Proposed Rule2024-05914
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
March 22, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to supersede Airworthiness Directive (AD) 2022-14-10, which applies 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 requires 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 provides, 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 proposed AD would continue to require the actions in AD 2022-14-10 and would add Model A321-271N airplanes to the applicability, 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
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<title>Federal Register, Volume 89 Issue 57 (Friday, March 22, 2024)</title>
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[Federal Register Volume 89, Number 57 (Friday, March 22, 2024)]
[Proposed Rules]
[Pages 20364-20367]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-05914]
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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]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2022-14-10, which applies 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 requires 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 provides, 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 proposed
AD would continue to require the actions in AD 2022-14-10 and would add
Model A321-271N airplanes to the applicability, 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 May 6,
2024.
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-2024-0757; 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 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:
<bullet> For the EASA AD identified in this NPRM, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999
000; email <a href="/cdn-cgi/l/email-protection#c08184b380a5a1b3a1eea5b5b2afb0a1eea5b5"><span class="__cf_email__" data-cfemail="4001043300252133216e2535322f30216e2535">[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-2024-0757.
<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 817-222-5102; email <a href="/cdn-cgi/l/email-protection#bdc9d4d0d2c9d5c493cd93d9d2cad1d4d3dafddbdcdc93dad2cb"><span class="__cf_email__" data-cfemail="7c08151113081405520c5218130b1015121b3c1a1d1d521b130a">[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 ADDRESSES. Include ``Docket No. FAA-2024-0757; Project Identifier
MCAI-2023-01205-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 817-222-5102; email
<a href="/cdn-cgi/l/email-protection#d6a2bfbbb9a2beaff8a6f8b2b9a1babfb8b196b0b7b7f8b1b9a0"><span class="__cf_email__" data-cfemail="ed99848082998594c39dc389829a8184838aad8b8c8cc38a829b">[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
The FAA issued AD 2022-14-10, Amendment 39-22115 (87 FR 42315, July
15, 2022) (AD 2022-14-10), 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. AD 2022-14-10 was prompted by an MCAI originated by
EASA, which is the Technical Agent for the Member States of the
European Union. EASA issued AD 2021-0241, dated November 8, 2021 (EASA
AD 2021-0241), to correct an unsafe condition. EASA AD 2021-0241 stated
that during full-scale certification fatigue testing of the center
fuselage, cracks were found on a wing front spar vertical stringer at
FR36.
AD 2022-14-10 requires repetitive inspections for cracking of the
radius of the front spar vertical stringers and the horizontal floor
beam on frame (FR) 36, repetitive inspections for cracking of the
fastener holes of the front spar vertical stringers on FR 36, and
repair if
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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 the reduced structural
integrity of the airplane.
Actions Since AD 2022-14-10 Was Issued
Since the FAA issued AD 2022-14-10, EASA superseded EASA AD 2021-
0241, dated November 8, 2021, and issued EASA AD 2023-0205, dated
November 21, 2023 (EASA AD 2023-0205) (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, -
232, and -271N airplanes. Model A320-215 airplanes are not certificated
by the FAA and are not included on the U.S. type certificate data
sheet; this AD, therefore, does not include those airplanes in the
applicability. 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.
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-2024-0757.
Explanation of Retained Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2022-14-10, this proposed AD would retain all of the
requirements of AD 2022-14-10. Those requirements are referenced in
EASA AD 2023-0205, which, in turn, is referenced in paragraph (g) of
this proposed AD.
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 frame 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 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 retain all requirements of AD 2022-14-10.
This proposed AD would add airplanes to the applicability and require
accomplishing the actions specified in EASA AD 2023-0205 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 2023-0205 by reference in the FAA
final rule. This proposed AD would, therefore, require compliance with
EASA AD 2023-0205 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 2023-0205 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 2023-
0205. Service information required by EASA AD 2023-0205 for compliance
will be available at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2024-0757
after the FAA final rule is published.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 1,755 airplanes of U.S. registry. The FAA estimates the
following costs to comply with this proposed AD:
Estimated Costs for Required Actions
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Action Labor cost Parts cost Cost per product Cost on U.S. operators
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Inspection, per inspection cycle.. 25 work-hours x $85 Up to $100................ Up to $2,225.................... Up to $3,904,875.
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 hour = Up to $66,050...................... Up to $100,815.
$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 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:
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:
Airbus SAS: Docket No. FAA-2024-0757; Project Identifier MCAI-2023-
01205-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by May 6, 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.''
(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#d3eafe928580fe929a81fee4e0e3fe929e9c9093b5b2b2fdb4bca5"><span class="__cf_email__" data-cfemail="93aabed2c5c0bed2dac1bea4a0a3bed2dedcd0d3f5f2f2bdf4fce5">[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
[[Page 20367]]
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.
(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 817-222-5102; email
<a href="/cdn-cgi/l/email-protection#b3c7dadedcc7dbca9dc39dd7dcc4dfdaddd4f3d5d2d29dd4dcc5"><span class="__cf_email__" data-cfemail="5e2a3733312a3627702e703a3129323730391e383f3f70393128">[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#4100053201242032206f2434332e31206f2434"><span class="__cf_email__" data-cfemail="85c4c1f6c5e0e4f6e4abe0f0f7eaf5e4abe0f0">[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="a4c2d68acdcad7d4c1c7d0cdcbcae4cac5d6c58ac3cbd2">[email protected]</span></a>.
Issued on March 15, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-05914 Filed 3-21-24; 8:45 am]
BILLING CODE 4910-13-P
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