Rule2024-14868
Airworthiness Directives; Airbus SAS Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
July 9, 2024
Effective
August 13, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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.
Full Text
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<title>Federal Register, Volume 89 Issue 131 (Tuesday, July 9, 2024)</title>
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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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 <a href="http://regulations.gov">regulations.gov</a> 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:
<bullet> For EASA material, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#dd9c99ae9db8bcaebcf3b8a8afb2adbcf3b8a8"><span class="__cf_email__" data-cfemail="1d5c596e5d787c6e7c3378686f726d7c337868">[email protected]</span></a>; website easa.europa.eu. You may find this material
on the EASA website at ad.easa.europa.eu.
<bullet> 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 <a href="http://regulations.gov">regulations.gov</a> 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 <a href="/cdn-cgi/l/email-protection#9beff2f6f4eff3e2b5ebb5fff4ecf7f2f5fcdbfdfafab5fcf4ed"><span class="__cf_email__" data-cfemail="45312c282a312d3c6b356b212a32292c2b22052324246b222a33">[email protected]</span></a>.
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 <a href="http://regulations.gov">regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#f4cdd9b5a2a7d9b5bda6d9c3c7c4d9b5b9bbb7b4929595da939b82"><span class="__cf_email__" data-cfemail="4a73670b1c19670b0318677d797a670b0705090a2c2b2b642d253c">[email protected]</span></a>. 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
<a href="/cdn-cgi/l/email-protection#b1c5d8dcdec5d9c89fc19fd5dec6ddd8dfd6f1d7d0d09fd6dec7"><span class="__cf_email__" data-cfemail="9ce8f5f1f3e8f4e5b2ecb2f8f3ebf0f5f2fbdcfafdfdb2fbf3ea">[email protected]</span></a>.
(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
<a href="/cdn-cgi/l/email-protection#fabbbe89ba9f9b899bd49f8f88958a9bd49f8f"><span class="__cf_email__" data-cfemail="d59491a695b0b4a6b4fbb0a0a7baa5b4fbb0a0">[email protected]</span></a>; 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 <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a>, or email <a href="/cdn-cgi/l/email-protection#5a3c28743334292a3f392e3335341a343b283b743d352c"><span class="__cf_email__" data-cfemail="1d7b6f3374736e6d787e697472735d737c6f7c337a726b">[email protected]</span></a>.
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
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