AD 2025-20-10

53210 Federal Register / Vol. 90, No. 225 / Tuesday, November 25, 2025 / Rules and Regulations 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: 2025–20–02 Pilatus Aircraft Ltd.: Amendment 39–23155; Docket No. FAA–2025–0917; Project Identifier MCAI–2024–00740–A. (a) Effective Date This airworthiness directive (AD) is effective December 30, 2025. (b) Affected ADs None. (c) Applicability This AD applies to Pilatus Aircraft Ltd Model PC–24 airplanes, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 3400, Navigation System. (e) Unsafe Condition This AD was prompted by a report of an inaccurate flight director calculation on approach. The FAA is issuing this AD to prevent heading splits that can cause errors in flight director calculations resulting in lateral offsets to the desired approach course. The unsafe condition, if not addressed, could result in an increased pilot workload, resulting in a reduction of the safety margins. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency AD 2024–0240, dated December 10, 2024 (EASA AD 2024–0240). (2) The actions required by paragraph (g)(1) of this AD may be performed by the owner/ operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9(a) and 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. (h) Exceptions to EASA AD 2024–0240 (1) Where EASA AD 2024–0240 refers to its effective date, this AD requires using the effective date of this AD. (2) Where paragraph (1) of EASA AD 2024– 0240 specifies to implement the AFM–TR, this AD requires revising the Abnormal Procedures Section of the existing AFM for your airplane by inserting a copy of the AFM–TR as defined in EASA AD 2024–0240. (3) Where paragraph (1) of EASA AD 2024– 0240 specifies to inform all flight crews and, thereafter, operate the [airplane] accordingly, this AD does not require those actions as those actions are already required by existing FAA regulations (see 14 CFR 91.9, 91.505, and 135.21). (4) This AD does not adopt the Remarks section of EASA AD 2024–0240. (i) 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 International Validation Branch, send it to the attention of the person identified in paragraph (j) 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 responsible Flight Standards Office/ certificate holding district office. (j) Additional Information For more information about this AD, contact Doug Rudolph, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (816) 329– 4059; email: doug.rudolph@faa.gov. (k) 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) AD 2024–0240, dated December 10, 2024. (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 this EASA AD on the EASA website at ad.easa.europa.eu. (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. 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 November 21, 2025. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2025–21090 Filed 11–24–25; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2025–0922; Project Identifier MCAI–2024–00650–R; Amendment 39–23163; AD 2025–20–10] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is superseding Airworthiness Directive (AD) 2021–26– 07, which applies to all Airbus Helicopters Model EC120B helicopters. AD 2021–26–07 requires performing repetitive inspections of the tail rotor (TR) hub body and, depending on the inspection results, replacing certain parts, and accomplishing further inspections. AD 2021–26–07 also requires for certain helicopters removing from service any bolt, washer, and nut installed on the TR hub body at certain life limits and replacing them with airworthy parts and accomplishing further inspections. Additionally, AD 2021–26–07 prohibits the installation of a certain part-numbered TR hub body unless certain requirements are met. Since the FAA issued AD 2021–26–07, it was determined that modifying the link of the TR hub body and splined flange by adding red paint marks is necessary to enable the detection of any loss of tightening torque. This AD retains the same repetitive inspections and corrective actions as AD 2021–26– 07 and requires modification of the link of the TR hub body, which is a terminating action for the repetitive inspections. This AD also requires repetitive inspections of the red paint line added during the modification of the link of the TR hub body for alignment. