[Federal Register Volume 90, Number 94 (Friday, May 16, 2025)]
[Proposed Rules]
[Pages 20952-20956]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-08664]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0758; Project Identifier MCAI-2024-00651-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 supersede Airworthiness Directive (AD)
2022-15-05, 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 2022-15-05 requires repetitive high frequency eddy
current (HFEC) inspections for cracks on the web horizontal flange and
inner cap, and applicable corrective actions. Since the FAA issued AD
2022-15-05, additional cracks have been found at the door stop fitting
number 1 holes at frame (FR) 68, after disassembly of the door stop
fitting as part of the inspections required by AD 2022-15-05. This
proposed AD would continue to require the actions in AD 2022-15-05, but
with reduced compliances times for some inspections, and would require
an additional inspection at door stop fitting number 1, as specified in
a European Union Aviation Safety Agency (EASA) AD, which is proposed
for incorporation by reference. 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 June 30,
2025.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.
Fax: 202-493-2251.
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.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
[[Page 20953]]
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2025-0758; 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:
For EASA material identified in this proposed AD, 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. It is also
available at regulations.gov under Docket No. FAA-2025-0758.
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: Nathan Weigand, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-
231-3531; email: [email protected].
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-2025-0758;
Project Identifier MCAI-2024-00651-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
regulations.gov, 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
Nathan Weigand, Aviation Safety Engineer, FAA, 2200 South 216th St.,
Des Moines, WA 98198; phone: 206-231-3531; email:
[email protected]. 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 2022-15-05, Amendment 39-22125 (87 FR 45013, July
27, 2022) (AD 2022-15-05), for all Airbus SAS Model A318-111, A318-112,
A318-121, A318-122, A319-111, A319-112, A319-113, A319-114, A319-115,
A319-131, A319-132, A319-133, A320-211, A320-212, A320-214, A320-216,
A320-231, A320-232, A320-233, A321-111, A321-112, A321-131, A321-211,
A321-212, A321-213, A321-231, and A321-232 airplanes, except those
airplanes with certain modifications installed that convert the
airplane to a corporate jet. AD 2022-15-05 was prompted by MCAI
originated by EASA, which is the Technical Agent for the Member States
of the European Union. EASA issued AD 2022-0030, dated February 25,
2022 (EASA AD 2022-0030), to correct an unsafe condition identified as
cracks on the web horizontal flange and inner cap on FR 68, left-hand
(LH) and right-hand (RH) sides, at stringer (STGR) 22, which could
result in reduced structural integrity of the fuselage.
AD 2022-15-05 requires repetitive HFEC inspections for cracks on
the web horizontal flange and inner cap and applicable corrective
actions in accordance with EASA AD 2022-0030, which specifies using the
original or later-approved revisions of Airbus Service Bulletin A320-
53-1491. The FAA issued AD 2022-15-05 to address a report that during
the inspection for the door stop fitting holes at FR 66 and FR 68
required by EASA AD 2016-0238, dated December 2, 2016; corrected
January 4, 2017 (which prompted FAA AD 2018-03-12, Amendment 39-19185
(83 FR 5906, February 12, 2018)), cracks were found on the web
horizontal flange and inner cap on FR 68, LH and RH sides, at STGR 22.
Actions Since AD 2022-15-05 Was Issued
Since the FAA issued AD 2022-15-05, EASA superseded EASA AD 2022-
0030, dated February 25, 2022, and issued EASA AD 2024-0210, dated
October 29, 2024 (EASA AD 2024-0210) (also referred to as ``the
MCAI''), for all Airbus SAS Model A318-111, A318-112, A318-121, A318-
122, A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-
132, A319-133, A320-211, A320-212, A320-214, A320-215, A320-216, A320-
231, A320-232, A320-233, A321-111, A321-112, A321-131, A321-211, A321-
212, A321-213, A321-231, and A321-232 airplanes, except those airplanes
with certain modifications installed that convert the airplane to a
corporate jet. The MCAI states that after EASA AD 2022-0030 was issued,
cracks have been found at the door stop fitting number 1 holes at FR
68, after the door stop fitting disassembly as part of the inspections
in Airbus Service Bulletin A320-53-1491 Revision 1. Therefore, Airbus
issued revision 2 of its service bulletin to include an additional
inspection of the FR 68 door stop fitting number 1 holes with a larger
inspection area, and an additional HFEC inspection on FR68 around the
door stop fitting number 1 nuts. Some compliance times have been
reduced and the procedures in the service bulletin have been updated.
