AD 2024-04-03

18769 Federal Register / Vol. 89, No. 52 / Friday, March 15, 2024 / Rules and Regulations required for normal and emergency operations. (b) Onset characteristics of each envelope protection function must be appropriate to the phase of flight and type of maneuver and must not conflict with the ability of the pilot to satisfactorily control the airplane flight path, speed, or attitude. (c) Excursions of a limited flight parameter beyond its nominal design limit value due to dynamic maneuvering, airframe and system tolerances, and non-steady atmospheric conditions must not result in unsafe flight characteristics or conditions. (d) Operation of envelope protection functions must not adversely affect aircraft control during expected levels of atmospheric disturbances, nor impede the application of recovery procedures in case of windshear. (e) Simultaneous activation of envelope protection functions must not result in adverse coupling or adverse priority. (f) In case of abnormal attitude or excursion of any flight parameters outside the protected boundaries, operation of envelope protection functions must not hinder airplane recovery. Issued in Kansas City, Missouri, on March 12, 2024. James David Foltz, Manager, Technical Policy Branch, Policy and Standards Division, Aircraft Certification Service. [FR Doc. 2024–05661 Filed 3–13–24; 11:15 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–1995; Project Identifier MCAI–2023–00905–T; Amendment 39–22682; AD 2024–04–03] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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 April 19, 2024. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 19, 2024. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2023–1995; 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 material incorporated by reference in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; website easa.europa.eu. You may find this material on the EASA website at ad.easa.europa.eu. • You may view this material that is incorporated by reference 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 in the AD docket at regulations.gov under Docket No. FAA– 2023–1995. FOR FURTHER INFORMATION CONTACT : Timothy Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 817–222–5102; email timothy.p.dowling@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 Model A318–111, –112, –121, and –122; A319–111, –112, –113, –114, –115, –131, –132, –133, –151N, –153N, and –171N; A320–211, –212, –214, –216, –231, –232, –233, –251N, –252N, –253N, –271N, –272N, and –273N; and A321–111, –112, –131, –211, –212, –213, –231, –232, –251N, –251NX, –252N, –252NX, –253N, –253NX, –271N, –271NX, –272N, and –272NX airplanes. The NPRM published in the Federal Register on October 17, 2023 (88 FR 71506). The NPRM was prompted by AD 2023–0151, dated July 25, 2023 (EASA AD 2023– 0151) (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 new or more restrictive airworthiness limitations have been developed. In the NPRM, the FAA proposed to require a task (limitation) related to the center wing box front spar stiffeners already in Airbus A318/A319/A320/ A321 ALS Part 2 DT–ALI Revision 09 or A318/A319/A320/A321 ALS Part 2 DT– ALI Revision 09 Variation 9.2 that are required by EASA AD 2022–0085 and EASA AD 2023–0008 respectively (which correspond to FAA AD 2023– 13–10, Amendment 39–22495 (88 FR 50005, August 1, 2023) (AD 2023–13– 10)), and that incorporation of EASA AD 2023–0151 invalidates (terminates) prior instructions for that task. This AD therefore terminates the limitations for tasks identified in the service information referenced in EASA AD 2023–0151 only, as required by paragraph (o) of AD 2023–13–10. The FAA is issuing this AD to address fatigue cracking, accidental damage, or corrosion in principal structural elements, which could result in reduced structural integrity of the airplane. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2023–1995. Discussion of Final Airworthiness Directive Comments The FAA received a comment from United Airlines (UAL). The following presents the comment received on the NPRM and the FAA’s response. Request To Allow Extensions to Certain Compliance Times UAL requested that the AD allow extensions provided in an Airbus approved Airbus Statement of Airworthiness Compliance (ASAC), when it supports extensions to compliance time of specified ALS part 2 tasks, as an alternative method of compliance (AMOC). UAL noted that Airbus does not have the authority for Design Organization Approval signatures on ASACs, and that Airbus analysis and technical substantiations justifying the extensions provided in an ASAC provide an acceptable level of safety to ensure that the structural integrity of the aircraft is maintained. VerDate Sep<11>2014 16:00 Mar 14, 2024 Jkt 262001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 E:\FR\FM\15MRR1.SGM 15MRR1 khammond on DSKJM1Z7X2PROD with RULES