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective December 30, 2025. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 30, 2025. 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53211 Federal Register / Vol. 90, No. 225 / Tuesday, November 25, 2025 / Rules and Regulations ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2025–0922; 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 Airbus Helicopters material identified in this AD, contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; phone: (972) 641–0000 or: (800) 232–0323; fax: (972) 641–3775; website: airbus.com/en/ products-services/helicopters/hcare- services/airbusworld. • You may view this material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N–321, 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–2025–0922. FOR FURTHER INFORMATION CONTACT : Camille Seay, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 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 to supersede AD 2021–26–07, Amendment 39–21866 (86 FR 72829, December 23, 2021) (AD 2021–26–07), which applied to all Airbus Helicopters Model EC120B helicopters. The NPRM published in the Federal Register on June 25, 2025 (90 FR 26951). The NPRM was prompted by European Union Aviation Safety Agency (EASA) AD 2024–0209, dated October 28, 2024 (EASA AD 2024–0209) (also referred to as the MCAI). EASA, the Technical Agent for the Member States of the European Union, issued EASA AD 2024–0209 to address loss of tightening torque in the interface between the TR hub body and splined flange, which creates the risk of crack initiation from a fretting area located on the TR hub body and splined flange or on the TR hub body and flange bolts. The MCAI states that Airbus Helicopters developed a modification, which consists of adding a line of red paint on each bolt and each nut of the link between the TR hub and the splined flange. The MCAI further states that an Airworthiness Limitations Section task was published for checking alignment of the marks. The FAA is issuing this AD to detect cracking and fretting of the TR hub body, which, if not addressed, could lead to loss of the TR drive, and consequent loss of yaw control of the helicopter. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2025–0922. 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 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 Airbus Helicopters Emergency Alert Service Bulletin 05A020, Revision 3, dated September 19, 2024 (EASB 05A0020 Rev 3), which specifies procedures for repetitive inspections of the TR hub body for cracks and the TR spline flange for cracks and fretting and the appropriate corrective actions to include replacing the hub body and the splined flange. EASB 05A0020 Rev. 3 also excludes helicopters that have complied with Airbus Helicopters Alert Service Bulletin EC120–64–21–0001, Issue 001, dated September 19, 2024 (ASB EC120– 64–21–0001) from its effectivity and limits the effectivity for ‘‘non installed equipment or parts’’. The FAA also reviewed ASB EC120– 64–21–0001, which specifies procedures for inspecting the torque applied on the nut of the link between the TR hub and the splined flange, and depending on the inspection results, applying torque and replacing parts. ASB EC120–64–21– 0001 also specifies procedures for applying a red paint line on the screw, nut, washer, TR hub, and splined flange. 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 EASA AD 2024–0209 allows a non- cumulative tolerance of 100 FH [flight hours] to be applied to the compliance times to allow for synchronization of the required inspections with other maintenance tasks, whereas this AD does not allow a non-cumulative tolerance to be applied to the compliance times. Costs of Compliance The FAA estimates that this AD affects 70 helicopters of U.S. registry. Labor rates are estimated at $85 per hour. Based on these numbers, the FAA estimates the following costs to comply with this AD. Visually inspecting a TR hub body for a crack takes 0.25 work-hour for an estimated cost of $22 per helicopter and $1,540 for the U.S. fleet. Visually inspecting a TR spline flange for corrosion, impacts, fretting, wear, and a crack takes 0.25 work-hour for an estimated cost of $22 per helicopter and $1,540 for the U.S. fleet. Replacing a T/R hub body bolt, washer, and nut takes 0.5 work-hour and parts cost $25 (per hardware set) for an estimated cost of $68 per helicopter. Inspecting torque and adding a red paint line on each bolt and each nut takes 4 work-hours for an estimated cost of $340 per helicopter and $23,800 for the U.S. fleet. If required, replacing a TR hub body takes 2 work-hours, and parts cost $16,485 for an estimated cost of $16,655 per helicopter. If required, replacing a TR spline flange takes 0.5 work-hour, and parts cost $2,950 for an estimated cost of $2,993 per helicopter. 