AD 2022-24-03

74294 Federal Register / Vol. 87, No. 232 / Monday, December 5, 2022 / Rules and Regulations (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 25, Equipment/Furnishings. (e) Unsafe Condition This AD was prompted by a report that damage (including delamination of work deck, and corroded and cracked retainer blocks) was found during inspection of certain galleys. The FAA is issuing this AD to detect and correct damage that could affect the galley’s capability to hold the trolley under emergency landing loads, which could lead to trolley detachment, possibly resulting in blocking of an escape path during an emergency exit. (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 2021–0183R1, dated September 20, 2021 (EASA AD 2021– 0183R1). (h) Exceptions to EASA AD 2021–0183R1 (1) Where EASA AD 2021–0183R1 refers to its effective date, this AD requires using the effective date of this AD. (2) Where EASA AD 2021–0183R1 refers to ‘‘18 August 2021,’’ this AD requires using the effective date of this AD. (3) The ‘‘Remarks’’ section of EASA AD 2021–0183R1 does not apply to this AD. (4) Where EASA AD 2021–0183R1 does not specify corrective action after a post-repair inspection that has findings of damage, this AD requires obtaining repair instructions before further flight from the FAA, EASA, or Airbus SAS’s EASA Design Organization Approval (DOA) and accomplishing those actions accordingly. If approved by the DOA, the approval must include the DOA- authorized signature. (i) No Reporting Requirement Although the service information referenced in EASA AD 2021–0183R1 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) 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, International Validation Branch, mail it to the address identified in paragraph (k) of this AD or email to: 9-AVS- AIR-730-AMOC@faa.gov. If mailing information, also submit information by email. 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 EASA; or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraphs (i) and (j)(2) of this AD, if any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (k) Additional Information For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3229; email vladimir.ulyanov@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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 2021–0183R1, dated September 20, 2021. (ii) [Reserved] (3) For EASA AD 2021–0183R1, 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 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 that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fr.inspection@nara.gov, or go to: www.archives.gov/federal-register/cfr/ibr- locations.html. Issued on November 9, 2022. Christina Underwood, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–26357 Filed 12–2–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2022–1155; Project Identifier MCAI–2022–00655–T; Amendment 39–22243; AD 2022–24–03] 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 all Airbus SAS Model A321–251N, A321– 251NX, A321–252N, A321–252NX, A321–253N, and A321–253NX airplanes. This AD was prompted by a stress analysis on the engine structure that indicated that the fail-safe lug may not be able to sustain, during one inspection interval as currently specified in an airworthiness limitations item, the loads deriving from the engagement of the secondary load path within that inspection interval for the aft engine mount system. This AD requires repetitive detailed inspections of the aft engine mount and secondary load path clearance fail-safe pin and replacement of the engine if necessary, 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 January 9, 2023. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 9, 2023. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2022–1155; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket VerDate Sep<11>2014 17:46 Dec 02, 2022 Jkt 259001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\05DER1.SGM 05DER1 ddrumheller on DSK30NT082PROD with RULES

