AD 2026-11-01

33587 Federal Register / Vol. 91, No. 107 / Thursday, June 4, 2026 / Rules and Regulations airplane and could lead to loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Actions for Model DHC–8–100, –200, and –300 Series Airplanes For Model DHC–8–101, –102, –103, and –106 airplanes, Model DHC–8–201 and –202 airplanes, and Model DHC–8–301, –311, and –315 airplanes: Do the actions specified in paragraphs (g)(1) through (4) of this AD. (1) As of 60 days after the effective date of this AD: At the next flight compartment windshield replacement, do a detailed inspection for cracks and corrosion of the barrel nuts at the windshield side posts and, before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of De Havilland Aircraft of Canada Limited Service Bulletin 8–05–11, dated April 29, 2022. Repeat the inspection thereafter at each flight compartment windshield replacement. (2) Within 6 years since entry into service, or within 60 days after the effective date of this AD, whichever occurs later, do detailed inspections for cracks and corrosion of the barrel nuts at the nose landing gear trunnion plate assemblies, nacelle lower longeron attachments, the front, mid and rear spar horizontal stabilizer to vertical stabilizer attachments, the bathtub fittings attachments, the wing rib YW23.858 assemblies, and the wing rib YW42.00 assemblies, and before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of De Havilland Aircraft of Canada Limited Service Bulletin 8–05–11, dated April 29, 2022. Repeat the inspection thereafter at intervals not to exceed 6 years. (3) Within 6 years since entry into service, or within 60 days after the effective date of this AD, whichever occurs later, do a detailed inspection for cracks and corrosion of the barrel nuts, having part number (P/N) DSC228–5, at the control attachment fittings, and before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of De Havilland Aircraft of Canada Limited Service Bulletin 8–27–122, dated July 18, 2019. Repeat the inspection thereafter at intervals not to exceed 6 years. (4) Within 7 years since entry into service, or within 60 days after the effective date of this AD, whichever occurs later, do a detailed inspection for cracks and corrosion of the barrel nuts, having P/N DSC228–4, at the rudder pedal adjustment mechanism, and before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of De Havilland Aircraft of Canada Limited Service Bulletin 8–27–121, dated July 30, 2019. Repeat the inspection thereafter at intervals not to exceed 7 years. (h) Actions for Model DHC–8–400 Series Airplanes For Model DHC–8–400, –401, and –402 airplanes: Do the actions specified in paragraphs (h)(1) through (3) of this AD. (1) As of 60 days after the effective date of this AD: At the next flight compartment windshield replacement, do a detailed inspection for cracks and corrosion of the barrel nuts at the flight compartment windshield side posts, and before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of De Havilland Aircraft of Canada Limited Service Bulletin 84–05–02, dated April 29, 2022. Repeat the inspection thereafter at each flight compartment windshield replacement. (2) Within 6 years since entry into service, or within 60 days after the effective date of this AD, whichever occurs later, do detailed inspections for cracks and corrosion of the barrel nuts at the vertical stabilizer pitch feel trim frame, the front and rear spar wing to fuselage attachment joint struts and fittings, and the bathtub fitting attachments, and before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of De Havilland Aircraft of Canada Limited Service Bulletin 84–05–02, dated April 29, 2022. Repeat the inspections thereafter at intervals not to exceed 6 years. (3) Within 7 years since entry into service, or within 60 days after the effective date of this AD, whichever occurs later, do a detailed inspection for cracks and corrosion of the barrel nuts, having P/N DSC228–4, at the rudder pedal adjustment mechanism, and before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of De Havilland Aircraft of Canada Limited Service Bulletin 84–27–73, dated May 8, 2019. Repeat the inspection thereafter at intervals not to exceed 7 years. (i) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): 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 responsible Flight Standards 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 (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, International Validation Branch, FAA; or Transport Canada; or De Havilland Aircraft of Canada Limited’s Transport Canada Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO- authorized signature. (j) Additional Information For more information about this AD, contact Christopher Spencer, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 516–228– 7300; email: 9-avs-nyaco-cos@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) De Havilland Aircraft of Canada Limited Service Bulletin 8–05–11, dated April 29, 2022. (ii) De Havilland Aircraft of Canada Limited Service Bulletin 8–27–121, dated July 30, 2019. (iii) De Havilland Aircraft of Canada Limited Service Bulletin 8–27–122, dated July 18, 2019. (iv) De Havilland Aircraft of Canada Limited Service Bulletin 84–05–02, dated April 29, 2022. (v) De Havilland Aircraft of Canada Limited Service Bulletin 84–27–73, dated May 8, 2019. (3) For De Havilland Aircraft of Canada Limited material identified in this AD, contact De Havilland Aircraft of Canada Limited, Dash 8 Series Customer Response Centre, 5800 Explorer Drive, Mississauga, Ontario, L4W 5K9, Canada; telephone North America (toll-free): 855–310–1013, Direct: 647–277–5820; email thd@dehavilland.com; website dehavilland.com. (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 26, 2026. