AD 2026-21-10

67439 Federal Register / Vol. 91, No. 206 / Tuesday, October 27, 2026 / Rules and Regulations (6) If any affected pitch trim actuator was replaced with a pitch trim actuator that makes the airplane a Group 2 airplane, the actions of this AD still apply at the applicable compliance times. (j) Installation Prohibition for All Airplane Models in Both Group 1 and Group 2 As of the effective date of this AD, do not install a pitch trim actuator unless, upon installation, the procedures in Step 2.C Return to Service of each applicable Service Bulletin referenced in paragraphs (h)(1) or (i)(1) of this AD are followed. (k) No Reporting Requirement Although the applicable Service Bulletins referenced in paragraphs (h)(1) and (i)(1) of this AD specify submission of certain information to the manufacturer, this AD does not include those reporting requirements. (l) Credit for Previous Actions (1) You may take credit for the actions required by paragraphs (h)(1) of this AD if those actions were performed before the effective date of this AD using Ontic Engineering and Manufacturing, Inc. SA227 Service Bulletin 227–27–067R2, dated November 8, 2024; Ontic Engineering and Manufacturing, Inc. SA226 Service Bulletin 226–27–087R2, dated November 8, 2024; Ontic Engineering and Manufacturing, Inc. SA227 Service Bulletin 227–27–067R1, dated August 16, 2024; or Ontic Engineering and Manufacturing Inc. SA227 Service Bulletin 227–27–067, dated July 29, 2024. (2) You may take credit for the actions required by paragraphs (i)(1) of this AD if those actions were performed before the effective date of this AD using Ontic Engineering and Manufacturing, Inc. SA227 Commuter Category Series Service Bulletin CC7–27–038R2, dated November 8, 2024. (m) Special Flight Permit Special flight permits, as described in 14 CFR 21.197 and 21.199, are not allowed. (n) Alternative Methods of Compliance (AMOCs) The Manager, East Certification 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 East Certification Branch, send it to the attention of the person identified in paragraph (o)(1) 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 local flight standards district office/certificate holding district office. (o) Additional Information (1) For more information about this AD, contact Trevor Carlton, Aviation Safety Engineer, FAA, East Certification Branch, FAA, 1701 Columbia Avenue, College Park, GA 30337; phone: (404) 474–5597; email: ECB-COS@faa.gov. (2) Material identified in this AD that is not incorporated by reference is available at the address specified in paragraph (p)(3) of this AD. (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) 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) Ontic Engineering and Manufacturing, Inc. SA227 Commuter Category Series, Service Bulletin CC7–27–038R3, dated January 27, 2026. (ii) Ontic Engineering and Manufacturing, Inc. SA227 Service Bulletin 227–27–067R3, dated March 2, 2026. (iii) Ontic Engineering and Manufacturing, Inc. SA226 Service Bulletin 226–27–087R3, dated March 2, 2026. (3) For Ontic Engineering and Manufacturing, Inc. material identified in this AD, contact Ontic Engineering and Manufacturing, Inc., 1176 Telecom Drive, Creedmoor, NC 27522; phone: (919) 956– 4300; email: metroliner@ontic.com; website: metromerlin.com . (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 1100 Main, Kansas City, MO 64105. 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 October 23, 2026. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026–21902 Filed 10–26–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–11815; Project Identifier MCAI–2026–00154–R; Amendment 39–23499; AD 2026–21–10] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule; request for comments. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model SA 365 N helicopters. This AD was prompted by reports of tightening torque loss on the input flange nut due to circular wear on the faces of the flange, the slip ring, and the input flange. This condition, if not addressed, could lead to degradation or jamming of the input roller bearings and loss of yaw control of the helicopter. This AD requires repetitive functional inspections (checks) and, depending on the results of the inspections, corrective actions. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective November 12, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 12, 2026. The FAA must receive comments on this AD by December 11, 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–2026–11815; 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 street address for Docket Operations is listed above. 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; 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. • 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–2026–11815. VerDate Sep<11>2014 15:58 Oct 26, 2026 Jkt 271001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\27OCR1.SGM 27OCR1 lotter on DSK8BHNXB4PROD with RULES1

