AD 2025-07-11

22453 Federal Register / Vol. 90, No. 101 / Wednesday, May 28, 2025 / Rules and Regulations Issued on April 3, 2025. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2025–09507 Filed 5–27–25; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–2720; Project Identifier MCAI–2024–00129–T; Amendment 39–23013; AD 2025–07–11] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD–700–1A10 and BD–700–1A11 airplanes. This AD was prompted by reports of engine- driven pump hydraulic pressure hoses for hydraulic systems number 1 and 2 chafing against the pylon in the aft equipment bay. This AD requires an inspection of the engine-driven pump pressure hoses for any damage and minimum clearance between the engine- driven pump hydraulic pressure hose and case drain, suction pressure hose, and surrounding pylon structure; and corrective actions if necessary. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective July 2, 2025. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 2, 2025. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2024–2720; 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 Bombardier material identified in this AD, contact Bombardier Business Aircraft Customer Response Center, 400 Co ˆ te-Vertu Road West, Dorval, Que ´bec H4S 1Y9, Canada; telephone 514–855– 2999; email ac.yul@ aero.bombardier.com; website bombardier.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–2024–2720. FOR FURTHER INFORMATION CONTACT : Joseph Catanzaro, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 516–228–7300; email: 9-avs-nyaco-cos@ 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 Bombardier, Inc., Model BD–700–1A10 and BD–700–1A11 airplanes. The NPRM published in the Federal Register on January 6, 2025 (90 FR 578). The NPRM was prompted by AD CF–2024–07, dated February 21, 2024 (referred to after this as ‘‘the MCAI’’), issued by Transport Canada, which is the aviation authority for Canada. The MCAI states that there have been reports of engine-driven pump hydraulic pressure hoses for hydraulic systems number 1, left-hand side (LHS), and number 2, right-hand side (RHS), chafing against the pylon in the aft equipment bay. In the NPRM, the FAA proposed to require an inspection of the engine- driven pump pressure hoses for any damage and minimum clearance between the engine-driven pump hydraulic pressure hose and case drain, suction pressure hose, and surrounding pylon structure; and corrective actions if necessary. The FAA is issuing this AD to address the chafing of the hydraulic systems engine-driven pump hoses against the pylon, which may lead to hydraulic system leaks and failures and result in the loss of the affected hydraulic system. Loss of both hydraulic systems number 1 and 2 would substantially reduce the airplane’s functional capabilities. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2024–2720. Discussion of Final Airworthiness Directive Comments The FAA received no comments on the NPRM or on the determination of the cost to the public. Conclusion This product has been approved by the aviation authority of another country and is approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with this State of Design Authority, it 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 this product. 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 the following material issued by Bombardier: • Service Bulletin 700–29–5502, dated November 29, 2023. • Service Bulletin 700–29–6011, dated November 29, 2023. • Service Bulletin 700–29–6502, dated November 29, 2023. This material describes procedures for a borescope inspection of the routing of hydraulic systems number 1, LHS, and number 2, RHS, engine-driven pump pressure hoses for any damage (including fouling or chafing) and for minimum clearance between the engine- driven pump hydraulic pressure hose and case drain, suction pressure hose, and surrounding pylon structure. Corrective actions include replacing and adjusting the pressure hoses. These documents are distinct since they apply to different airplane models. This material is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance The FAA estimates that this AD affects 36 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: VerDate Sep<11>2014 15:49 May 27, 2025 Jkt 265001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\28MYR1.SGM 28MYR1 khammond on DSK9W7S144PROD with RULES

