05

52221 Federal Register / Vol. 91, No. 155 / Thursday, August 13, 2026 / Rules and Regulations to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (k) 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. (k) Additional Information For more information about this AD, contact Zakaria Abdi, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (316) 946– 4141; email: zakaria.f.abdi@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 the AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2025–0191, dated September 4, 2025. (ii) [Reserved] (3) For EASA material identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: ADs@easa.europa.eu; website: easa.europa.eu. You may find the EASA 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, 10101 Hillwood Parkway, Fort Worth, TX 76177. 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 30, 2026. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026–16506 Filed 8–12–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–4646; Project Identifier MCAI–2025–01763–R; Amendment 39–23435; AD 2026–16–05] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS350B2 helicopters. This AD was prompted by a report of magnetization on the solenoid valves for the three main servo- controls, the regulator block, and the tail servo-control due to a diode not properly installed in the hydraulic circuit. This AD requires performing a cut-off test of the rear rotor actuator valve and, depending on the results of the test, performing corrective actions. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective September 17, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 17, 2026. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2026–4646; 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 Konrad- Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: ADs@easa.europa.eu; website: easa.europa.eu. • You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 10101 Hillwood Parkway, Fort Worth, TX 76177. 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–2026–4646. FOR FURTHER INFORMATION CONTACT : Aryanna Sanchez, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (817) 222–4058; email: aryanna.t.sanchez@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 Helicopters Model AS350B2 helicopters. The NPRM was published in the Federal Register on May 28, 2026 (91 FR 31673). The NPRM was prompted by an MCAI, issued by EASA, which is the Technical Agent for the Member States of the European Union. EASA issued EASA AD 2025–0263, dated November 26, 2025; corrected December 9, 2025 (EASA AD 2025–0263) (also referred to as the MCAI). The MCAI states that during maintenance on a helicopter, magnetization was observed on the solenoid valves for the three main servo- controls, the regulator block, and the tail servo-control. The MCAI also states that after further investigation, it was determined that diode 43D2 was not installed in the hydraulic circuit. In the NPRM, the FAA proposed to require performing a cut-off test of the rear rotor actuator valve and depending on the results of the test, the FAA proposed to require performing corrective actions. 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–2026–4646. Discussion of Final Airworthiness Directive Comments The FAA received no comments on the NPRM or on the determination of the costs. 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 The FAA reviewed EASA AD 2025– 0263, which specifies procedures for performing a cut-off test, and, if any discrepancy (failure of the test) is detected, replacing any affected diodes, or installing any missing diodes. This material is reasonably available because the interested parties have access to it through their normal course of business VerDate Sep<11>2014 15:47 Aug 12, 2026 Jkt 268001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\13AUR1.SGM 13AUR1 khammond on DSK9W7S144PROD with RULE

52222 Federal Register / Vol. 91, No. 155 / Thursday, August 13, 2026 / Rules and Regulations or by the means identified in the ADDRESSES section. Costs of Compliance The FAA estimates that this AD affects 12 helicopters of U.S. registry. 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 Perform cut-off test ......................................... 3 work-hours × $85 per hour = $255 ............. $0 $255 $3,060 The FAA estimates the following costs to do any installations or replacements that would be required based on the results of the test. The agency has no way of determining the number of helicopters that might need these installations or replacements. O N -C ONDITION C OSTS Action Labor cost Parts cost Cost per product Replace diode ............................................................... 1 work-hour × $85 per hour = $85 ............................... $180 $265 Install diode .................................................................. 5 work-hours × $85 per hour = $425 ........................... 1,000 1,425 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: 2026–16–05 Airbus Helicopters: Amendment 39–23435; Docket No. FAA–2026–4646; Project Identifier MCAI–2025–01763–R. (a) Effective Date This airworthiness directive (AD) is effective September 17, 2026. