Airworthiness Directives; Airbus SAS Airplanes, 97564-97567 [2024-28758]

Download as PDF 97564 Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Proposed Rules possibly leading to an undetected fire and consequent reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements 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, EASA AD 2024– 0119. (h) Exceptions to EASA AD 2024–0119 (1) Where EASA AD 2024–0119 refers to its effective date, this AD requires using the effective date of this AD. (2) Where paragraph (1) of the EASA AD 2024–0119 states to ‘‘replace each affected part with a serviceable part in accordance with the instructions of the SB’’ this AD requires replacing that text with ‘‘replace each affected part with a serviceable part in accordance with the applicable tasks for removal and installation of the affected parts as specified in the accomplishment instructions of the SB.’’ (3) Where EASA AD 2024–0119 defines a serviceable part as ‘‘Engine pylon fire detector, eligible for installation in accordance with Airbus instructions, which is not an affected part’’ for this AD replace that text with ‘‘Engine pylon fire detector, eligible for installation that is not an affected part.’’ (4) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2024–0119. ddrumheller on DSK120RN23PROD with PROPOSALS1 (i) No Return of Parts Requirement Although the material referenced in EASA AD 2024–0119 specifies to send affected pylon fire detectors to Kidde Technologies Inc., 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, AIR–520, Continued Operational Safety 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 AIR–520, Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (k) 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, AIR–520, Continued Operational Safety Branch, FAA; or EASA; or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, VerDate Sep<11>2014 15:30 Dec 06, 2024 Jkt 265001 the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): Except as required by paragraph (i) of this AD, if any material 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, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 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 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) European Union Aviation Safety Agency (EASA) AD 2024–0119, dated June 27, 2024. (ii) [Reserved] (3) 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; website easa.europa.eu. You may find this material 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 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 December 3, 2024. Peter A. White, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2024–28759 Filed 12–6–24; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–2548; Project Identifier MCAI–2024–00401–T] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus SAS Model A318 series airplanes, Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. This proposed AD was prompted by cracks being found during full-scale fatigue testing of the keel beam bottom panel between the edge profile and stringer run-out at a certain frame and stringer. This proposed AD would require repetitive special detailed inspections (SDI) of the affected area, and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference (IBR). The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by January 23, 2025. 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–2024–2548; 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 NPRM, the mandatory SUMMARY: E:\FR\FM\09DEP1.SGM 09DEP1 Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Proposed Rules continuing airworthiness information (MCAI), any comments received, and other information. The street address for Docket Operations is listed above. Material Incorporated by Reference: • For EASA material identified in this proposed AD, contact EASA, KonradAdenauer-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. It is also available at regulations.gov under Docket No. FAA– 2024–2548. • 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. FOR FURTHER INFORMATION CONTACT: Timothy Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206–231–3667; email Timothy.P.Dowling@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2024–2548; Project Identifier MCAI–2024–00401–T’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, 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 proposal 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 substantive verbal contact received about this NPRM. ddrumheller on DSK120RN23PROD with PROPOSALS1 Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as VerDate Sep<11>2014 15:30 Dec 06, 2024 Jkt 265001 private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Timothy Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206–231–3667; email Timothy.P.Dowling@faa.gov. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2024–0135, dated July 10, 2024 (EASA AD 2024– 0135) (also referred to as the MCAI), to correct an unsafe condition for certain Airbus SAS Model A318 series airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes, Model A320–211, –212, –214, –215, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. Model A320–215 airplanes are not certificated by the FAA and are not included on the U.S. type certificate data sheet; this proposed AD therefore does not include those airplanes in the applicability. The MCAI states that during full-scale fatigue testing, cracks were found on the keel beam bottom panel between the edge profile and stringer run-out at frame 46 and stringer 37, left- and right-hand sides. Crack propagation in this area could possibly result in reduced structural integrity of the airplane. The FAA is proposing 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–2024–2548. Material Incorporated by Reference Under 1 CFR Part 51 EASA AD 2024–0135 specifies procedures for repetitive SDIs for discrepancies (cracks) of the keel beam bottom panel between the edge profile and stringer run-out at frame 46 and stringer 37, left-hand and right-hand sides. EASA AD 2024–0135 also specifies corrective actions including crack repair. This material is reasonably available because the interested parties have access to it through their normal course PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 97565 of business or by the means identified in the ADDRESSES section. FAA’s Determination 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 is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements in This NPRM This proposed AD would require accomplishing the actions specified in EASA AD 2024–0135 described previously, except for any differences identified as exceptions in the regulatory text of this proposed AD. Explanation of Required Compliance Information In the FAA’s ongoing efforts to improve the efficiency of the AD process, the FAA developed a process to use some civil aviation authority (CAA) ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. The FAA has been coordinating this process with manufacturers and CAAs. As a result, the FAA proposes to incorporate EASA AD 2024–0135 by reference in the FAA final rule. This proposed AD would, therefore, require compliance with EASA AD 2024–0135 in its entirety through that incorporation, except for any differences identified as exceptions in the regulatory text of this proposed AD. Using common terms that are the same as the heading of a particular section in EASA AD 2024–0135 does not mean that operators need comply only with that section. For example, where the AD requirement refers to ‘‘all required actions and compliance times,’’ compliance with this AD requirement is not limited to the section titled ‘‘Required Action(s) and Compliance Time(s)’’ in EASA AD 2024–0135. Material required by EASA AD 2024– 0135 for compliance will be available at regulations.gov under Docket No. FAA– 2024–2548 after the FAA final rule is published. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 1,920 airplanes of U.S. registry. The FAA E:\FR\FM\09DEP1.SGM 09DEP1 97566 Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Proposed Rules estimates the following costs to comply with this proposed AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Parts cost Cost per product Cost on U.S. operators 16 work-hours × $85 per hour = $1,360 ..................................................................................... $0 $1,360 $2,611,200 The FAA has received no definitive data on which to base the cost estimates for the on-condition repairs specified in this proposed AD. 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. ddrumheller on DSK120RN23PROD with PROPOSALS1 Regulatory Findings The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska, and (3) Would 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. VerDate Sep<11>2014 15:30 Dec 06, 2024 Jkt 265001 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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: ■ Airbus SAS: Docket No. FAA–2024–2548; Project Identifier MCAI–2024–00401–T. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by January 23, 2025. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus SAS airplanes, certificated in any category, as identified in paragraphs (c)(1) through (4) of this AD and in European Union Aviation Safety Agency (EASA) AD 2024–0135, dated July 10, 2024 (EASA AD 2024–0135). (1) Model A318–111, –112, –121, and –122 airplanes. (2) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes. (4) Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by cracks being found during full-scale fatigue testing of the keel beam bottom panel between the edge profile and stringer run-out at frame 46 and stringer 37, left- and right-hand sides. The FAA is issuing this AD to address the unsafe condition on these products. The unsafe condition, if not addressed, could result in crack propagation, possibly resulting in reduced structural integrity of the airplane. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements 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, EASA AD 2024– 0135. (h) Exceptions to EASA AD 2024–0135 (1) Where EASA AD 2024–0135 refers to its effective date, this AD requires using the effective date of this AD. (2) Where paragraph (2) of EASA AD 2024– 0135 specifies ‘‘if, during any inspection as required by paragraph (1) of this AD, discrepancies are detected, as defined in the SB, before next flight, contact Airbus for approved repair instructions and accomplish those instructions accordingly,’’ this AD requires replacing that text with ‘‘if, during any inspection as required by paragraph (1) of this AD, any cracking is detected, the cracking must be repaired before further flight using a method approved by the Manager, AIR–520, Continued Operational Safety 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) Where paragraph (3) of EASA AD 2024– 0135 does not allow corrective action as terminating action for the repetitive inspection requirements ‘‘unless otherwise stated in the repair instructions provided by Airbus,’’ this AD requires that any terminating action be approved in accordance with the procedures specified in paragraph (j)(1) of this AD. (4) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2024–0135. (i) No Reporting Requirement Although the material referenced in EASA AD 2024–0135 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, AIR–520, Continued Operational Safety 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 AIR–520, Continued Operational Safety Branch, send it to the E:\FR\FM\09DEP1.SGM 09DEP1 Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Proposed Rules attention of the person identified in paragraph (k) 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, AIR–520, Continued Operational Safety Branch, FAA; or EASA; or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): Except as required by paragraph (j)(2) of this AD, if any material 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 Timothy Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206– 231–3667; email Timothy.P.Dowling@faa.gov. ddrumheller on DSK120RN23PROD with PROPOSALS1 (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 this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2024–0135, dated July 10, 2024. (ii) [Reserved] (3) 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; website easa.europa.eu. You may find this material 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 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-locationsoremailfr.inspection@nara.gov. VerDate Sep<11>2014 15:30 Dec 06, 2024 Jkt 265001 Issued on December 3, 2024. Peter A. White, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2024–28758 Filed 12–6–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2024–2591; Airspace Docket No. 24–AGL–26] RIN 2120–AA66 Amendment of VOR Federal Airways V–38, V–133, and V–144, and Revocation of VOR Federal Airway V– 214 in the Vicinity of Zanesville, OH Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This action proposes to amend Very High Frequency Omnidirectional Range (VOR) Federal Airways V–38, V–133, and V–144; and to revoke VOR Federal Airway V–214. The FAA is proposing this action due to the planned decommissioning of the VOR portion of the Zanesville, OH (ZZV), VOR/Distance Measuring Equipment (VOR/DME) navigational aid (NAVAID). The Zanesville VOR is being decommissioned in support of the FAA’s VOR Minimum Operational Network (MON) program. DATES: Comments must be received on or before January 23, 2025. ADDRESSES: Send comments identified by FAA Docket No. FAA–2024–2591 and Airspace Docket No. 24–AGL–26 using any of the following methods: * Federal eRulemaking Portal: Go to www.regulations.gov and follow the online instructions for sending your comments electronically. * Mail: Send comments to Docket Operations, M–30; U.S. Department of Transportation, 1200 New Jersey Avenue SE, Room W12–140, West Building Ground Floor, Washington, DC 20590–0001. * Hand Delivery or Courier: Take comments to Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. * Fax: Fax comments to Docket Operations at (202) 493–2251. Docket: Background documents or comments received may be read at SUMMARY: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 97567 www.regulations.gov at any time. Follow the online instructions for accessing the docket or go to the Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. FAA Order JO 7400.11J, Airspace Designations and Reporting Points, and subsequent amendments can be viewed online at www.faa.gov/air_traffic/ publications/. You may also contact the Rules and Regulations Group, Office of Policy, Federal Aviation Administration, 600 Independence Avenue SW, Washington, DC 20597; telephone: (202) 267–8783. FOR FURTHER INFORMATION CONTACT: Colby Abbott, Rules and Regulations Group, Office of Policy, Federal Aviation Administration, 600 Independence Avenue SW, Washington, DC 20597; telephone: (202) 267–8783. SUPPLEMENTARY INFORMATION: Authority for This Rulemaking The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. 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. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart I, Section 40103. Under that section, the FAA is charged with prescribing regulations to assign the use of the airspace necessary to ensure the safety of aircraft and the efficient use of airspace. This regulation is within the scope of that authority as it would modify the National Airspace System as necessary to preserve the safe and efficient flow of air traffic. Comments Invited The FAA invites interested persons to participate in this rulemaking by submitting written comments, data, or views. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should submit only one time if comments are filed electronically, or commenters should send only one copy of written comments if comments are filed in writing. E:\FR\FM\09DEP1.SGM 09DEP1