67440 Federal Register / Vol. 91, No. 206 / Tuesday, October 27, 2026 / Rules and Regulations FOR FURTHER INFORMATION CONTACT : Anthony Kenward, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (817) 222–5257; email: anthony.b.kenward@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 ADDRESSES . Include ‘‘Docket No. FAA–2026–11815; Project Identifier MCAI–2026–00154–R’’ 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 Anthony Kenward, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2026–0029, dated February 12, 2026 (EASA AD 2026–0029) (also referred to as the MCAI), to correct an unsafe condition on all Airbus Helicopters Model SA 365 N helicopters. The MCAI states that occurrences were reported of a tightening torque loss on the input flange nut, due to circular wear on the faces of the flange, the slip ring, and the input flange. This condition, if not addressed, could lead to degradation or jamming of the input roller bearings and loss of yaw control of the helicopter. 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–2026–11815. Material Incorporated by Reference Under 1 CFR Part 51 The FAA reviewed EASA AD 2026– 0029, which specifies procedures for repetitive functional checks (inspections) of the tail gear box part number 365A33500000 for non- displacement of the tail gear box (TGB) input flange and, depending on the results of the inspections, corrective actions. These corrective actions include gauging the non-displacement of the input flange with a comparator gauge and contacting Airbus Helicopters for a repair solution before resuming flights if the comparator gauge confirms a value more than or equal to 0.1 millimeters (.0039 inches), as specified in the service material referenced in EASA AD 2026–0029. 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. FAA’s Determination These products have been approved by the civil aviation authority (CAA) 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 is issuing this AD after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design. AD Requirements This AD requires accomplishing the actions specified in EASA AD 2026– 0029, described previously as incorporated by reference, except for any differences identified as exceptions in the regulatory text of this AD. See ‘‘Differences Between this AD and the MCAI’’ for a discussion of the general differences included in this AD. Differences Between This AD and the Referenced Material Where EASA AD 2026–0029 and the material referenced in EASA AD 2026– 0029 specify to contact Airbus Helicopters if the comparator gauge confirms a value more than or equal to 0.03 mm, or after completing an oil sample analysis, this AD requires corrective actions to be done in accordance with a method approved by the Manager, International Validation Branch, FAA; EASA; or Airbus Helicopters Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. Explanation of Required Compliance Information In the FAA’s ongoing efforts to improve the efficiency of the AD process, the FAA developed a process to use some CAA ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. The FAA has been coordinating this process with manufacturers and CAAs. As a result, EASA AD 2026–0029 is incorporated by reference in this AD. This AD requires compliance with EASA AD 2026–0029 in its entirety through that incorporation, except for any differences identified as exceptions in the regulatory text of this AD. Using common terms that are the same as the heading of a particular section in EASA AD 2026–0029 does not mean that operators need comply only with that section. For example, where the AD requirement refers to ‘‘all required actions and compliance times,’’ compliance with this AD requirement is not limited to the section titled ‘‘Required Action(s) and Compliance Time(s)’’ in EASA AD 2026–0029. Material required by EASA AD 2026– 0029 for compliance will be available at regulations.gov under Docket No. FAA– 2026–11815 after this AD is published. 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 VerDate Sep<11>2014 15:58 Oct 26, 2026 Jkt 271001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\27OCR1.SGM 27OCR1 lotter on DSK8BHNXB4PROD with RULES1

67441 Federal Register / Vol. 91, No. 206 / Tuesday, October 27, 2026 / Rules and Regulations make rules effective in less than thirty days, upon a finding of good cause. There are currently no domestic operators of these products. 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 the 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 There are no costs of compliance with this AD because there are no helicopters with this type certificate on the U.S. Registry. 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. 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: 2026–21–10 Airbus Helicopters: Amendment 39–23499; Docket No. FAA–2026–11815; Project Identifier MCAI–2026–00154–R. (a) Effective Date This airworthiness directive (AD) is effective November 12, 2026. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Helicopters SA 365 N helicopters, certified in any category. (d) Subject Joint Aircraft System Component (JASC) Code 6520, Tail rotor gearbox. (e) Unsafe Condition This AD was prompted by reports of tightening torque loss on the input flange nut due to circular wear on the faces of the flange, the slip ring, and the input flange. This condition, if not addressed, could lead to degradation or jamming of the input roller bearings and loss of yaw control of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements 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, European Union Aviation Safety Agency (EASA) AD 2026– 0029, dated February 12, 2026 (EASA AD 2026–0029). (h) Exceptions (1) Where EASA AD 2026–0029 refers to its effective date, this AD requires the effective date of this AD. (2) Where EASA AD 2026–0029 requires compliance in terms of flight hours, this AD requires using hours time-in-service. (3) Where EASA AD 2026–0029 or the material referenced in EASA AD 2026–0029 specifies ‘‘check’’, this AD requires replacing that text with ‘‘inspection’’. (4) Where EASA AD 2026–0029 and the material referenced in EASA AD 2026–0029 specify to contact the manufacturer if the comparator gauge confirms a value more than or equal to 0.03 mm, or after completing an oil sample analysis, this AD requires