Airworthiness Directives; Airbus SAS Airplanes, 107063-107066 [2024-31378]

Download as PDF Federal Register / Vol. 89, No. 250 / Tuesday, December 31, 2024 / Proposed Rules (b) The committees must discuss related proposals with other committees. (c) The committees shall make recommendations to the House of Delegates as a whole concerning each proposal. The House of Delegates report shall show any proposed change in wording, record the votes on each proposal, and suggest an effective date for each proposal recommended for adoption. The individual committee reports shall be submitted to the chairperson of the House of Delegates, who will combine them into one report showing, in numerical sequence, the committee recommendations on each proposal. Once completed, the combined committee report will be distributed electronically to the Official State Agencies prior to the delegates voting on the final day of the House of Delegates conference. (d) The Technical Committee meetings shall be open to any interested person. Advocates for or against any proposal may appear before the appropriate committee and present their views. khammond on DSK9W7S144PROD with PROPOSALS § 149.7 House of Delegates consideration of proposed changes. (a) The chairperson of the House of Delegates shall be a representative of the Department. (b) At the time designated for voting on proposed changes by the official delegates, the chairman of the General Conference Committee and all committee chairpersons shall sit at the speaker’s table and assist the chairperson of the House of Delegates. (c) The chairperson shall set the rules of order for the General Conference Committee. (d) Proposals that have not been submitted in accordance with § 149.5 will be considered by the House of Delegates only with the unanimous consent of the General Conference Committee. Any such proposals must be referred to the appropriate committee for consideration before being presented for action by the House of Delegates. (e) Voting will be by States, and each official delegate, as determined by § 149.5, will be allowed one vote on each proposal pertaining to the program prescribed by the subpart which they represent. (f) A roll call of States for a recorded vote will be used when requested by a delegate or at the discretion of the chairman. (g) All motions on proposed changes shall be for adoption. (h) Proposed changes shall be adopted by a two-thirds majority vote of the official delegates present and voting. VerDate Sep<11>2014 17:13 Dec 30, 2024 Jkt 265001 (i) The House of Delegates conference shall be open to any interested person. § 149.8 Approval of House of Delegates recommendations by the Department. Proposals adopted by the official delegates will be recommended to the Department for incorporation into the provisions of the US SHIP in part 148 of this subchapter and this part. The Department reserves the right to approve or disapprove the recommendations of the House of Delegates as an integral part of its sponsorship of the US SHIP. § 149.9 Changes to the US SHIP Program Standards. The US SHIP Program Standards document contains content on the testing requirements for diseases covered by the regulations in part 148 of this subchapter, approved procedures for maintaining biosecurity at participating swine operations, traceability requirements for participating swine operations, and calculations for official delegate allocations. Changes to the US SHIP Program Standards document for any of the foregoing will be made in the following manner: (a) Normal process for updating the US SHIP Program Standards document. (1) APHIS will publish a notice in the Federal Register providing the proposed changes to the US SHIP Program Standards document and the basis for the changes. The notice will request public comment. (2) If no comments are received on the notice, or if the comments received do not call into question the basis for the changes, APHIS will publish a subsequent notice in the Federal Register announcing that the changes have been made to the US SHIP Program Standards document and making available the revised US SHIP Program Standards document. If comments identify concerns with the proposed revisions, APHIS will consider and address those comments as appropriate prior to taking any action to revise the US SHIP Program Standards. (b) Process for making immediate changes to the US SHIP Program Standards document. (1) If the Administrator determines that procedures for maintaining biosecurity and animal traceability at participating swine operations that are described in the US SHIP Program Standards document are not adequate or that testing procedures must be revised in order to ensure that they provide reliable assurances regarding test results, APHIS will make the relevant change to the US SHIP Program PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 107063 Standards document. As soon as is feasible, APHIS will publish a notice in the Federal Register announcing the change, as well as the basis for the change. The notice will request public comment. (2) APHIS may make further revisions to the US SHIP Program Standards document based on the comments received. Done in Washington, DC, this 23rd day of December 2024. Donna Lalli, Acting Administrator, Animal and Plant Health Inspection Service. [FR Doc. 2024–31386 Filed 12–30–24; 8:45 