18770 Federal Register / Vol. 89, No. 52 / Friday, March 15, 2024 / Rules and Regulations The FAA does not agree since the FAA needs to review each individual extension request, which can then be supported through the AMOC process, provided sufficient justification is available. Sufficient justification, supported by an acceptable level of safety, is needed to grant such a request. In such situations, the operator should work with the FAA as early as possible. This AD has not been changed with regard to this request. 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, considered the comment 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 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. Related Service Information Under 1 CFR Part 51 The FAA reviewed EASA AD 2023– 0151, which specifies new or more restrictive airworthiness limitations for airplane structures and safe life limits. 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 1,680 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: The FAA has determined that revising the existing maintenance or inspection program takes an average of 90 work- hours per operator, although the agency recognizes that this number may vary from operator to operator. Since operators incorporate maintenance or inspection program changes for their affected fleet(s), the FAA has determined that a per-operator estimate is more accurate than a per-airplane estimate. Therefore, the agency estimates the average total cost per operator to be $7,650 (90 work-hours × $85 per work-hour). 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: 2024–04–03 Airbus SAS: Amendment 39– 22682; Docket No. FAA–2023–1995; Project Identifier MCAI–2023–00905–T. (a) Effective Date This airworthiness directive (AD) is effective April 19, 2024. (b) Affected ADs This AD affects AD 2023–13–10, Amendment 39–22495 (88 FR 50005, August 1, 2023) (AD 2023–13–10). (c) Applicability This AD applies to Airbus SAS airplanes specified in paragraphs (c)(1) through (4) of this AD, certificated in any category, with an original airworthiness certificate or original export certificate of airworthiness issued on or before May 12, 2023. (1) Model A318–111, –112, –121, and –122 airplanes. (2) Model A319–111, –112, –113, –114, –115, –131, –132, –133, –151N, –153N, and –171N airplanes. (3) Model A320–211, –212, –214, –216, –231, –232, –233, –251N, –252N, –253N, –271N, –272N, and –273N airplanes. (4) Model A321–111, –112, –131, –211, –212, –213, –231, –232, –251N, –251NX, –252N, –252NX, –253N, –253NX, –271N, –271NX, –272N, and –272NX airplanes. (d) Subject Air Transport Association (ATA) of America Code 05, Time Limits/Maintenance Checks. (e) Unsafe Condition This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address fatigue cracking, accidental damage, or corrosion in principal structural elements, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements 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 (EASA) AD 2023–0151, dated July 25, 2023 (EASA AD 2023–0151). (h) Exceptions to EASA AD 2023–0151 (1) This AD does not adopt the requirements specified in paragraph (1) and (2) of EASA AD 2023–0151. (2) Where paragraph (3) of EASA AD 2023– 0151 specifies ‘‘Within 12 months after the effective date of this AD, revise the approved AMP,’’ this AD requires replacing that text with ‘‘Within 90 days after the effective date of this AD, revise the existing maintenance or inspection program, as applicable.’’ (3) The initial compliance time for doing the tasks specified in paragraph (3) of EASA AD 2023–0151 is at the applicable ‘‘associated thresholds’’ as incorporated by the requirements of paragraph (3) of EASA AD 2023–0151, or within 90 days after the effective date of this AD, whichever occurs later. VerDate Sep<11>2014 16:00 Mar 14, 2024 Jkt 262001 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 E:\FR\FM\15MRR1.SGM 15MRR1 khammond on DSKJM1Z7X2PROD with RULES

18771 Federal Register / Vol. 89, No. 52 / Friday, March 15, 2024 / Rules and Regulations (4) This AD does not adopt the provisions specified in paragraph (4) of EASA AD 2023– 0151. (5) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2023–0151. (i) Provisions for Alternative Actions and Intervals After the existing maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions ( e.g., inspections) and intervals are allowed unless they are approved as specified in the provisions of the ‘‘Ref. Publications’’ section of EASA AD 2023–0151. (j) Terminating Action for Certain Tasks Required by AD 2023–13–10 Accomplishing the actions required by this AD terminates the corresponding requirements of AD 2023–13–10 for the tasks identified in the service information referenced in EASA AD 2023–0151 only. (k) 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 International Validation Branch, send it to the attention of the person identified in paragraph (l) of this AD. Information may be emailed to: 9-AVS-AIR-730-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. (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 EASA; or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (l) Additional Information For more information about this AD, contact Timothy Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 817– 222–5102; email timothy.p.dowling@faa.gov. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2023–0151, dated July 25, 2023. (ii) [Reserved] (3) For EASA AD 2023–0151, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +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 that is incorporated by reference 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 March 11, 2024. Victor Wicklund, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024–05491 Filed 3–14–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–0465; Project Identifier AD–2024–00139–E,R; Amendment 39–22702; AD 2024–05–51] RIN 2120–AA64 Airworthiness Directives; General Electric Company Engines, and Various Restricted Category Rotorcraft AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule; request for comments. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) Model CT7–2E1, CT7–2F1, CT7–8A, CT7–8E, CT7–8F5 engines, and various restricted category helicopters with GE Model T700–GE–700,–701A, –701C, –701D/CC, –701D, –401, –401C, CT7–2D or CT7– 2D1 engines installed. This AD was prompted by at least four reports of failures of the torque reference tube magnetic insert braze joint of the power turbine drive shaft assembly within the last several months. This AD requires a phase array ultrasonic inspection of the torque reference tube magnetic insert braze joint of the power turbine drive shaft assembly for inadequate braze coverage, and repair or replacement of the power turbine drive shaft assembly if necessary. The FAA previously sent an emergency AD to all known U.S. owners and operators of these engines and helicopters and is now issuing this AD to address the unsafe condition on these products. DATES : This AD is effective April 1, 2024. Emergency AD 2024–05–51, issued on February 28, 2024, which contained the requirements of this amendment, was effective with actual notice. The Director of the Federal Register approved the incorporation by reference of certain publications identified in this AD as of April 1, 2024. The FAA must receive comments on this AD by April 29, 2024. 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–2024–0465; 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 service information that is incorporated by reference, contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; phone: (513) 552–3272; email: aviation.fleetsupport@ge.com; website: ge.com . • You may view this service information that is incorporated by reference at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. 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–2024–0465. FOR FURTHER INFORMATION CONTACT : Barbara Caufield, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238–7146; email: barbara.caufield@ faa.gov . SUPPLEMENTARY INFORMATION : Comments Invited The FAA invites you to send any written data, views, or arguments about VerDate Sep<11>2014 16:00 Mar 14, 2024 Jkt 262001 PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 E:\FR\FM\15MRR1.SGM 15MRR1 khammond on DSKJM1Z7X2PROD with RULES