[Federal Register Volume 89, Number 131 (Tuesday, July 9, 2024)]
[Rules and Regulations]
[Pages 56195-56198]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-14868]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-0757; Project Identifier MCAI-2023-01205-T; 
Amendment 39-22765; AD 2024-12-01]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2022-14-
10, which applied to 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. 
AD 2022-14-10 required repetitive inspections for cracking of the 
radius of the front spar vertical stringers and the horizontal floor 
beam on a certain frame (FR), repetitive inspections for cracking of 
the fastener holes of the front spar vertical stringers on that frame, 
and repair if necessary. AD 2022-14-10 also provided, for certain 
airplanes, a modification of the center wing box area that terminates 
the repetitive inspections under certain conditions. Since the FAA 
issued AD 2022-14-10, an additional airplane model has been identified 
that is also subject to the unsafe condition. This AD continues to 
require the actions in AD 2022-14-10 and adds Model A321-271N airplanes 
to the applicability, as specified in a European Union Aviation Safety 
Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective August 13, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 13, 
2024.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2024-0757; or in person at Docket Operations between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this final rule, the mandatory continuing airworthiness 
information (MCAI), any comments received, and other information. The 
address for Docket Operations is U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.
    Material Incorporated by Reference:
     For EASA material, 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.
     You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 2200 South 216th St., Des 
Moines, WA. For information on the availability of this material at the 
FAA, call 206-231-3195. It is also available at regulations.gov under 
Docket No. FAA-2024-0757.

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: 

[[Page 56196]]

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2022-14-10, Amendment 39-22115 (87 FR 
42315, July 15, 2022), (AD 2022-14-10). AD 2022-14-10 applied to 
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. AD 2022-14-10 required 
repetitive inspections for cracking of the radius of the front spar 
vertical stringers and the horizontal floor beam on FR 36, repetitive 
inspections for cracking of the fastener holes of the front spar 
vertical stringers on FR 36, and repair if necessary, and, for certain 
airplanes, a potential terminating action modification of the center 
wing box area. The FAA issued AD 2022-14-10 to address fatigue cracking 
of the front spar vertical stringers on the wings, which, if not 
corrected, could result in reduced structural integrity of the 
airplane.
    The NPRM published in the Federal Register on March 22, 2024 (89 FR 
20364). The NPRM was prompted by AD 2023-0205, dated November 21, 2023 
(EASA AD 2023-0205) (also referred to as the MCAI), issued by EASA, 
which is the Technical Agent for the Member States of the European 
Union. The MCAI states that analysis of the full-scale certification 
fatigue testing findings indicated that Model A321-271N airplanes are 
also subject to the unsafe condition. Fatigue cracking of the front 
spar vertical stringers on the wings, if not detected and corrected, 
could lead to crack propagation, possibly resulting in reduced 
structural integrity of the airplane.
    In the NPRM, the FAA proposed to continue to require the actions in 
AD 2022-14-10 and add Model A321-271N airplanes to the applicability, 
as specified in EASA AD 2023-0205. The FAA is issuing this AD to 
address the unsafe condition on these products.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2024-0757.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from United Airlines who supported the 
NPRM without change.

Additional Changes Made to This AD

    The FAA added paragraphs (h)(5) and (6) of this AD to clarify who 
can provide approval instructions for certain actions. These paragraphs 
correspond to actions retained from AD 2022-14-10 and were 
inadvertently omitted from the proposed AD.

Conclusion

    This product has been approved by the aviation authority of another 
country and is approved for operation in the United States. Pursuant to 
the FAA's bilateral agreement with this State of Design Authority, it 
has notified the FAA of the unsafe condition described in the MCAI 
referenced above. The FAA reviewed the relevant data, considered the 
comment received, and determined that air safety requires adopting this 
AD as proposed. Accordingly, the FAA is issuing this AD to address the 
unsafe condition on this product. Except for minor editorial changes, 
and any other changes described previously, this AD is adopted as 
proposed in the NPRM. None of the changes will increase the economic 
burden on any operator.