am] BILLING CODE 3410–34–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–2718; Project Identifier MCAI–2024–00319–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 all Airbus SAS Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –216, –231, –232, –233, –251N, –252N, –253N, –271N, –272N, and –273N airplanes; Model A321–211, –212, –213, –231, –232, –251N, –251NX, –252N, –252NX, –253N, –253NX, –253NY, –271N, –271NX, –272N, and –272NX airplanes; Airbus SAS Model A330–200 series airplanes; Model A330–300 series airplanes; Model A330–800 series airplanes; Model A330–900 series airplanes; Model A350–941 and –1041 airplanes; and Model A380–800 series airplanes. This proposed AD was prompted by a report of corrosion and cracks on the broadband antenna adapter plate during an inspection. This proposed AD would require repetitive general visual inspections (GVI) of the broadband antenna adapter plate, skirt, vents, and attachment fittings and limit the installation of affected parts under certain conditions, 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. SUMMARY: E:\FR\FM\31DEP1.SGM 31DEP1 107064 Federal Register / Vol. 89, No. 250 / Tuesday, December 31, 2024 / Proposed Rules The FAA must receive comments on this proposed AD by February 14, 2025. DATES: 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–2024–2718; 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 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– 2024–2718. • 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: Dan Rodina, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206– 231–3225; email Dan.Rodina@faa.gov. SUPPLEMENTARY INFORMATION: ADDRESSES: khammond on DSK9W7S144PROD with PROPOSALS 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–2024–2718; Project Identifier MCAI–2024–00319–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 VerDate Sep<11>2014 17:13 Dec 30, 2024 Jkt 265001 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 Dan Rodina, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206–231–3225; email Dan.Rodina@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 2024–0199, dated October 18, 2024 (EASA AD 2024–0199) (also referred to as the MCAI), to correct an unsafe condition for Airbus SAS Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –215, –216, –231, –232, –233, –251N, –252N, –253N, –271N, –272N, and –273N airplanes; Model A321–211, –212, –213, –231, –232, –251N, –251NX, –252N, –252NX, –253N, –253NX, –253NY, –271N, –271NX, –272N, and –272NX airplanes; Airbus SAS Model A330–200 series airplanes; Model A330–300 series airplanes; Model A330–800 series airplanes; Model A330–900 series airplanes; Model A350–941 and –1041 airplanes; and Model A380–800 series airplanes. PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 Model A320–215 airplanes are not certificated by the FAA and are not included on the U.S. type certificate data sheet; this AD therefore does not include those airplanes in the applicability. The MCAI states that corrosion and cracks were found on the broadband antenna adapter plate during an inspection. Further investigation determined that the broadband antenna adapter plate and skirt assembly-adapter are made of material susceptible to corrosion cracking, and that the recommended maintenance programs do not ensure timely detection of cracks and damage in this area. The FAA is proposing this AD to address the corrosion and cracks on the broadband antenna adapter plate and skirt assembly-adapter. The unsafe condition, if not addressed, could lead to in-flight detachment of the radome, antenna, and affected parts, which could impact the tail section of the airplane, possibly resulting in damage and reduced control of the airplane. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2024–2718. Material Incorporated by Reference Under 1 CFR Part 51 EASA AD 2024–0199 specifies procedures for repetitive general visual inspections (GVI) for cracks and corrosion of the broadband antenna adapter plate, skirt, vents, and attachment fittings, and, depending on findings, corrective actions including repair or replacement of the affected parts. EASA AD 2024–0199 also limits the installation of affected parts under certain conditions and requires reporting of the inspection results after each inspection. 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. E:\FR\FM\31DEP1.SGM 31DEP1 Federal Register / Vol. 89, No. 250 / Tuesday, December 31, 2024 / Proposed Rules this process with manufacturers and CAAs. As a result, the FAA proposes to incorporate EASA AD 2024–0199 by reference in the FAA final rule. This proposed AD would, therefore, require compliance with EASA AD 2024–0199 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 2024–0199 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 Proposed AD Requirements in This NPRM This proposed AD would require accomplishing the actions specified in EASA AD 2024–0199 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 107065 Time(s)’’ in EASA AD 2024–0199. Material required by EASA AD 2024– 0199 for compliance will be available at regulations.gov under Docket No. FAA– 2024–2718 after the FAA final rule is published. Interim Action The FAA considers that this proposed AD would be an interim action. The FAA anticipates that further AD action will follow. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 4 airplanes of U.S. registry. The FAA 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 Up to 61 work-hours × $85 per hour = $5,185 ....................................................................................... $0 Up to $5,185 Up to $20,740 The FAA estimates the following costs to do any on-condition action 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 this oncondition action: ESTIMATED COSTS OF ON-CONDITION ACTIONS Labor cost Parts cost Cost per product 50 work-hours × $85 per hour = $4,250 ........ $10,000 $14,250 The FAA has received no definitive data on which to base the cost estimates for the repairs specified in this proposed AD. khammond on DSK9W7S144PROD with PROPOSALS Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a currently valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to take approximately 1 hour per response, including the time for reviewing VerDate Sep<11>2014 17:13 Dec 30, 2024 Jkt 265001 instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. All responses to this collection of information are mandatory. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to: Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177–1524. 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 PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 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: E:\FR\FM\31DEP1.SGM 31DEP1 107066 Federal Register / Vol. 89, No. 250 / Tuesday, December 31, 2024 / Proposed Rules 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–2024–2718; Project Identifier MCAI–2024–00319–T. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by February 14, 2025. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus SAS Model airplanes specified in paragraphs (c)(1) through (6) of this AD, certificated in any category. (1) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (2) Model A320–211, –212, –214, –216, –231, –232, –233, –251N, –252N, –253N, –271N, –272N, and –273N airplanes. (3) Model A321–211, –212, –213, –231, –232, –251N, –251NX, –252N, –252NX, –253N, –253NX, –253NY, –271N, –271NX, –272N, and –272NX airplanes. (4) Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, –343, –841, and –941 airplanes. (5) Model A350–941 and –1041 airplanes. (6) Model A380–841, –842, and –861 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a report that found corrosion and cracks on the broadband antenna adapter plate during an inspection. The FAA is issuing this AD to address the corrosion and cracks on the broadband antenna adapter plate and skirt assemblyadapter. The unsafe condition, if not addressed, could lead to in-flight detachment of the radome, antenna, and affected parts, which could impact the tail section of the airplane, possibly resulting in damage and reduced control of the airplane. khammond on DSK9W7S144PROD with PROPOSALS (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 2024–0199, dated October 18, 2024 (EASA AD 2024–0199). VerDate Sep<11>2014 17:13 Dec 30, 2024 Jkt 265001 (h) Exceptions to EASA AD 2024–0199 (1) Where Appendix A in ‘‘the applicable SB’’ identified in EASA AD 2024–0199 specifies a compliance time ‘‘from SB publication date,’’ this AD requires using the effective date of this AD. (2) Where EASA AD 2024–0199 specifies ‘‘14 June 2024 [the effective date of EASA AD 2024–0106],’’ this AD requires using the effective date of this AD. (3) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2024–0199. (4) Where paragraph (2) of EASA AD 2024– 0199 specifies ‘‘If, during any GVI as required by paragraph (1) of this AD, any crack and/ or corrosion are detected on an affected part, before next flight, accomplish the applicable corrective action(s) in accordance with the instructions of the applicable SB, or contact Airbus for approved repair instructions and accomplish those instructions accordingly,’’ this AD requires replacing that text with ‘‘If, during any GVI as required by paragraph (1) of this AD, any crack and/or corrosion are detected on an affected part, the crack and/ or corrosion 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.’’ (5) Paragraph (4) of EASA AD 2024–0199 specifies to report inspection results to Airbus within a certain compliance time. For this AD, report inspection results at the applicable time specified in paragraph (h)(5)(i) or (ii) of this AD. (i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (ii) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (i) 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, AIR–520, Continued Operational Safety 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, AIR–520, Continued Operational Safety, 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. PO 00000 Frm 00023 Fmt 4702 Sfmt 9990 (3) Required for Compliance (RC): Except as required by paragraph (i)(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. (j) Additional Information For more information about this AD, contact Dan Rodina, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 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 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 2024–0199, dated October 18, 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. Issued on December 23, 2024. Suzanne Masterson, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2024–31378 Filed 12–30–24; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\31DEP1.SGM 31DEP1