corrective actions in accordance with a method approved by the Manager, International Validation Branch, FAA; EASA; or Airbus Helicopters Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA- authorized signature. (i) No Reporting Requirement Although the material referenced in EASA AD 2026–0029 specifies to submit certain information to the manufacturer, this AD does not require that action. (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 Anthony Kenward, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (817) 222– 5257; email: anthony.b.kenward@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) 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) EASA AD 2026–0029, dated February 12, 2026. (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. VerDate Sep<11>2014 15:58 Oct 26, 2026 Jkt 271001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\27OCR1.SGM 27OCR1 lotter on DSK8BHNXB4PROD with RULES1

67442 Federal Register / Vol. 91, No. 206 / Tuesday, October 27, 2026 / Rules and Regulations (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 October 19, 2026. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026–21854 Filed 10–26–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2025–0003; Project Identifier AD–2024–00110–T; Amendment 39–23501; AD 2026–21–12] 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 certain The Boeing Company Model 757–200 and –300 series airplanes. This AD was prompted by a report that some passenger service unit (PSU)-mounted video monitors became detached from the PSU rails during a hard landing. This AD requires replacing PSU- mounted video monitors that do not have secondary retention lanyards. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective December 1, 2026. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 1, 2026. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2025–0003; 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 the 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–2025–0003. FOR FURTHER INFORMATION CONTACT : Julie Linn, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206–231–3584; email: julie.linn@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 The Boeing Company Model 757–200 and –300 series airplanes. The NPRM was published in the Federal Register on January 17, 2025 (90 FR 5754). The NPRM was prompted by a report that some PSU- mounted video monitors became detached from the PSU rails during a hard landing that did not exceed the emergency load requirements for the PSUs. In the NPRM, the FAA proposed to require replacing PSU-mounted video monitors that do not have secondary retention lanyards. The FAA is issuing this AD to address PSU-mounted video monitors that could become fully detached or be held at an unsafe height, which, if not addressed, could result in injury to passengers and impede passenger and crew egress during emergency evacuation. Discussion of Final Airworthiness Directive Comments The FAA received a comment from one commenter, an individual, who supported the NPRM without change. The FAA received additional comments from four commenters, including Aviation Partners Boeing, Delta Air Lines (Delta), Panasonic Avionics Corporation (Panasonic), and Precision Conversions, LLC (Precision). The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Clarify Method for Determining Applicability Delta requested that the FAA clarify that they can accomplish either a physical inspection for the existence of PSU-mounted video monitors or accomplish a review of Delta’s PSU Layouts (Delta’s PSU drawing configuration) to determine if this AD applies. The FAA agrees to clarify that operators can determine if their airplanes are equipped with PSU- mounted video monitors by performing a physical inspection or a records check, provided the presence of PSU-mounted video monitors can be conclusively determined from that review; either method is acceptable to determine if this AD applies. The FAA did not change this AD in response to this comment. Request To Revise Applicability Precision requested that the FAA revise the applicability of the proposed AD to exclude Boeing Model 757–200 series airplanes that have been converted from passenger to freighter in accordance with a certain supplemental type certificate (STC). Precision STC ST01529SE, which converts Model 757– 200 series airplanes from passenger to freighter airplanes, removes all PSU- mounted video monitors to convert the main deck into a cargo compartment, thus eliminating the unsafe condition referenced in the NPRM. The FAA acknowledges that this AD does not apply to Model 757–200 airplanes converted to freighter in accordance with STC ST01529SE. This AD applies to Model 757–200 and –300 series airplanes equipped with PSU- mounted video monitors. Since Model 757–200 series airplanes converted to freighter in accordance with STC ST01529SE no longer have PSU- mounted video monitors installed, this AD does not apply. The FAA did not change this AD in response to this comment. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that the installation of blended or scimitar blended winglets per STC ST01518SE does not affect compliance with the mandated actions in the proposed rule. The FAA agrees with the commenter that STC ST01518SE does not affect compliance with this AD. Therefore, the installation of STC ST01518SE does not affect the ability to accomplish the actions required by this AD. The FAA did not change this AD in response to this comment. VerDate Sep<11>2014 15:58 Oct 26, 2026 Jkt 271001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\27OCR1.SGM 27OCR1 lotter on DSK8BHNXB4PROD with RULES1