74295 Federal Register / Vol. 87, No. 232 / Monday, December 5, 2022 / Rules and Regulations 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 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– 2022–1155. FOR FURTHER INFORMATION CONTACT : Dan Rodina, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th Street Des Moines, WA 98198; telephone 206–231–3225; email dan.rodina@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 SAS Model A321– 251N, A321–251NX, A321–252N, A321–252NX, A321–253N, and A321– 253NX airplanes. The NPRM published in the Federal Register on September 12, 2022 (87 FR 55737). The NPRM was prompted by AD 2022–0089, dated May 17, 2022, issued by EASA, which is the Technical Agent for the Member States of the European Union (referred to after this as the MCAI). The MCAI states that the engine fail safe lug may not be able to sustain, during one inspection interval as currently specified in airworthiness limitation item (ALI) task 712232–01–1, the loads deriving from the engagement of the secondary load path. This condition, if not detected and corrected, could lead to engine mount rupture, possibly resulting in engine loss during flight and loss of control of the airplane. In the NPRM, the FAA proposed to require repetitive detailed inspections of the aft engine mount and secondary load path clearance fail-safe pin and replacement of the engine if necessary, as specified in EASA AD 2022–0089. The FAA is issuing this AD to address the unsafe condition on these products. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2022–1155. Discussion of Final Airworthiness Directive Comments The FAA received comments from Air Line Pilots Association, International (ALPA) and an anonymous commenter. Both commenters supported the NPRM without change. 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 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 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 EASA AD 2022–0089 specifies procedures for repetitive detailed inspections (DET) for discrepancies of the aft engine mount and secondary load path clearance fail-safe pin for each engine, and replacement of any engine with discrepant findings on the secondary load path clearance check. 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 156 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: E STIMATED C OSTS FOR R EQUIRED A CTIONS Labor cost Parts cost Cost per product Cost on U.S. operators Up to 4 work-hours × $85 per hour = $340 ............... $0 Up to $340 ..................................... Up to $53,040. The FAA estimates that it would take 64 work-hours (at $85 per work-hour) to replace an engine, if required based on the results of any required actions. The FAA has received no definitive data on which to base the estimate for the cost of a replacement engine or any necessary additional on-condition actions that would be required by this AD. The FAA has no way of determining the number of aircraft that might need these on-condition actions. 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 VerDate Sep<11>2014 17:46 Dec 02, 2022 Jkt 259001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\05DER1.SGM 05DER1 ddrumheller on DSK30NT082PROD with RULES

74296 Federal Register / Vol. 87, No. 232 / Monday, December 5, 2022 / Rules and Regulations 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: 2022–24–03 Airbus SAS: Amendment 39– 22243; Docket No. FAA–2022–1155; Project Identifier MCAI–2022–00655–T. (a) Effective Date This airworthiness directive (AD) is effective January 9, 2023. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus SAS Model A321–251N, A321–251NX, A321–252N, A321–252NX, A321–253N, and A321–253NX airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Unsafe Condition This AD was prompted by a stress analysis on the engine structure that indicated that the fail-safe lug may not be able to sustain, during one inspection interval, as currently specified in airworthiness limitation item (ALI) task 712232–01–1, the loads deriving from the engagement of the secondary load path within that inspection interval for the aft engine mount system. The FAA is issuing this AD to address potential failure of the LEAP–1A aft engine mount waiting fail-safe male lug, which could lead to engine mount rupture, possibly resulting in engine loss during flight and loss of control 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 2022–0089, dated May 17, 2022 (EASA AD 2022–0089). (h) Exceptions to EASA AD 2022–0089 (1) Where paragraph (3) of EASA AD 2022– 0089 specifies corrective action if ‘‘discrepancies are detected, as defined in the SB,’’ for purposes of this AD, discrepancies include a fail-safe pin that does not rotate freely, or has damage (dents, scratches, nicks, corrosion, or cracks). (2) The ‘‘Remarks’’ section of EASA AD 2022–0089 does not apply to this AD. (i) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, 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 Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (j) 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 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, Large Aircraft Section, 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. (j) Additional Information For more information about this AD, contact Dan Rodina, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198; telephone 206–231–3225; email dan.rodina@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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 2022–0089, dated May 17, 2022. (ii) [Reserved] (3) For EASA AD 2022–0089, 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 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 that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fr.inspection@nara.gov, or go to: www.archives.gov/federal-register/cfr/ibr- locations.html. Issued on November 9, 2022. Christina Underwood, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–26356 Filed 12–2–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2022–0890; Project Identifier MCAI–2022–00391–T; Amendment 39–22242; AD 2022–24–02] 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 A300 F4–600R series airplanes. This AD was prompted by a determination that the forward cargo door compartment between certain frame forks is susceptible to widespread fatigue damage (WFD). This AD completes certain mandated programs to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD requires modifying the forward cargo compartment between certain frame forks, 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 January 9, 2023. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 9, 2023. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2022–0890; 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 VerDate Sep<11>2014 17:46 Dec 02, 2022 Jkt 259001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\05DER1.SGM 05DER1 ddrumheller on DSK30NT082PROD with RULES