Related Service Information Under 1 CFR Part 51

    EASA AD 2023-0205 specifies procedures for repetitive special 
detailed inspections for cracking of the radius of the front spar 
vertical stringers, horizontal floor beam radius and fastener holes of 
the front spear vertical stringers on FR 36, and for installing new 
fasteners. EASA AD 2023-0205 further describes procedures for 
repetitive high frequency eddy current (HFEC) inspections for cracking 
of the horizontal floor beam, repetitive HFEC inspections for cracking 
of the fastener holes of the front spar vertical stringers on FR 36, 
repetitive rototest inspections of the fastener holes of the spar 
vertical stringers, and repair. EASA AD 2023-0205 also describes 
procedures for the modification of the center wing box area. The 
modification is required for airplanes in configuration 1, 2 or 3; and 
for airplanes in configuration 5, 6, or 7, the modification is optional 
and is a terminating action for the repetitive inspections when done 
within a specified time frame. The modification includes related 
investigative and corrective actions. Related investigative actions 
include an HFEC inspection on the radius of the rib flanges, a rototest 
inspection of the fastener holes, detailed and HFEC inspections for 
cracking on the cut edges, detailed and rototest inspections on all 
open fastener holes, and an inspection to determine if secondary 
structure brackets are installed. Corrective actions include rework of 
the secondary structure bracket and repair.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    The FAA estimates that this AD affects 1,755 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
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                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
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Inspection, per inspection cycle  25 work-hours x     Up to $100........  Up to $2,225......  Up to $3,904,875.
                                   $85 per hour =
                                   $2,125.
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                  Estimated Costs for Optional Actions
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           Labor cost                 Parts cost       Cost per product
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Up to 409 work-hours x $85 per    Up to $66,050.....  Up to $100,815.
 hour = Up to $34,765.
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    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition actions specified in this 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

[[Page 56197]]

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 AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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:
0
a. Removing Airworthiness Directive (AD) 2022-14-10, Amendment 39-22115 
(87 FR 42315, July 15, 2022); and
0
b. Adding the following new AD:

2024-12-01 Airbus SAS: Amendment 39-22765; Docket No. FAA-2024-0757; 
Project Identifier MCAI-2023-01205-T.

(a) Effective Date

    This airworthiness directive (AD) is effective August 13, 2024.

(b) Affected ADs

    This AD replaces AD 2022-14-10, Amendment 39-22115 (87 FR 42315, 
July 15, 2022) (AD 2022-14-10).

(c) Applicability

    This AD applies to the Airbus SAS airplanes identified in 
paragraphs (c)(1) through (4) of this AD, certificated in any 
category, as identified in European Union Aviation Safety Agency 
(EASA) AD 2023-0205, dated November 21, 2023 (EASA AD 2023-0205).
    (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, -232, 
and -271N airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a report that, during a center fuselage 
certification full-scale fatigue test, cracks were found on the 
front spar vertical stringer at a certain frame. This AD was also 
prompted by a determination that Model A321 airplanes that have 
incorporated modification 160021 are also subject to the unsafe 
condition. The FAA is issuing this AD to address fatigue cracking of 
the front spar vertical stringers on the wings. 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 paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2023-0205.

(h) Exceptions to EASA AD 2023-0205

    (1) Where EASA AD 2023-0205 refers to ``22 November 2021 [the 
effective date of EASA AD 2021-0241],'' this AD requires using 
August 19, 2022 (the effective date of AD 2022-14-10).
    (2) Where EASA AD 2023-0205 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 
2023-0205.
    (4) Where paragraph (5) of EASA AD 2023-0205 specifies ``if any 
crack is found, before next flight, contact Airbus for approved 
corrective action instructions and accomplish those instructions 
accordingly,'' this AD requires replacing that text with ``if any 
crack is found, the crack must be repaired before further flight 
using a method approved by the Manager, International Validation 
Branch, FAA; or EASA; or Airbus SAS's EASA Design Organization 
Approval (DOA). If approved by the DOA, the approval must include 
the DOA-authorized signature.''
    (5) Where paragraph (4) of EASA AD 2023-0205 specifies actions 
for airplanes repaired ``in accordance with instructions approved by 
EASA or approved under the authority of Airbus Design Organization 
Approval (DOA) privileges,'' this AD requires replacing that text 
with ``using a method approved by the Manager, International 
Validation Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.''
    (6) Where paragraph (9) of EASA AD 2023-0205 specifies approval 
``by Airbus DOA,'' this AD requires replacing that text with ``by 
the Manager, International Validation Branch, FAA; or EASA; or 
Airbus SAS's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.''

(i) No Reporting Requirement

    Although the service information referenced in EASA AD 2023-0205 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

(j) Additional AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Validation Branch, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or responsible Flight Standards Office, as 
appropriate. If sending information directly to the manager of the 
International Validation Branch, mail it to the address identified 
in paragraph (k) of this AD. Information may be emailed 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, International 
Validation Branch, FAA; or EASA; or Airbus SAS's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (j)(2) of this AD, if any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

[[Page 56198]]

(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 (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) European Union Aviation Safety Agency (EASA) AD 2023-0205, 
dated November 21, 2023.
    (ii) [Reserved]
    (3) For EASA AD 2023-0205, 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 EASA 
AD on the EASA website at ad.easa.europa.eu.
    (4) You may view this service information 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 [email protected].

    Issued on June 5, 2024.
Suzanne Masterson,
Deputy Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2024-14868 Filed 7-8-24; 8:45 am]
BILLING CODE 4910-13-P