Rule2024-06996
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
April 3, 2024
Effective
May 8, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-214, A320-216, A320-251N, A320-271N, and A321-253NX airplanes. This AD was prompted by a quality review of the forward cargo door frame-to-fuselage skin panel assembly identified several fastener holes that deviated from the manufacturing requirements. This AD requires a geometrical check of the diameter of certain fastener holes for deviations, and if any deviation is found, repetitive special detailed inspections of the affected area for discrepancies and, depending on findings, accomplishment of applicable corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. 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 65 (Wednesday, April 3, 2024)</title>
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[Federal Register Volume 89, Number 65 (Wednesday, April 3, 2024)]
[Rules and Regulations]
[Pages 22932-22934]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-06996]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-1897; Project Identifier MCAI-2023-00921-T;
Amendment 39-22692; AD 2024-05-02]
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 adopting a new airworthiness directive (AD) for
certain Airbus SAS Model A320-214, A320-216, A320-251N, A320-271N, and
A321-253NX airplanes. This AD was prompted by a quality review of the
forward cargo door frame-to-fuselage skin panel assembly identified
several fastener holes that deviated from the manufacturing
requirements. This AD requires a geometrical check of the diameter of
certain fastener holes for deviations, and if any deviation is found,
repetitive special detailed inspections of the affected area for
discrepancies and, depending on findings, accomplishment of applicable
corrective actions, as specified in a European Union Aviation Safety
Agency (EASA) AD, which is incorporated by reference. The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective May 8, 2024.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 8, 2024.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2023-1897; 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 material identified in this AD, contact EASA, Konrad-
Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000;
email <a href="/cdn-cgi/l/email-protection#a7e6e3d4e7c2c6d4c689c2d2d5c8d7c689c2d2"><span class="__cf_email__" data-cfemail="49080d3a092c283a28672c3c3b263928672c3c">[email protected]</span></a>; website easa.europa.eu. You may find this
material on the EASA website ad.easa.europa.eu.
<bullet> You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th Street,
Des Moines, WA. For information on the availability of this material at
the FAA, call 206-231-3195. It is also available in the AD docket at
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2023-1897.
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#dbafb2b6b4afb3a2f5abf5bfb4acb7b2b5bc9bbdbabaf5bcb4ad"><span class="__cf_email__" data-cfemail="3b4f5256544f5342154b155f544c5752555c7b5d5a5a155c544d">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain Airbus SAS
Model A320-214, A320-216, A320-251N, A320-271N, and A321-253NX
airplanes. The NPRM published in the Federal Register on October 5,
2023 (88 FR 69110). The NPRM was prompted by AD 2023-0153, dated July
26, 2023 (EASA AD 2023-0153) (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 a quality review of the forward cargo
door frame-to-fuselage skin panel assembly identified several drillings
as deviating from manufacturing requirements, creating oversized
fastener holes, which could lead to cracking. This condition, if not
addressed, could lead to reduced structural integrity of the fuselage.
In the NPRM, the FAA proposed to require repetitive special
detailed inspections of the affected area for discrepancies and,
depending on findings, accomplishment of applicable corrective actions,
as specified in EASA AD 2023-0153. 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-2023-1897.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from two commenters. Air Line Pilots
Association, International (ALPA) and an individual who both supported
the NPRM without change.
Additional Changes Made to This AD
Since the NPRM was published, EASA AD 2023-0153 was superseded by
EASA AD 2023-0179, dated October 11, 2023 (EASA AD 2023-0179). Since
EASA AD 2023-0153 was issued, it has been determined that, depending on
inspection findings, no repetitive inspection may be required. EASA AD
2023-0179 also clarified that the initial inspection is a geometrical
check of the diameter of certain fastener holes for deviations. The FAA
has updated this final rule accordingly by replacing EASA AD 2023-0153
with EASA AD 2023-0179 in all affected paragraphs and added a ``Credit
for Previous Actions'' paragraph to retain the requirements of EASA AD
2023-0153, however the concession identified in EASA AD 2023-0153 was
removed in EASA AD 2023-0179.
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
comments 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.
[[Page 22933]]
Related Service Information Under 1 CFR Part 51
EASA AD 2023-0179 specifies procedures for a geometrical check of
the diameter of certain fastener holes for deviations, and if any
deviation is found, repetitive special detailed inspections of the
affected area for discrepancies and, depending on findings,
accomplishment of applicable corrective action. The special detailed
inspection consists of a rototest inspection for cracking of the
forward cargo door frame to fuselage skin panel, and if no cracking is
found, checking the fastener hole diameters. Corrective actions include
installing oversized fasteners if the fastener hole diameter is less
than or equal to the specified nominal diameter, contacting the
manufacturer for repair instructions if the fastener hole diameter is
greater than the specified nominal diameter, and repairing any cracking
by contacting the manufacturer for repair instructions. 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 section.