Agencies

[Federal Register Volume 89, Number 250 (Tuesday, December 31, 2024)]
[Proposed Rules]
[Pages 107063-107066]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-31378]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-2718; Project Identifier MCAI-2024-00319-T]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, 
-251N, -252N, -253N, -271N, -272N, and -273N airplanes; Model A321-211, 
-212, -213, -231, -232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -
253NY, -271N, -271NX, -272N, and -272NX airplanes; Airbus SAS Model 
A330-200 series airplanes; Model A330-300 series airplanes; Model A330-
800 series airplanes; Model A330-900 series airplanes; Model A350-941 
and -1041 airplanes; and Model A380-800 series airplanes. This proposed 
AD was prompted by a report of corrosion and cracks on the broadband 
antenna adapter plate during an inspection. This proposed AD would 
require repetitive general visual inspections (GVI) of the broadband 
antenna adapter plate, skirt, vents, and attachment fittings and limit 
the installation of affected parts under certain conditions, 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.

[[Page 107064]]


DATES: The FAA must receive comments on this proposed AD by February 
14, 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-2024-2718; 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 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-2024-2718.
     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: Dan Rodina, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206-
231-3225; 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-2024-2718; 
Project Identifier MCAI-2024-00319-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 Dan 
Rodina, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; telephone 206-231-3225; 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 2024-0199, dated October 18, 2024 
(EASA AD 2024-0199) (also referred to as the MCAI), to correct an 
unsafe condition for Airbus SAS Model A319-111, -112, -113, -114, -115, 
-131, -132, and -133 airplanes; Model A320-211, -212, -214, -215, -216, 
-231, -232, -233, -251N, -252N, -253N, -271N, -272N, and -273N 
airplanes; Model A321-211, -212, -213, -231, -232, -251N, -251NX, -
252N, -252NX, -253N, -253NX, -253NY, -271N, -271NX, -272N, and -272NX 
airplanes; Airbus SAS Model A330-200 series airplanes; Model A330-300 
series airplanes; Model A330-800 series airplanes; Model A330-900 
series airplanes; Model A350-941 and -1041 airplanes; and Model A380-
800 series airplanes. Model A320-215 airplanes are not certificated by 
the FAA and are not included on the U.S. type certificate data sheet; 
this AD therefore does not include those airplanes in the 
applicability. The MCAI states that corrosion and cracks were found on 
the broadband antenna adapter plate during an inspection. Further 
investigation determined that the broadband antenna adapter plate and 
skirt assembly-adapter are made of material susceptible to corrosion 
cracking, and that the recommended maintenance programs do not ensure 
timely detection of cracks and damage in this area.
    The FAA is proposing this AD to address the corrosion and cracks on 
the broadband antenna adapter plate and skirt assembly-adapter. The 
unsafe condition, if not addressed, could lead to in-flight detachment 
of the radome, antenna, and affected parts, which could impact the tail 
section of the airplane, possibly resulting in damage and reduced 
control of the airplane.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2024-2718.

Material Incorporated by Reference Under 1 CFR Part 51

    EASA AD 2024-0199 specifies procedures for repetitive general 
visual inspections (GVI) for cracks and corrosion of the broadband 
antenna adapter plate, skirt, vents, and attachment fittings, and, 
depending on findings, corrective actions including repair or 
replacement of the affected parts. EASA AD 2024-0199 also limits the 
installation of affected parts under certain conditions and requires 
reporting of the inspection results after each inspection.
    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.

[[Page 107065]]

Proposed AD Requirements in This NPRM

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2024-0199 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 2024-0199 by reference in the FAA 
final rule. This proposed AD would, therefore, require compliance with 
EASA AD 2024-0199 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 2024-0199 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-
0199. Material required by EASA AD 2024-0199 for compliance will be 
available at regulations.gov under Docket No. FAA-2024-2718 after the 
FAA final rule is published.