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026–11217 Filed 6–3–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–2283; Project Identifier MCAI–2026–00077–R; Amendment 39–23362; AD 2026–11–01] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. VerDate Sep<11>2014 16:32 Jun 03, 2026 Jkt 268001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\04JNR1.SGM 04JNR1 lotter on DSK8BHNXB4PROD with RULES1

33588 Federal Register / Vol. 91, No. 107 / Thursday, June 4, 2026 / Rules and Regulations SUMMARY : The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model H160–B helicopters modified by Supplemental Type Certificate (STC) SR00223IB. This AD was prompted by reports of various deficiencies on the parts installed on the jettisonable window system. This AD requires removing the jettisonable window and, depending on the removal results, replacing the locking fingers; inspecting and installing any missing retaining rings; and inspecting the left- hand (LH) side and right-hand (RH) side emergency handle latch covers (covers) and, depending on the inspection results, replacing the covers or reinstalling airworthy covers. This AD also requires performing repetitive lubrication of the locking fingers installed on the windows jettisonable system and repetitive operational tests of the windows jettisonable system after each lubrication. Additionally, this AD requires modifying the helicopter by replacing each cover and prohibits the installation of certain window aesthetic covers or electrochromic windows unless certain requirements are met. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective July 9, 2026. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 9, 2026. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2026–2283; 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; 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. For Mecaer Aviation Group (MAG) material identified in this AD, contact MAG, Via dell’Artigianato 1, Monteprandone 63076 Ascoli Piceno, Italy; phone: +39 0735–7091; email: caw@mecaer.com; or at mecaer.com . • 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–2026–2283. FOR FURTHER INFORMATION CONTACT : Brenda Buitrago Perez, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (516) 228–7368; email: brenda.l.buitrago.perez@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 all Airbus Helicopters Model H160–B helicopters modified by STC SR00223IB. The NPRM was published in the Federal Register on February 26, 2026 (91 FR 9506). The NPRM was prompted by EASA AD 2025–0269, dated December 1, 2025 (EASA AD 2025–0269) (also referred to as the MCAI), issued by EASA, which is the Technical Agent for the Member States of the European Union. The MCAI states there have been reports of various deficiencies involving parts installed on the jettisonable window system, which include difficulty moving the locking fingers from the locking position that could cause the jettison function to fail; missing retaining rings on the jettison window hinge pins; and intermediate covers found partially detached. In the NPRM, the FAA proposed to require removing the jettisonable window and, depending on the removal results, replacing the locking fingers; inspecting and replacing any missing retaining rings; and inspecting the LH side and RH side covers and, depending on the inspection results, replacing the covers or reinstalling airworthy covers. In the NPRM, the FAA also proposed to require performing repetitive lubrication of the locking fingers installed on the windows jettisonable system and repetitive operational tests of the windows jettisonable system after each lubrication. Additionally, in the NPRM the FAA proposed to require modifying the helicopter by replacing each cover and to prohibit installing certain window aesthetic covers or electrochromic windows unless certain requirements are met. The FAA is issuing this AD to prevent failure of the jettisoning function of the window, which if not addressed, could result in the inability to evacuate helicopter occupants during an emergency situation. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2026–2283. 