Proposed Rule2024-28758
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
December 9, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt a new airworthiness directive (AD) for 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. This proposed AD was prompted by cracks being found during full-scale fatigue testing of the keel beam bottom panel between the edge profile and stringer run- out at a certain frame and stringer. This proposed AD would require repetitive special detailed inspections (SDI) of the affected area, and corrective actions if necessary, 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.
Full Text
<html>
<head>
<title>Federal Register, Volume 89 Issue 236 (Monday, December 9, 2024)</title>
</head>
<body><pre>
[Federal Register Volume 89, Number 236 (Monday, December 9, 2024)]
[Proposed Rules]
[Pages 97564-97567]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-28758]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-2548; Project Identifier MCAI-2024-00401-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 adopt a new airworthiness directive (AD)
for 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. This proposed AD
was prompted by cracks being found during full-scale fatigue testing of
the keel beam bottom panel between the edge profile and stringer run-
out at a certain frame and stringer. This proposed AD would require
repetitive special detailed inspections (SDI) of the affected area, and
corrective actions if necessary, 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 January 23,
2025.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> 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.
<bullet> 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 <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2024-2548; 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
[[Page 97565]]
continuing airworthiness information (MCAI), any comments received, and
other information. The street address for Docket Operations is listed
above.
Material Incorporated by Reference:
<bullet> For EASA material identified in this proposed AD, contact
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221
8999 000; email <a href="/cdn-cgi/l/email-protection#a1e0e5d2e1c4c0d2c08fc4d4d3ced1c08fc4d4"><span class="__cf_email__" data-cfemail="17565364577276647639726265786776397262">[email protected]</span></a>; website easa.europa.eu. You may
find this material on the EASA website at ad.easa.europa.eu. It is also
available at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2024-2548.
<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.
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#fca8959193889485d2acd2b8938b9095929bbc9a9d9dd29b938a"><span class="__cf_email__" data-cfemail="5e0a3733312a3627700e701a3129323730391e383f3f70393128">[email protected]</span></a>.
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-2024-2548;
Project Identifier MCAI-2024-00401-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
<a href="http://regulations.gov">regulations.gov</a>, 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
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#7e2a1713110a1607502e503a1109121710193e181f1f50191108"><span class="__cf_email__" data-cfemail="297d4044465d41500779076d465e4540474e694f4848074e465f">[email protected]</span></a>. 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 2024-0135, dated July 10, 2024 (EASA
AD 2024-0135) (also referred to as the MCAI), to correct an unsafe
condition for certain Airbus SAS Model A318 series airplanes; Model
A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes, Model
A320-211, -212, -214, -215, -216, -231, -232, and -233 airplanes; and
Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
Model A320-215 airplanes are not certificated by the FAA and are not
included on the U.S. type certificate data sheet; this proposed AD
therefore does not include those airplanes in the applicability. The
MCAI states that during full-scale fatigue testing, cracks were found
on the keel beam bottom panel between the edge profile and stringer
run-out at frame 46 and stringer 37, left- and right-hand sides. Crack
propagation in this area could possibly result in reduced structural
integrity of the airplane.
The FAA is proposing 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-2024-2548.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2024-0135 specifies procedures for repetitive SDIs for
discrepancies (cracks) of the keel beam bottom panel between the edge
profile and stringer run-out at frame 46 and stringer 37, left-hand and
right-hand sides. EASA AD 2024-0135 also specifies corrective actions
including crack repair.
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 2024-0135 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 2024-0135 by reference in the FAA
final rule. This proposed AD would, therefore, require compliance with
EASA AD 2024-0135 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 2024-0135 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-
0135. Material required by EASA AD 2024-0135 for compliance will be
available at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2024-2548 after the
FAA final rule is published.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 1,920 airplanes of U.S. registry. The FAA
[[Page 97566]]
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
----------------------------------------------------------------------------------------------------------------
16 work-hours x $85 per hour = $1,360........................ $0 $1,360 $2,611,200
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs specified in this proposed 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 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
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-2024-2548; Project Identifier MCAI-2024-
00401-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by January 23, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus SAS airplanes, certificated in any
category, as identified in paragraphs (c)(1) through (4) of this AD
and in European Union Aviation Safety Agency (EASA) AD 2024-0135,
dated July 10, 2024 (EASA AD 2024-0135).
(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, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by cracks being found during full-scale
fatigue testing of the keel beam bottom panel between the edge
profile and stringer run-out at frame 46 and stringer 37, left- and
right-hand sides. The FAA is issuing this AD to address the unsafe
condition on these products. The unsafe condition, if not addressed,
could result in crack propagation, possibly resulting 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, EASA AD 2024-0135.
(h) Exceptions to EASA AD 2024-0135
(1) Where EASA AD 2024-0135 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where paragraph (2) of EASA AD 2024-0135 specifies ``if,
during any inspection as required by paragraph (1) of this AD,
discrepancies are detected, as defined in the SB, before next
flight, contact Airbus for approved repair instructions and
accomplish those instructions accordingly,'' this AD requires
replacing that text with ``if, during any inspection as required by
paragraph (1) of this AD, any cracking is detected, the cracking
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.''
(3) Where paragraph (3) of EASA AD 2024-0135 does not allow
corrective action as terminating action for the repetitive
inspection requirements ``unless otherwise stated in the repair
instructions provided by Airbus,'' this AD requires that any
terminating action be approved in accordance with the procedures
specified in paragraph (j)(1) of this AD.
(4) This AD does not adopt the ``Remarks'' section of EASA AD
2024-0135.
(i) No Reporting Requirement
Although the material referenced in EASA AD 2024-0135 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, 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
AIR-520, Continued Operational Safety Branch, send it to the
[[Page 97567]]
attention of the person identified in paragraph (k) of this AD and
email to: <a href="/cdn-cgi/l/email-protection#21606c6e62614740400f464e57"><span class="__cf_email__" data-cfemail="7d3c30323e3d1b1c1c531a120b">[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, 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.
(3) Required for Compliance (RC): Except as required by
paragraph (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, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 206-231-3667; email
<a href="/cdn-cgi/l/email-protection#92c6fbfffde6faebbcc2bcd6fde5fefbfcf5d2f4f3f3bcf5fde4"><span class="__cf_email__" data-cfemail="22764b4f4d564a5b0c720c664d554e4b4c45624443430c454d54">[email protected]</span></a>.
(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 2024-0135,
dated July 10, 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 <a href="/cdn-cgi/l/email-protection#36777245765357455718534344594657185343"><span class="__cf_email__" data-cfemail="4d0c093e0d282c3e2c6328383f223d2c632838">[email protected]</span></a>; 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 <a href="/cdn-cgi/l/email-protection#79451859110b1c1f44" http: www.archives.gov federal-register cfr ibr-locationsoremailfr.inspection@nara.gov">www.archives.gov/federal-register/cfr/<span class="__cf_email__" data-cfemail="345d564619585b5755405d5b5a475b465159555d5852461a5d5a47445157405d5b5a745a5546551a535b42">[email protected]</span></a>"><a href="http://www.archives.gov/federal-register/cfr/ibr-locationsoremailfr.inspection@nara.gov">www.archives.gov/federal-register/cfr/<span class="__cf_email__" data-cfemail="bdd4dfcf90d1d2dedcc9d4d2d3ced2cfd8d0dcd4d1dbcf93d4d3cecdd8dec9d4d2d3fdd3dccfdc93dad2cb">[email protected]</span></a></a>.
Issued on December 3, 2024.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2024-28758 Filed 12-6-24; 8:45 am]
BILLING CODE 4910-13-P
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on December 9, 2024.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.