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Helicopters Model AS350B2 helicopters as specified in European Union Aviation Safety Agency AD 2025–0263, dated November 26, 2025; corrected December 9, 2025 (EASA AD 2025– 0263). (d) Subject Joint Aircraft System Component (JASC) Code 2900, Hydraulic power system. (e) Unsafe Condition This AD was prompted by a report of magnetization on the solenoid valves for the three main servo-controls, the regulator block, and the tail servo-control due to a diode not properly installed in the hydraulic circuit. The FAA is issuing this AD to prevent loss of the efficiency of the yaw load compensator and of hydraulic assistance for the three main servo-controls and the tail servo-control. The unsafe condition, if not addressed, could result in reduced control of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2025– 0263. (h) Exceptions to EASA AD 2025–0263 (1) Where EASA AD 2025–0263 refers to its effective date, this AD requires using the effective date of this AD. (2) Where EASA AD 2025–0263 requires compliance in terms of flight hours, this AD requires using hours’ time-in-service. (3) Where the material referenced in EASA AD 2025–0263 specifies ‘‘remove the diode 43D2’’, this AD requires replacing that text with ‘‘remove the diode 43D2 from service’’. (4) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2025–0263. (i) No Reporting Requirement Although the material referenced in EASA AD 2025–0263 specifies to submit certain information to the manufacturer, this AD does not require that action. 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52223 Federal Register / Vol. 91, No. 155 / Thursday, August 13, 2026 / Rules and Regulations (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, International Validation 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 International Validation Branch, send it to the attention of the person identified in paragraph (k) 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. (k) Additional Information For more information about this AD, contact Aryanna Sanchez, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (817) 222– 5110; email: aryanna.t.sanchez@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 the AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2025–0263, dated November 26, 2025; corrected December 9, 2025. (ii) [Reserved] (3) For EASA material identified in this AD, contact EASA Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: ADs@easa.europa.eu; website: easa.europa.eu. (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 10101 Hillwood Parkway, Fort Worth, TX 76177. 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, 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 30, 2026. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026–16507 Filed 8–12–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–0023; Project Identifier AD–2025–00427–T; Amendment 39–23436; AD 2026–16–06] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is superseding Airworthiness Directive (AD) 2018–11– 14, which applied to certain The Boeing Company Model 767–300 and –300F series airplanes with certain winglets installed. AD 2018–11–14 required high frequency eddy current (HFEC) inspections for cracking of the lower outboard wing skin and repair or modification if necessary. AD 2018–11– 14 also required one of three follow-on actions: Repeating the HFEC inspections; modifying certain internal stringers and oversizing and plugging the existing fastener holes of the lower wing; or modifying the external doubler/tripler and doing repetitive post-modification inspections. This AD was prompted by reports of fatigue cracking in the lower outboard wing skin at the inboard fastener of stringer L–9.5, and the lower outboard wing skin of stringer L–6.5, on airplanes with winglets installed per Supplemental Type Certificate (STC) ST01920SE. This AD was also prompted by a determination that, for certain airplanes, the area of the lower wing skin in the vicinity of the critical inboard end fasteners of installed repair doublers must be inspected. This AD continues to require the actions in AD 2018–11–14, adds to the applicability airplanes that have had STC ST01920SE installed and the STC winglets removed, and, for certain airplanes, requires repetitive internal and external HFEC inspections of the lower outboard wing skin common to the external doubler repair at stringer L–9.5 and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective September 17, 2026. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 17, 2026. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of July 10, 2018 (83 FR 25885, June 5, 2018). ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2026–0023; 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 Aviation Partners Boeing material identified in this AD, contact Aviation Partners Boeing, 555 Andover Park West, Suite 200, Tukwila, Washington 98188; telephone 206–830– 7699; email certification@ aviationpartners.com; website aviationpartnersboeing.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–2026–0023. FOR FURTHER INFORMATION CONTACT : Sarah Illg, Aviation Safety Engineer, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone: 206–231– 3517; email: Sarah.A.Illg@faa.gov. SUPPLEMENTARY INFORMATION : Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2018–11–14, Amendment 39–19302 (83 FR 25885, June 5, 2018) (AD 2018–11–14). AD 2018–11–14 applied to certain The Boeing Company Model 767–300 and –300F series airplanes with Aviation Partners Boeing (APB) winglets installed. The NPRM was published in the Federal Register on January 26, 2026 (91 FR 3084). The NPRM was prompted by reports of fatigue cracking in the lower outboard wing skin at the inboard fastener of stringer L–9.5, and the lower outboard wing skin of stringer L–6.5, on airplanes with winglets installed per STC ST01920SE. The NPRM was also prompted by a determination that, for certain airplanes, the area of the lower wing skin in the vicinity of the critical inboard end fasteners of installed repair doublers must be inspected. The FAA is issuing this AD to prevent fatigue cracking in the lower outboard wing skin. The VerDate Sep<11>2014 15:47 Aug 12, 2026 Jkt 268001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\13AUR1.SGM 13AUR1 khammond on DSK9W7S144PROD with RULE