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 and corrections to the cost calculations, 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– 0269. This material specifies, for helicopters that have aesthetic cover installation part number (P/N) 6A6H5600A002001XYZ and electrochromic window installation P/N 6A6H5600A001001XYZ installed, procedures for removing the jettisonable windows and, if applicable, replacing the locking fingers and inspecting and installing any missing retaining rings. EASA AD 2025–0269 also specifies procedures for inspecting the LH side and RH side covers and, depending on the inspection results, replacing any covers that have discrepancies with certain part-numbered covers. EASA AD 2025–0269 specifies procedures for repetitively lubricating the locking fingers and performing an operational test after each lubrication for helicopters that have aesthetic cover installation P/ N 6A6H5600A002001XYZ and electrochromic window installation P/N 6A6H5600A001001XYZ installed. Additionally, EASA AD 2025–0269 specifies procedures for modifying the helicopter by replacing the LH side and RH side covers and prohibits the installation of certain part-numbered aesthetic covers or certain part- numbered electrochromic windows on VerDate Sep<11>2014 16:32 Jun 03, 2026 Jkt 268001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\04JNR1.SGM 04JNR1 lotter on DSK8BHNXB4PROD with RULES1

33589 Federal Register / Vol. 91, No. 107 / Thursday, June 4, 2026 / Rules and Regulations any helicopter unless certain requirements are met. The FAA also reviewed MAG Mandatory Service Bulletin No. SB– A6H–015, dated November 19, 2025, which specifies procedures for inspection, replacement, and lubrication of the locking fingers; inspection for missing retaining rings and installation instructions for any missing retaining rings; inspection and replacement of certain part-numbered covers; and an operational test for the jettisonable windows system. 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. Differences Between This AD and the MCAI The MCAI applies to Airbus Helicopters Model H160–B helicopters modified with EASA STC 10080809, whereas this AD applies to Airbus Helicopters Model H160–B helicopters modified with FAA STC SR00223IB, dated October 3, 2024. Where the MCAI specifies contacting MAG for corrective instructions, this AD requires using a method approved by the FAA, or EASA, or Airbus Helicopters’ EASA Design Organizational Approval. Costs of Compliance The FAA estimates that this AD affects eight 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 Remove jettisonable window systems (6 per heli- copter). 4 work-hours × $85 per hour = $340 (per window) $0 ......................... $2,040 (6 win- dows). $16,320 Inspect retaining rings .............................................. 1 work-hour × $85 per hour = $85 .......................... $0 ......................... $85 ....................... 680 Inspect LH and RH covers ....................................... 4 work-hours × $85 per hour = $340 ....................... $0 ......................... $680 (2 covers) .... 5,440 Lubricate locking fingers ........................................... 2 work-hours × $85 per hour = $170 ....................... $0 ......................... $170 ..................... 1,360 Perform operational test ........................................... 2 work-hours × $85 per hour = $170 ....................... $0 ......................... $170 ..................... 1,360 Modify LH and RH covers ........................................ 2 work-hours × $85 per hour = $170 ....................... $290 (per cover) ... $920 (2 covers) .... 7,360 E STIMATED C OSTS FOR O N -C ONDITION C OSTS Action Labor cost Parts cost Cost per product Replace locking fingers ................................................ Up to 12 work-hours × $85 per hour = $1,020 ........... $3,520 (per kit) ............... $4,540 (per kit). Install missing retaining rings ....................................... 1 work-hour × $85 per hour = $85 .............................. Up to $50 (per ring) ........ Up to $135 (per ring). The FAA has included all known costs in its cost estimate. According to the manufacturer, however, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators. 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: 2026–11–01 Airbus Helicopters: Amendment 39–23362; Docket No. FAA–2026–2283; Project Identifier MCAI–2026–00077–R. (a) Effective Date This airworthiness directive (AD) is effective July 9, 2026. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Helicopters Model H160–B helicopters, certificated in any category, modified by Supplemental Type Certificate (STC) SR00223IB. (d) Subject Joint Aircraft System Component (JASC) Code 5630, Door windows. (e) Unsafe Condition This AD was prompted by reports of various deficiencies on the parts installed on the jettisonable window system. The FAA is issuing this AD to prevent failure of the jettisoning function of the window. The unsafe condition, if not addressed, could result in the inability to evacuate helicopter occupants during an emergency situation. VerDate Sep<11>2014 16:32 Jun 03, 2026 Jkt 268001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\04JNR1.SGM 04JNR1 lotter on DSK8BHNXB4PROD with RULES1