Interim Action

    The FAA considers that this proposed AD would be an interim action. 
The FAA anticipates that further AD action will follow.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 4 airplanes of U.S. registry. The FAA 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
------------------------------------------------------------------------
Up to 61 work-hours x $85 per            $0   Up to $5,185        Up to
 hour = $5,185................                                  $20,740
------------------------------------------------------------------------

    The FAA estimates the following costs to do any on-condition action 
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 this on-condition action:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                              Cost per
                 Labor cost                    Parts cost      product
------------------------------------------------------------------------
50 work-hours x $85 per hour = $4,250.......      $10,000       $14,250
------------------------------------------------------------------------

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

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a currently valid OMB Control Number. The OMB 
Control Number for this information collection is 2120-0056. Public 
reporting for this collection of information is estimated to take 
approximately 1 hour per response, including the time for reviewing 
instructions, searching existing data sources, gathering and 
maintaining the data needed, and completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Send comments regarding this burden estimate 
or any other aspect of this collection of information, including 
suggestions for reducing this burden, to: Information Collection 
Clearance Officer, Federal Aviation Administration, 10101 Hillwood 
Parkway, Fort Worth, TX 76177-1524.

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:

[[Page 107066]]

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-2024-2718; Project Identifier MCAI-
2024-00319-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by February 14, 2025.

 (b) Affected ADs

    None.

 (c) Applicability

    This AD applies to all Airbus SAS Model airplanes specified in 
paragraphs (c)(1) through (6) of this AD, certificated in any 
category.
    (1) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (2) Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -
252N, -253N, -271N, -272N, and -273N airplanes.
    (3) Model A321-211, -212, -213, -231, -232, -251N, -251NX, -
252N, -252NX, -253N, -253NX, -253NY, -271N, -271NX, -272N, and -
272NX airplanes.
    (4) Model A330-201, -202, -203, -223, -243, -301, -302, -303, -
321, -322, -323, -341, -342, -343, -841, and -941 airplanes.
    (5) Model A350-941 and -1041 airplanes.
    (6) Model A380-841, -842, and -861 airplanes.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report that found corrosion and cracks 
on the broadband antenna adapter plate during an inspection. The FAA 
is issuing this AD to address the corrosion and cracks on the 
broadband antenna adapter plate and skirt assembly-adapter. The 
unsafe condition, if not addressed, could lead to in-flight 
detachment of the radome, antenna, and affected parts, which could 
impact the tail section of the airplane, possibly resulting in 
damage and 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 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 
2024-0199, dated October 18, 2024 (EASA AD 2024-0199).

(h) Exceptions to EASA AD 2024-0199

    (1) Where Appendix A in ``the applicable SB'' identified in EASA 
AD 2024-0199 specifies a compliance time ``from SB publication 
date,'' this AD requires using the effective date of this AD.
    (2) Where EASA AD 2024-0199 specifies ``14 June 2024 [the 
effective date of EASA AD 2024-0106],'' this AD requires using the 
effective date of this AD.
    (3) This AD does not adopt the ``Remarks'' section of EASA AD 
2024-0199.
    (4) Where paragraph (2) of EASA AD 2024-0199 specifies ``If, 
during any GVI as required by paragraph (1) of this AD, any crack 
and/or corrosion are detected on an affected part, before next 
flight, accomplish the applicable corrective action(s) in accordance 
with the instructions of the applicable SB, or contact Airbus for 
approved repair instructions and accomplish those instructions 
accordingly,'' this AD requires replacing that text with ``If, 
during any GVI as required by paragraph (1) of this AD, any crack 
and/or corrosion are detected on an affected part, the crack and/or 
corrosion 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.''
    (5) Paragraph (4) of EASA AD 2024-0199 specifies to report 
inspection results to Airbus within a certain compliance time. For 
this AD, report inspection results at the applicable time specified 
in paragraph (h)(5)(i) or (ii) of this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (ii) If the inspection was done before the effective date of 
this AD: Submit the report within 30 days after the effective date 
of this AD.

(i) 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, AIR-
520, Continued Operational Safety Branch, send it to the attention 
of the person identified in paragraph (j) 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, 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 (i)(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.

(j) Additional Information

    For more information about this AD, contact Dan Rodina, Aviation 
Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 206-231-3225; email [email protected].

(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) European Union Aviation Safety Agency (EASA) AD 2024-0199, 
dated October 18, 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 23, 2024.
Suzanne Masterson,
Deputy Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2024-31378 Filed 12-30-24; 8:45 am]
BILLING CODE 4910-13-P
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