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 VerDate Sep<11>2014 15:58 Nov 24, 2025 Jkt 268001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\25NOR1.SGM 25NOR1 khammond on DSK9W7S144PROD with RULES

53212 Federal Register / Vol. 90, No. 225 / Tuesday, November 25, 2025 / Rules and Regulations 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 The FAA has determined that 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: ■ a. Removing Airworthiness Directive 2021–26–07, Amendment 39–21866 (86 FR 72829, December 23, 2021); and ■ b. Adding the following new airworthiness directive: 2025–20–10 Airbus Helicopters: Amendment 39–23163; Docket No. FAA–2025–0922; Project Identifier MCAI–2024–00650–R. (a) Effective Date This airworthiness directive (AD) is effective December 30, 2025. (b) Affected ADs This AD replaces AD 2021–26–07, Amendment 39–21866 (86 FR 72829, December 23, 2021). (c) Applicability This AD applies to Airbus Helicopters Model EC120B helicopters, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 6422, Tail Rotor System. (e) Unsafe Condition This AD was prompted by analysis of recurrent loss of tightening torque on several attachment bolts on the tail rotor (TR) hub body. The FAA is issuing this AD to detect cracking and fretting of the TR hub body. The unsafe condition, if not addressed, could lead to loss of the TR drive, and consequent loss of yaw control of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Within 15 hours time-in-service (TIS) or 7 days, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 15 hours TIS, using a light source and mirror, visually inspect TR hub body part number (P/N) C642A0100103 for a crack in the entire inspection area depicted in Figure 1 of Airbus Helicopters Emergency Alert Service Bulletin 05A020 Revision 3, dated September 19, 2024. If any crack is found, before further flight, perform the actions in paragraphs (g)(1)(i) and (ii) of this AD. (i) Remove the TR hub body and each bolt, washer, and nut installed on the TR hub body from service and replace with airworthy parts. (ii) Inspect the TR splined flange for corrosion, impacts, fretting, wear, and a crack in the areas identified in Figure 2 to paragraph (g)(1)(ii) of this AD. If the condition of the part (including corrosion, impacts, fretting, wear, or cracks) exceeds the criteria as specified in Figure 1 to paragraph (g)(1)(ii) of this AD, before further flight, remove the splined flange from service and replace with an airworthy part. Note 1 to paragraph (g)(1)(ii): You may refer to ‘‘Detailed Check-Splined Flange,’’ Task 64–21–00, 6–5, Airbus Aircraft Maintenance Manual (AMM), dated October 15, 2020, which pertains to the TR splined flange inspection. Figure 1 to paragraph (g)(1)(ii)—Inspection Criteria for TR Splined Flange VerDate Sep<11>2014 15:58 Nov 24, 2025 Jkt 268001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\25NOR1.SGM 25NOR1 khammond on DSK9W7S144PROD with RULES

53213 Federal Register / Vol. 90, No. 225 / Tuesday, November 25, 2025 / Rules and Regulations Figure 2 to paragraph (g)(1)(ii)—Inpsection Area of Tail Rotor Splined Flange VerDate Sep<11>2014 15:58 Nov 24, 2025 Jkt 268001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 E:\FR\FM\25NOR1.SGM 25NOR1 ER25NO25.300</GPH> khammond on DSK9W7S144PROD with RULES Location as specified in Maximum damage, which causes replacement (El, Figure 2 to paragraph Dia. 2, Dia. 3, and Dia. 4 are shown in Figure 2 to (g)(l )(ii) of this AD paragraph (g)(l)(ii) of this AD) Zone A Scratch depth> 0.2 mm (0.008 in.). Crack. El< 2.75 mm (0.108 in.). Dia. 3 > 6.02 mm (0.2371 in.). Dia. 2 > 33.03 mm (1.3004 in.). ZoneB Touch-up depth> 0.1 mm (0.004 in.). Crack. ZoneC Crack. Scratch depth> 0.2 mm (0.008 in.). Zone D [Dia. 4 = 14 mm Touch-up depth> 0.1 mm (0.004 in.). +/- 0.1 mm (0.548; Crack. 0.555in.)] El< 2.75 mm (0.108 in.).