33590 Federal Register / Vol. 91, No. 107 / Thursday, June 4, 2026 / Rules and Regulations (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, European Union Aviation Safety Agency (EASA) AD 2025– 0269, dated December 1, 2025 (EASA AD 2025–0269). (h) Exceptions to EASA AD 2025–0269 and MAG SB–A6H–015 (1) Where EASA AD 2025–0269 refers to its effective date, this AD requires using the effective date of this AD. (2) Where EASA AD 2025–0269 requires compliance in terms of flight hours, this AD requires using hours time-in-service. (3) Where paragraph (5) of EASA AD 2025– 0269 specifies ‘‘perform one operational test of the window jettisonable systems in accordance with the instructions of Part IV of the MSB’’, this AD requires replacing that text with ‘‘perform one operational test (also referred to as a functional test) of the window jettisonable systems in accordance with the instructions of Part IV of the MSB’’. (4) Where paragraph (6) of EASA AD 2025– 0269 and Mecaer Aviation Group Mandatory Service Bulletin No. SB–A6H–015, dated November 19, 2025 (MAG SB–A6H–015) referenced in EASA AD 2025–0269 specifies ‘‘new’’, this AD requires replacing that text with ‘‘new (zero hours time-in-service)’’. (5) Where paragraph (8) of EASA AD 2025– 0269 specifies contacting MAG [Mecaer Aviation Group] for applicable corrective actions and instructions if a discrepancy is detected during the operational test, and where the material referenced in EASA AD 2025–0269 specifies to contact MAG if a functional test fails, this AD requires, before further flight, performing these actions in accordance with a method approved by the Manager, International Validation Branch, FAA; or EASA; or Airbus Helicopters’ EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (6) Where MAG SB–A6H–015 referenced in EASA AD 2025–0269 specifies ‘‘in case of doubt’’, this AD requires replacing that text with ‘‘inspect for broken locking fingers’’. (7) Where MAG SB–A6H–015 referenced in EASA AD 2025–0269 specifies ‘‘confirm that no visible damage is present’’, this AD requires replacing that text with ‘‘inspect for damage (any crack, deformation, wear, corrosion, looseness, elongation, impact mark, or structural defect)’’. (8) Where MAG SB–A6H–015 referenced in EASA AD 2025–0269 specifies ‘‘scrapped’’, this AD requires replacing that text with ‘‘remove from service’’. (9) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2025–0269. (i) No Reporting Requirement Although the material referenced in EASA AD 2025–0269 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 Brenda Buitrago Perez, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (516) 228–7368; email: brenda.l.buitrago.perez@ 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 2025–0269, dated December 1, 2025. (ii) Mecaer Aviation Group (MAG) Mandatory Service Bulletin No. SB–A6H– 015, dated November 19, 2025. (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. For MAG material identified in this AD, contact MAG, Via dell’Artigianato 1, Monteprandone 63076 Ascoli Piceno, Italy; phone: +39 0735–7091; email: caw@mecaer.com; or at mecaer.com. (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 May 22, 2026. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026–11174 Filed 6–3–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–2297; Project Identifier AD–2025–00184–R; Amendment 39–23366; AD 2026–11–05] RIN 2120–AA64 Airworthiness Directives; Various Helicopters AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for various helicopters. This AD was prompted by a report of a loss of tail rotor authority due to auxiliary system fluid loss caused by a yaw pedal damper housing fatigue fracture and attachment bolt fatigue fracture. This AD requires performing repetitive visual inspections of the auxiliary servo assembly, a fluorescent penetrant inspection (FPI) of the yaw pedal damper housing and, if necessary, corrective actions. This AD also requires determining and recording the remaining life of a certain part and revising the existing rotorcraft flight manual (RFM) to provide the flight crew with procedures to follow under certain conditions. This AD also requires revising the airworthiness limitations section (ALS) of the existing maintenance manual (MM) or instructions for continued airworthiness (ICAs) and the existing approved maintenance or inspection program, as applicable by incorporating a new service life limit for a certain part. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective July 9, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 9, 2026. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2026–2297; 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 Sikorsky Aircraft Corporation material identified in this AD, contact VerDate Sep<11>2014 16:32 Jun 03, 2026 Jkt 268001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\04JNR1.SGM 04JNR1 lotter on DSK8BHNXB4PROD with RULES1