The FAA is proposing this AD to address cracks on the door stop 1,
web horizontal flange and inner cap on FR 68, LH and RH sides, at STGR
22, which could result in reduced structural integrity of the fuselage.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2025-0758.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2024-0210 specifies procedures for repetitive inspections
of certain areas of the fuselage and taking corrective actions if there
are cracks or discrepancies by following the manufacturer's service
information. EASA AD 2024-0210 also specifies reporting all inspection
findings to Airbus. Specifically, the inspections are high frequency
eddy current inspections of the frame horizontal flange radii, inner
cap fillet radius, the door stop 1 fasteners, and the frame inner cap
corner at FR 68. The instructions for the inspections depend on whether
a repair
[[Page 20954]]
part has been installed. On-condition corrective actions include
additional inspections for cracking, inspections to determine if a
certain modification or repair was done, and repair of cracking at the
web horizontal flange. 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 the requirements of AD 2022-15-
05, with reduced compliance times for some actions, additional
inspections, and updated procedures and figures. This proposed AD would
require accomplishing the actions specified in EASA AD 2024-0210
described previously, except for any differences identified as
exceptions in the regulatory text of this proposed AD. See
``Differences Between This NPRM and the MCAI'' for a discussion of
these differences.
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 2024-0210 by reference in the FAA
final rule. This proposed AD would, therefore, require compliance with
EASA AD 2024-0210 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 2024-0210 does not mean that
operators need to 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-
0210. Material required by EASA AD 2024-0210 for compliance will be
available at regulations.gov under Docket No. FAA-2025-0758 after the
FAA final rule is published.
Differences Between This NPRM and the MCAI
Where the MCAI specifies reporting information to the manufacturer,
this NPRM does not propose to require reporting. The FAA has determined
that it does not need the data from the reports.
Although the MCAI applies to Model A320-215 airplanes, this
proposed AD would not because that model does not have an FAA type
certificate.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 1,924 airplanes of U.S. registry. The FAA estimates the
following costs to comply with this proposed AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection for repair part..... 1 work-hour x $85 per $0 $85............... $163,540.
hour = $85.
High frequency eddy current 27 work-hours x $85 per 0 $2,295 per $4,415,580 per
inspection. hour = $2,295 per inspection cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any on-condition
inspections that would be required based on the results of the high
frequency eddy current inspections. The FAA has no way of determining
the number of airplanes that might need these on-condition inspections:
Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
On-condition inspections.............. Up to 30 work-hours x $85 per $0 Up to $2,550.
hour = $2,550.
----------------------------------------------------------------------------------------------------------------
The extent of cracking and other conditions found during the
inspections could vary significantly from airplane to airplane. The FAA
has no way of determining which conditions may be found on each
airplane, the cost to correct or repair each airplane, or the number of
airplanes that may require repair.
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
[[Page 20955]]
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) 2022-15-05, Amendment 39-22125
(87 FR 45013, July 27, 2022); and
0
b. Adding the following new AD:
Airbus SAS: Docket No. FAA-2025-0758; Project Identifier MCAI-2024-
00651-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by June 30, 2025.
(b) Affected ADs
This AD replaces AD 2022-15-05, Amendment 39-22125 (87 FR 45013,
July 27, 2022) (AD 2022-15-05).
(c) Applicability
This AD applies to Airbus SAS Model 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 2024-0210, dated October 29, 2024 (EASA AD 2024-0210).
(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 a report that cracks were found on the
web horizontal flange and inner cap on frame (FR) 68, left-hand (LH)
and right-hand (RH) sides, at stringer (STGR) 22, and at the door
stop fitting number 1 holes at FR 68. The FAA is issuing this AD to
address the cracks on the door stop 1, web horizontal flange and
inner cap on FR 68, LH and RH sides, at STGR 22. The unsafe
condition, if not addressed, 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 2024-0210.
(h) Exceptions to EASA AD 2024-0210
(1) Where EASA AD 2024-0210 refers to ``22 November 2021 [the
effective date of EASA AD 2021-0242]'', this AD requires using
August 31, 2022 (the effective date of AD 2022-15-05).
(2) Where EASA AD 2024-0210 refers to its effective date, this
AD requires using the effective date of this AD.
(3) Where paragraph (1) of EASA AD 2024-0210 refers to ``the
SDI'', this AD requires replacing that text with ``the applicable
inspections''.
(4) This AD does not adopt the ``Remarks'' section of EASA AD
2024-0210.
(5) This AD does not adopt paragraphs (2) and (3) of EASA AD
2024-0210.
(6) Where paragraph (4) of EASA AD 2024-0210 states
``discrepancies'', this AD requires replacing that word with
``conditions''.
(7) Where paragraph (4) of EASA AD 2024-0210 states ``within the
compliance time specified therein'', this AD requires replacing that
text with ``before further flight''.
(8) Where paragraph (6) of EASA AD 2024-0210 specifies ``the
instructions provided by Airbus'', for this AD, those instructions
must be approved by the FAA, 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 paragraph (7) of and the material referenced in EASA AD
2024-0210 specify 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
the Continued Operational Safety Branch, send it to the attention of
the person identified in paragraph (k) of this AD and email 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, 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
paragraphs (h), (i), and (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 Nathan Weigand,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; phone: 206-231-3531; email: [email protected].
(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 2024-0210,
dated October 29, 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 [email protected]; 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 www.archives.gov/federal-register/cfr/ibr-locations, or email [email protected].
[[Page 20956]]
Issued on May 12, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-08664 Filed 5-15-25; 8:45 am]
BILLING CODE 4910-13-P