Agencies

[Federal Register Volume 89, Number 236 (Monday, December 9, 2024)]
[Proposed Rules]
[Pages 97564-97567]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-28758]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-2548; Project Identifier MCAI-2024-00401-T]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus SAS Model A318 series airplanes, Model A319-111, -
112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, 
-212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -
112, -131, -211, -212, -213, -231, and -232 airplanes. This proposed AD 
was prompted by cracks being found during full-scale fatigue testing of 
the keel beam bottom panel between the edge profile and stringer run-
out at a certain frame and stringer. This proposed AD would require 
repetitive special detailed inspections (SDI) of the affected area, and 
corrective actions if necessary, as specified in a European Union 
Aviation Safety Agency (EASA) AD, which is proposed for incorporation 
by reference (IBR). The FAA is proposing this AD to address the unsafe 
condition on these products.

DATES: The FAA must receive comments on this proposed AD by January 23, 
2025.

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-2024-2548; 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 NPRM, the mandatory

[[Page 97565]]

continuing airworthiness information (MCAI), any comments received, and 
other information. The street address for Docket Operations is listed 
above.
    Material Incorporated by Reference:
     For EASA material identified in this proposed AD, contact 
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
8999 000; email [email protected]; website easa.europa.eu. You may 
find this material on the EASA website at ad.easa.europa.eu. It is also 
available at regulations.gov under Docket No. FAA-2024-2548.
     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.

FOR FURTHER INFORMATION CONTACT: Timothy Dowling, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
telephone 206-231-3667; email [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2024-2548; 
Project Identifier MCAI-2024-00401-T'' at the beginning of your 
comments. The most helpful comments reference a specific portion of the 
proposal, 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 proposal 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 substantive verbal 
contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to 
Timothy Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, 
Suite 410, Westbury, NY 11590; telephone 206-231-3667; email 
[email protected]. Any commentary that the FAA receives which 
is not specifically designated as CBI will be placed in the public 
docket for this rulemaking.

Background

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2024-0135, dated July 10, 2024 (EASA 
AD 2024-0135) (also referred to as the MCAI), to correct an unsafe 
condition for certain Airbus SAS Model A318 series airplanes; Model 
A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes, Model 
A320-211, -212, -214, -215, -216, -231, -232, and -233 airplanes; and 
Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. 
Model A320-215 airplanes are not certificated by the FAA and are not 
included on the U.S. type certificate data sheet; this proposed AD 
therefore does not include those airplanes in the applicability. The 
MCAI states that during full-scale fatigue testing, cracks were found 
on the keel beam bottom panel between the edge profile and stringer 
run-out at frame 46 and stringer 37, left- and right-hand sides. Crack 
propagation in this area could possibly result in reduced structural 
integrity of the airplane.
    The FAA is proposing 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-2024-2548.

Material Incorporated by Reference Under 1 CFR Part 51

    EASA AD 2024-0135 specifies procedures for repetitive SDIs for 
discrepancies (cracks) of the keel beam bottom panel between the edge 
profile and stringer run-out at frame 46 and stringer 37, left-hand and 
right-hand sides. EASA AD 2024-0135 also specifies corrective actions 
including crack repair.
    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.

FAA's Determination

    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 is issuing this NPRM after determining that 
the unsafe condition described previously is likely to exist or develop 
in other products of the same type design.