Costs of Compliance
The FAA estimates that this AD affects 8 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 per Cost on U.S.
Labor cost Parts cost product operators
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42.5 work-hours x $85 per hour = $3,613...................... $100 $3,713 $29,704
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The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs specified in this AD.
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some or all of the costs of
this AD may be covered under warranty, thereby reducing the cost impact
on affected operators.
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
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 adding the following new airworthiness
directive:
2024-05-02 Airbus SAS: Amendment 39-22692; Docket No. FAA-2023-1897;
Project Identifier MCAI-2023-00921-T.
(a) Effective Date
This airworthiness directive (AD) is effective May 8, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model A320-214, A320-216, A320-
251N, A320-271N, and A321-253NX airplanes, certificated in any
category, as identified in European Union Aviation Safety Agency
(EASA) AD 2023-0179, dated October 11, 2023 (EASA AD 2023-0179).
(d) Subject
Air Transport Association (ATA) of America Code: 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a quality review of the forward cargo
door frame-to-fuselage skin panel assembly identified several
drillings as deviating from manufacturing requirements, creating
oversized fastener holes. The FAA is issuing this AD to address
oversized fastener holes and cracking. The unsafe condition, if not
detected and corrected, could result in reduced structural integrity
of the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraphs (h) and (i) of this AD: Comply
with all required actions and compliance times specified in, and in
accordance with, EASA AD 2023-0179.
(h) Exceptions to EASA AD 2023-0179
(1) Where EASA AD 2023-0179 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where paragraph (4) of EASA AD 2023-0179 specifies ``If,
during any SDI as required by paragraph (3) of this AD, any crack is
detected, before next flight, contact Airbus for approved repair
instructions and, within the compliance time identified therein,
accomplish those instructions accordingly,'' this AD requires
replacing those words with ``If, during any SDI as required by
paragraph (3) of this AD, any cracking is found, before next flight,
repair the cracking 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) Where paragraph (8) of EASA AD 2023-0179 specifies the
repair be done in
[[Page 22934]]
accordance with ``approved Airbus repair instructions,'' for this AD
the repair must have been done 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.
(4) Where paragraph (6) of EASA AD 2023-0179 specifies to
``oversize that fastener hole and install a new oversize fastener
and new rivet,'' this AD requires replacing those words with
``before next flight, oversize that fastener hole and install a new
oversize fastener and new rivet.''
(5) This AD does not adopt the ``Remarks'' section of EASA AD
2023-0179.
(i) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using EASA AD 2023-0153, dated July 26,
2023.
(j) No Reporting Requirement
Although the service information referenced in EASA AD 2023-0179
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
(k) 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 in paragraph
(l) of this AD or email to: <a href="/cdn-cgi/l/email-protection#edd4c0acbbbec0aca4bfc0dadeddc0aca0a2aead8b8c8cc38a829b"><span class="__cf_email__" data-cfemail="e8d1c5a9bebbc5a9a1bac5dfdbd8c5a9a5a7aba88e8989c68f879e">[email protected]</span></a>. If mailing
information, also submit information by email. 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 DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(3) Required for Compliance (RC): Except as required by
paragraphs (j) and (k)(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.
(l) 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#87f3eeeae8f3effea9f7a9e3e8f0ebeee9e0c7e1e6e6a9e0e8f1"><span class="__cf_email__" data-cfemail="ef9b8682809b8796c19fc18b809883868188af898e8ec1888099">[email protected]</span></a>.
(m) 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 2023-0179,
dated October 11, 2023.
(ii) [Reserved]
(3) For EASA AD 2023-0179, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#0c4d487f4c696d7f6d2269797e637c6d226979"><span class="__cf_email__" data-cfemail="1554516655707466743b7060677a65743b7060">[email protected]</span></a>; website easa.europa.eu. You may find this EASA
AD on the EASA website ad.easa.europa.eu.
(4) You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th
Street, 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#4523376b2c2b36352026312c2a2b052b2437246b222a33"><span class="__cf_email__" data-cfemail="593f2b7730372a293c3a2d3036371937382b38773e362f">[email protected]</span></a>.
Issued on February 29, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-06996 Filed 4-2-24; 8:45 am]
BILLING CODE 4910-13-P
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