22454 Federal Register / Vol. 90, No. 101 / Wednesday, May 28, 2025 / Rules and Regulations E STIMATED C OSTS FOR R EQUIRED A CTIONS Labor cost Parts cost Cost per product Cost on U.S. operators 2 work-hours × $85 per hour = $170 .............................................................. $0 $170 $6,120 The FAA estimates the following costs to do any necessary on-condition actions that would be required based on the results of any required actions. The FAA has no way of determining the number of aircraft that might need these on-condition actions: E STIMATED C OSTS OF O N -C ONDITION A CTIONS Labor cost Parts cost Cost per product 2 work-hours × $85 per hour = $170 .......................................................................................................... $1,226 $1,396 The FAA has included all known costs in its cost estimate. According to the manufacturer, however, some or all 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: 2025–07–11 Bombardier, Inc.: Amendment 39–23013; Docket No. FAA–2024–2720; Project Identifier MCAI–2024–00129–T. (a) Effective Date This airworthiness directive (AD) is effective July 2, 2025. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc., Model BD–700–1A10 and BD–700–1A11 airplanes, certificated in any category, serial numbers (S/Ns) 60001 through 60076 inclusive, 60083, 60087, and 60089. (d) Subject Air Transport Association (ATA) of America Code 29, Hydraulic Power. (e) Unsafe Condition This AD was prompted by reports of engine-driven pump hydraulic pressure hoses for hydraulic systems number 1 and 2 chafing against the pylon in the aft equipment bay. The FAA is issuing this AD to address the chafing of the hydraulic systems engine-driven pump hydraulic pressure hoses for the hydraulic system against the pylon, which may lead to hydraulic system leaks and failures and result in the loss of the affected hydraulic system. Loss of both hydraulic systems number 1 and 2 would substantially reduce the airplane’s functional capabilities. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection of Engine-Driven Pump Hydraulic Hoses Within 500 flight hours or 18 months after the effective date of this AD, whichever occurs first, do a borescope inspection of the routing of hydraulic systems number 1, left- hand side, and number 2, right-hand side, engine-driven pump pressure hoses over the length of the hoses for any damage and for minimum clearance between the engine- driven pump hydraulic pressure hose and case drain, suction pressure hose, and surrounding pylon structure, in accordance with section 2.B. of the Accomplishment Instructions of the applicable service information identified in paragraph (g)(1) through (3) of this AD. (1) For airplanes identified in Bombardier Service Bulletin 700–29–5502, dated November 29, 2023: Bombardier Service Bulletin 700–29–5502, dated November 29, 2023. Where paragraph 1.A. of Bombardier Service Bulletin 700–29–5502, dated November 29, 2023, identifies ‘‘Model BD– 700–1A10 aircraft,’’ this AD requires replacing that text with ‘‘Model BD–700– 1A11 aircraft.’’ (2) For airplanes identified in Bombardier Service Bulletin 700–29–6011, dated November 29, 2023: Bombardier Service Bulletin 700–29–6011, dated November 29, 2023. (3) For airplanes identified in Bombardier Service Bulletin 700–29–6502, dated November 29, 2023: Bombardier Service Bulletin 700–29–6502, dated November 29, 2023. (h) Corrective Actions (1) If clearance is found to be less than 0.500 inch (12.70 mm) during the inspection required by paragraph (g) of this AD: Before further flight, adjust the applicable hose(s) to VerDate Sep<11>2014 15:49 May 27, 2025 Jkt 265001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\28MYR1.SGM 28MYR1 khammond on DSK9W7S144PROD with RULES

22455 Federal Register / Vol. 90, No. 101 / Wednesday, May 28, 2025 / Rules and Regulations obtain minimum clearance between the engine-driven pump hydraulic pressure hose and case drain, suction pressure hose, and surrounding pylon structure, in accordance with section 2.C. of the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1) through (3) of this AD. (2) If any damage (including fouling or chafing) is found during the inspection required by paragraph (g) of this AD: Before further flight, replace all damaged pressure hoses, in accordance with section 2.D. of the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1) through (3) of this AD. (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 Bombardier, Inc.’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 Joseph Catanzaro, 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) Bombardier Service Bulletin 700–29– 5502, dated November 29, 2023. (ii) Bombardier Service Bulletin 700–29– 6011, dated November 29, 2023. (iii) Bombardier Service Bulletin 700–29– 6502, dated November 29, 2023. (3) For Bombardier material identified in this AD, contact Bombardier Business Aircraft Customer Response Center, 400 Co ˆ te- Vertu Road West, Dorval, Que ´bec H4S 1Y9, Canada; telephone 514–855–2999; email ac.yul@aero.bombardier.com; website bombardier.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 April 3, 2025. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2025–09504 Filed 5–27–25; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2025–0203; Project Identifier MCAI–2024–00360–T; Amendment 39–23042; AD 2025–10–08] RIN 2120–AA64 Airworthiness Directives; ATR—GIE Avions de Transport Re ´ gional Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain ATR—GIE Avions de Transport Re ´gional Model ATR42–500 and ATR72–212A airplanes. This AD was prompted by a report of potential use of improper material during the production of vertical tail plane (VTP) fittings. This AD requires, for certain airplanes, an inspection for the material of affected fuselage-to-VTP fittings, an inspection report, and corrective actions, and, for certain other airplanes, part replacement, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective July 2, 2025. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 2, 2025. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2025–0203; 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 EASA material identified in this AD, contact EASA, Konrad-Adenauer- Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu. You may find this material on the EASA website at ad.easa.europa.eu. • You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available at regulations.gov under Docket No. FAA–2025–0203. FOR FURTHER INFORMATION CONTACT : Darren Gassetto, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 516–228–7323; email: 9-AVS-AIR- BACO-COS@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 ATR—GIE Avions de Transport Re ´gional Model ATR42–500 and ATR72–212A airplanes. The NPRM was published in the Federal Register on February 18, 2025 (90 FR 9698). The NPRM was prompted by AD 2024–0120, dated June 27, 2024 (EASA AD 2024– 0120) (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 that there was a report of potential use of improper material during the production of fuselage-to-VTP fittings. After this supplier production quality escape was found, further review identified the affected parts population and the airplanes equipped with the affected parts. VTP fittings made of improper material, if not detected and corrected, could reduce the structural integrity of the airplane. In the NPRM, the FAA proposed to require, for certain airplanes, an inspection for the material of affected fuselage-to-VTP fittings, an inspection report, and corrective actions, and, for certain other airplanes, part replacement, as specified in EASA AD 2024–0120. The FAA is issuing this AD VerDate Sep<11>2014 15:49 May 27, 2025 Jkt 265001 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\28MYR1.SGM 28MYR1 khammond on DSK9W7S144PROD with RULES