Proposed AD Requirements in This NPRM

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2024-0135 described previously, except for any differences 
identified as exceptions in the regulatory text of this proposed AD.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA developed a process to use some civil aviation 
authority (CAA) ADs as the primary source of information for compliance 
with requirements for corresponding FAA ADs. The FAA has been 
coordinating this process with manufacturers and CAAs. As a result, the 
FAA proposes to incorporate EASA AD 2024-0135 by reference in the FAA 
final rule. This proposed AD would, therefore, require compliance with 
EASA AD 2024-0135 in its entirety through that incorporation, except 
for any differences identified as exceptions in the regulatory text of 
this proposed AD. Using common terms that are the same as the heading 
of a particular section in EASA AD 2024-0135 does not mean that 
operators need comply only with that section. For example, where the AD 
requirement refers to ``all required actions and compliance times,'' 
compliance with this AD requirement is not limited to the section 
titled ``Required Action(s) and Compliance Time(s)'' in EASA AD 2024-
0135. Material required by EASA AD 2024-0135 for compliance will be 
available at regulations.gov under Docket No. FAA-2024-2548 after the 
FAA final rule is published.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 1,920 airplanes of U.S. registry. The FAA

[[Page 97566]]

estimates the following costs to comply with this proposed AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
16 work-hours x $85 per hour = $1,360........................              $0           $1,360       $2,611,200
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition repairs specified in this proposed AD.

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

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would 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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

Airbus SAS: Docket No. FAA-2024-2548; Project Identifier MCAI-2024-
00401-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by January 23, 2025.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus SAS airplanes, certificated in any 
category, as identified in paragraphs (c)(1) through (4) of this AD 
and in European Union Aviation Safety Agency (EASA) AD 2024-0135, 
dated July 10, 2024 (EASA AD 2024-0135).
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by cracks being found during full-scale 
fatigue testing of the keel beam bottom panel between the edge 
profile and stringer run-out at frame 46 and stringer 37, left- and 
right-hand sides. The FAA is issuing this AD to address the unsafe 
condition on these products. The unsafe condition, if not addressed, 
could result in crack propagation, possibly resulting 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 paragraphs (h) and (i) of this AD: Comply 
with all required actions and compliance times specified in, and in 
accordance with, EASA AD 2024-0135.

(h) Exceptions to EASA AD 2024-0135

    (1) Where EASA AD 2024-0135 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where paragraph (2) of EASA AD 2024-0135 specifies ``if, 
during any inspection as required by paragraph (1) of this AD, 
discrepancies are detected, as defined in the SB, before next 
flight, contact Airbus for approved repair instructions and 
accomplish those instructions accordingly,'' this AD requires 
replacing that text with ``if, during any inspection as required by 
paragraph (1) of this AD, any cracking is detected, the cracking 
must be repaired before further flight using a method approved by 
the Manager, AIR-520, Continued Operational Safety 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) Where paragraph (3) of EASA AD 2024-0135 does not allow 
corrective action as terminating action for the repetitive 
inspection requirements ``unless otherwise stated in the repair 
instructions provided by Airbus,'' this AD requires that any 
terminating action be approved in accordance with the procedures 
specified in paragraph (j)(1) of this AD.
    (4) This AD does not adopt the ``Remarks'' section of EASA AD 
2024-0135.

(i) No Reporting Requirement

    Although the material referenced in EASA AD 2024-0135 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, AIR-
520, Continued Operational Safety 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 
AIR-520, Continued Operational Safety Branch, send it to the

[[Page 97567]]

attention of the person identified in paragraph (k) of this AD and 
email to: [email protected]. 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, AIR-520, 
Continued Operational Safety 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 
paragraph (j)(2) of this AD, if any material 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 Timothy Dowling, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; telephone 206-231-3667; email 
[email protected].

(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 this AD specifies otherwise.
    (i) European Union Aviation Safety Agency (EASA) AD 2024-0135, 
dated July 10, 2024.
    (ii) [Reserved]
    (3) For EASA material identified in this AD, contact EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
8999 000; email [email protected]; website easa.europa.eu. You may 
find this material 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 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/[email protected]">www.archives.gov/federal-register/cfr/[email protected].

    Issued on December 3, 2024.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2024-28758 Filed 12-6-24; 8:45 am]
BILLING CODE 4910-13-P
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