53214 Federal Register / Vol. 90, No. 225 / Tuesday, November 25, 2025 / Rules and Regulations (2) For helicopters with 9,000 or more total hours TIS or with unknown total hours TIS, within 15 hours TIS or 7 days, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 1,000 hours TIS, remove each bolt washer, and nut installed on the TR hub body from service and replace with airworthy parts and perform the actions in paragraph (g)(1)(ii) of this AD. (3) For helicopters with less than 9,000 total hours TIS, within 1,000 hours TIS or before accumulating 9,000 total hours TIS, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 1,000 hours TIS, remove each bolt, washer, and nut installed on the TR hub body from service and replace with airworthy parts and perform the actions in paragraph (g)(1)(ii) of this AD. (4) Within 24 months after the effective date of this AD, inspect the torque on the nut of the TR hub body in accordance with paragraph 4.1.2 of Airbus Helicopters Alert Service Bulletin ASB EC120–64–21–0001, Issue 001, dated September 19, 2024. (i) If the torque is not within allowable limits, before further flight, remove the nut on the TR hub body from service and replace it with an airworthy nut; and accomplish the actions in paragraph (g)(4)(ii) of this AD. (ii) If the torque is within allowable limits, before further flight, using polyurethane paint, apply a red paint line to the bolt and washer on the TR hub body; and apply a red paint line to the nut and washer on the splined flange. These actions terminate the repetitive inspections and replacements required by paragraphs (g)(1) through (3) of this AD. (5) Within 100 hours TIS or 12 months, whichever occurs first after the action required in paragraph (g)(4)(ii) of this AD, and thereafter at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first, inspect the red paint line for alignment. If the red paint line is misaligned, before further flight, perform the actions as specified in paragraphs (g)(4)(i) of this AD. (h) Parts Installation Limitations As of the effective date of this AD, do not install on any helicopter a TR hub body P/ N C642A0100103 or a splined flange unless VerDate Sep<11>2014 15:58 Nov 24, 2025 Jkt 268001 PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 E:\FR\FM\25NOR1.SGM 25NOR1 ER25NO25.301</GPH> khammond on DSK9W7S144PROD with RULES DZoneA ZoneB -Zonec -ZoneD SECTION A-A Dia. 2

53215 Federal Register / Vol. 90, No. 225 / Tuesday, November 25, 2025 / Rules and Regulations the part is new (zero hours TIS) or has passed the inspection requirements required by paragraph (g)(1) of this AD. (i) Credit for Previous Actions This paragraph provides credit for the initial instance of the actions required by paragraphs (g)(1) through (3) of this AD, if those actions were performed before the effective date of this AD in accordance with Airbus Helicopters Emergency Alert Service Bulletin 05A020 Revision 0, dated October 29, 2019; Revision 1, dated November 8, 2019; or Revision 2, dated February 8, 2021. (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 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 (k)(1) of this AD and email to: AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. The following provisions also apply to this AD. (k) Additional Information (1) For more information about this AD, contact Camille Seay, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (817) 222– 5149; email: camille.l.seay@faa.gov . (2) For Airbus Helicopters material identified in this AD that is not incorporated by reference, can be found at the contact information identified in paragraph (l)(3) of this AD. (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) Airbus Helicopters Emergency Alert Service Bulletin 05A020, Revision 3, dated September 19, 2024. (ii) Airbus Helicopters Alert Service Bulletin EC120–64–21–0001, Issue 001, dated September 19, 2024. (3) For Airbus Helicopters material identified in this AD, contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; phone: (972) 641–0000 or: (800) 232–0323; fax: (972) 641–3775; website: airbus.com/en/products-services/helicopters/ hcare-services/airbusworld. (4) You may view this material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N– 321, 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 November 20, 2025. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2025–20946 Filed 11–24–25; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2025–5025; Project Identifier AD–2025–01595–T; Amendment 39–23197; AD 2025–24–02] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule; request for comments. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737–700, –800, –900, and –900ER series airplanes. This AD was prompted by a report of a runway excursion caused by loss of braking. An inspection found that the right main landing gear (MLG) hydraulic hoses for the brakes were incorrectly installed at the flow limiters, and the left MLG wheel speed transducer wires were also interchanged. This AD requires a general visual inspection (GVI) of the left and right MLG brake hydraulic hoses for any crossed installation, antiskid valve and transducer operational tests, and applicable on- condition actions. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective December 10, 2025. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 10, 2025. The FAA must receive comments on this AD by January 9, 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–2025–5025; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, any comments received, and other information. The street address for Docket Operations is listed above. Material Incorporated by Reference: • For 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–2025–5025. FOR FURTHER INFORMATION CONTACT : Katherine Venegas, Aviation Safety Engineer, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone: 562–627–5353; email: katherine.venegas@faa.gov. SUPPLEMENTARY INFORMATION : Comments Invited The FAA invites you to send any written data, views, or arguments about this final rule. Send your comments using a method listed under the ADDRESSES section. Include Docket No. FAA–2025–5025 and Project Identifier AD–2025–01595–T 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 VerDate Sep<11>2014 15:58 Nov 24, 2025 Jkt 268001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 E:\FR\FM\25NOR1.SGM 25NOR1 khammond on DSK9W7S144PROD with RULES