90 FR 38 pgs. 10801-10804 - Airworthiness Directives; Airbus SAS Airplanes
Type: PRORULEVolume: 90Number: 38Pages: 10801 - 10804
Pages: 10801, 10802, 10803, 10804Docket number: [Docket No. FAA-2025-0213; Project Identifier MCAI-2024-00385-T]
FR document: [FR Doc. 2025-03159 Filed 2-26-25; 8:45 am]
Agency: Transportation Department
Sub Agency: Federal Aviation Administration
Official PDF Version: PDF Version
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0213; Project Identifier MCAI-2024-00385-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 supersede Airworthiness Directive (AD) 2017-14-14, which applies to all Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2017-14-14 requires repetitive inspections for cracking in the cabin floor beam junction at certain fuselage frame locations, and repair if necessary. Since the FAA issued AD 2017-14-14, further analysis determined that the compliance times for the inspections must also be based on flight hours. This proposed AD would continue to require the actions in AD 2017-14-14, and would require revised compliance times and add a provision for optional modifications, 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 April 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.
• 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-2025-0213; 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 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-2025-0213.
• 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, 2200 South 216th St., Des Moines, WA 98198; 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-2025-0213; Project Identifier MCAI-2024-00385-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
[top] 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, 2200 South 216th St., Des Moines, WA 98198; 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
The FAA issued AD 2017-14-14, Amendment 39-18958 (82 FR 33002, July 19, 2017) (AD 2017-14-14), for all Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2017-14-14 was prompted by an MCAI originated by EASA, which is the Technical Agent for the Member States of the European Union. EASA issued AD 2016-0105, dated June 6, 2016, to correct an unsafe condition.
AD 2017-14-14 requires repetitive inspections for cracking in the cabin floor beam junction at certain fuselage frame locations, and repair if necessary. The FAA issued AD 2017-14-14 to detect and correct cracking in the cabin floor beam junction at certain fuselage frame locations, which could result in reduced structural integrity of the airplane.
Actions Since AD 2017-14-14 Was Issued
Since the FAA issued AD 2017-14-14, EASA revised EASA AD 2016-0105, dated June 6, 2016, and issued EASA ADs 2016-0105R1, dated September 21, 2018 (EASA AD 2016-0105R1), and 2016-0105R2, dated October 8, 2021 (EASA AD 2016-0105R2), for all Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. EASA AD 2016-0105R1 stated that the manufacturer developed a modification that restores the fatigue potential at each location (junction) by doing cold-working at the cabin floor beam and fitting junction for airplanes with a pre-mod 155607 configuration. EASA AD 2016-0105R1 was revised by EASA AD 2016-0105R2, which stated that the manufacturer developed optional modification instructions for airplanes with a post-mod 155607 configuration. These modifications can be used to extend the compliance time for an inspection cycle. EASA then superseded EASA AD 2016-0105R2 with EASA AD 2024-0128, dated July 3, 2024 (EASA AD 2024-0128) (also referred to as the MCAI), to correct the unsafe condition for the same airplanes. EASA AD 2024-0128 states that further analysis determined that the compliance times for the inspections must also be based on flight hours.
The FAA is proposing this AD to address cracking in the cabin floor beam junction at certain fuselage frame locations, which could result in reduced structural integrity of the airplane. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA-2025-0213.
Explanation of Retained Requirements
Although this proposed AD does not explicitly restate the requirements of AD 2017-14-14, this proposed AD would retain all of the requirements of AD 2017-14-14. Those requirements are referenced in EASA AD 2024-0128, which, in turn, is referenced in paragraph (g) of this proposed AD.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2024-0128 specifies procedures for inspections for cracking on the frame to cabin floor beam junction at certain fuselage frame locations (frames 35.1 and 35.2, left- and right-hand sides), and repairs, and optional modifications to extend an inspection interval. 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 2024-0128 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 2024-0128 by reference in the FAA final rule. This proposed AD would, therefore, require compliance with EASA AD 2024-0128 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 2024-0128 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 2024-0128. Material required by EASA AD 2024-0128 for compliance will be available at regulations.gov under Docket No. FAA-2025-0213 after the FAA final rule is published.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would affect 494 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD:
| Action | Labor cost | Parts cost | Cost per product | Cost on U.S. operators |
|---|---|---|---|---|
| Retained actions from AD 2017-14-14 | Up to 8 work-hours × $85 per hour = $680 | None | Up to $680 | Up to $335,920. |
| Labor cost | Parts cost | Cost per product |
|---|---|---|
| Up to 135 work-hours × $85 per hour = $11,475 | Up to $7,510 | Up to $18,985. |
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The FAA estimates the following costs to do any necessary on-condition actions that would be required based on the results of any required actions. The FAA has no way of determining the number of aircraft that might need these on-condition actions:
| Labor cost | Parts cost | Cost per product |
|---|---|---|
| Up to 50 work-hours × $85 per hour = $4,250 | $1,600 | $5,850 |
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
1. The authority citation for part 39 continues to read as follows:
Authority:
49 U.S.C. 106(f), 40113, 44701.
§?39.13 [Amended]
2. The FAA amends §?39.13 by:
a. Removing Airworthiness Directive (AD) 2017-14-14, Amendment 39-18958 (82 FR 33002, July 19, 2017); and
b. Adding the following new AD:
Airbus SAS: Docket No. FAA-2025-0213; Project Identifier MCAI-2024-00385-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive (AD) by April 14, 2025.
(b) Affected ADs
This AD replaces AD 2017-14-14, Amendment 39-18958 (82 FR 33002, July 19, 2017) (AD 2017-14-14).
(c) Applicability
This AD applies to all Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a determination from fatigue testing on the Model A321 airframe that cracks could develop in the cabin floor beam junction at certain fuselage frame locations. The FAA is issuing this AD to address cracking in the cabin floor beam junction at certain fuselage frame locations. The unsafe condition, if not addressed, could result in reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Requirements
Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2024-0128, dated July 3, 2024 (EASA AD 2024-0128).
(h) Exceptions to EASA AD 2024-0128
(1) Where EASA AD 2024-0128 refers to "13 June 2016 [the effective date of EASA AD 2016-0105]," this AD requires using August 23, 2017 (the effective date of AD 2017-14-14).
(2) Where EASA AD 2024-0128 refers to its effective date, this AD requires using the effective date of this AD.
(3) This AD does not adopt the "Remarks" section of EASA AD 2024-0128.
(4) Where paragraph (2) of EASA AD 2024-0128 specifies an option to "contact Airbus for approved repair instructions and, within the compliance time specified therein, accomplish those instructions accordingly," this AD requires replacing that text with "the crack 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."
(i) No Reporting Requirement
Although the material referenced in EASA AD 2024-0128 specifies to submit certain information (inspection report sheet) 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 the 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 .
(i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.
(ii) AMOCs approved previously for AD 2017-14-14 are approved as AMOCs for the corresponding provisions of EASA AD 2024-0128 that are required by paragraph (g) of this AD.
[top] (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
(3) Required for Compliance (RC): Except as required by paragraphs (i) and (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, 2200 South 216th St., Des Moines, WA 98198; telephone 206-231-3667; email timothy.p.dowling@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 2024-0128, dated July 3, 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 February 21, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service.
[FR Doc. 2025-03159 Filed 2-26-25; 8:45 am]
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