[Federal Register Volume 90, Number 91 (Tuesday, May 13, 2025)]
[Proposed Rules]
[Pages 20261-20264]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-08331]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0754; Project Identifier MCAI-2024-00489-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)
2017-23-04, which applies to all Airbus SAS Model A300 B4-600R series
airplanes; all Model A300 B4-603, B4-620, and B4-622 airplanes; all
Model A300 C4-605R Variant F airplanes; and certain Model A300 F4-605R
airplanes. AD 2017-23-04 requires an inspection of the upper wing skin
and top stringer joints, and modification of the stringer joint
couplings if necessary. Since the FAA issued AD 2017-23-04, it has been
determined that additional airplanes may be subject to the identified
unsafe condition. This proposed AD would continue to require the
actions in AD 2017-23-04 and would add airplanes, as specified in a
European Union Aviation Safety Agency (EASA) AD, which is proposed for
incorporation by reference (IBR). This proposed AD would also remove
certain airplanes from the applicability. 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 27,
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.
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2025-0754; 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]. 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-2025-0754.
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: Aaron Nguyen, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 817-
222-5134; 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-2025-0754;
Project Identifier MCAI-2024-00489-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 Aaron
Nguyen, Aviation Safety Engineer, FAA, 2200 South 216th St., Des
Moines, WA 98198; phone: 817-222-5134; 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 2017-23-04, Amendment 39-19098 (82 FR 52832,
November 15, 2017) (AD 2017-23-04), for all Airbus SAS Model A300 B4-
600R series airplanes; all Model A300 B4-603, B4-620, and B4-622
airplanes; all Model A300 C4-605R Variant F airplanes; and certain
Model A300 F4-605R airplanes. AD 2017-23-04 was prompted by an MCAI
originated by EASA, which is the Technical Agent for the Member States
of the European Union. EASA issued AD 2017-0023, dated February 10,
2017 (EASA AD 2017-0023), to correct an unsafe condition.
AD 2017-23-04 requires an inspection of the upper wing skin and top
stringer joints, and modification of the stringer joint couplings if
necessary. The FAA issued AD 2017-23-04 to
[[Page 20262]]
detect and correct damage (including cracking) at the stringer joints,
which could reduce the structural integrity of the wing.
Actions Since AD 2017-23-04 Was Issued
Since the FAA issued AD 2017-23-04, EASA superseded AD 2017-0023
and issued EASA AD 2024-0170, dated August 26, 2024 (EASA AD 2024-0170)
(also referred to as the MCAI), to correct an unsafe condition for all
Airbus SAS Model A300 B4-603, B4-605R, B4-622, B4-622R, C4-605R Variant
F, C4-620, F4-605R, and F4-622R airplanes. Model A300 C4-620 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 also removes Model A300
B4-620 airplanes from the applicability as none are operational. The
MCAI states that EASA AD 2024-0170 was issued to expand the
applicability to include Model A300 F4-605R airplanes in post-
modification 12699 configuration (i.e., airplanes embodied with Airbus
modification 12699) and A300 F4-622R airplanes, even though the
introduced models are below the lower threshold of the embodiment
window (for modification of the stringer joint couplings), ensuring
that their structures remain resistant against widespread fatigue
damage within their established limit of validity.
The FAA is proposing this AD to detect and correct damage
(including cracking) at the stringer joints, which could reduce the
structural integrity of the wing. You may examine the MCAI in the AD
docket at regulations.gov under Docket No. FAA-2025-0754.
Explanation of Retained Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2017-23-04, this proposed AD would retain all of the
requirements of AD 2017-23-04. Those requirements are referenced in
EASA AD 2024-0170, which, in turn, is referenced in paragraph (g) of
this proposed AD.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2024-0170 specifies procedures for a detailed visual
inspection of the upper wing skin and top stringer joints at rib 18 for
damage (including cracking), modification of the stringer joint
couplings at rib 18, and corrective actions if necessary. The
modification includes oversizing fastener holes in the upper wing skin
and doing a special detailed (roto-probe) inspection for damage,
including cracking, of the fastener holes. Corrective actions include
obtaining and following 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 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 2017-23-04.
This proposed AD would revise the applicability by removing Model A300
B4-620 airplanes, adding Model A300 F4-622R airplanes, and expanding
the applicability to include Model A300 F4-605R airplanes that were
excepted from AD 2017-23-04 (i.e., airplanes embodied with Airbus
modification 12699 in production). This proposed AD would require
accomplishing the actions specified in EASA AD 2024-0170 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 2024-0170 by reference in the FAA
final rule. This proposed AD would, therefore, require compliance with
EASA AD 2024-0170 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 2024-0170 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-
0170. Material required by EASA AD 2024-0170 for compliance will be
available at regulations.gov under Docket No. FAA-2025-0754 after the
FAA final rule is published.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 119 airplanes of U.S. registry. The FAA estimates the following
costs to comply with this proposed AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2017-23-04... 38 work-hours x $85 per $9,540 $12,770 $1,519,630
hour = $3,230.
----------------------------------------------------------------------------------------------------------------
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 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
[[Page 20263]]
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(f), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive (AD) 2017-23-04, Amendment 39-19098
(82 FR 52832, November 15, 2017); and
0
b. Adding the following new AD:
Airbus SAS: Docket No. FAA-2025-0754; Project Identifier MCAI-2024-
00489-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by June 27, 2025.
(b) Affected ADs
This AD replaces AD 2017-23-04, Amendment 39-19098 (82 FR 52832,
November 15, 2017) (AD 2017-23-04).
(c) Applicability
This AD applies to all Airbus SAS Model A300 B4-603, B4-605R,
B4-622, B4-622R, C4-605R Variant F, F4-605R, and F4-622R airplanes,
certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by the determination that the top stringer
joints at rib 18 are an area of uniform stress distribution, which
indicates that cracks may develop in adjacent stringer at the same
time, and by the determination that additional airplanes are subject
to the unsafe condition. The FAA is issuing this AD to detect and
correct damage (including cracking) at the stringer joints. The
unsafe condition, if not addressed, could result in reduced
structural integrity of the wing.
(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, European Union Aviation Safety Agency (EASA) AD
2024-0170, dated August 26, 2024 (EASA AD 2024-0170).
(h) Exceptions to EASA AD 2024-0170
(1) Where EASA AD 2024-0170 refers to ``24 February 2017 [the
effective date of EASA AD 2017-0023]'', this AD requires using
``December 20, 2017 (the effective date of AD 2017-23-04)''.
(2) Where EASA AD 2024-0170 refers to its effective date, this
AD requires using the effective date of this AD.
(3) Where EASA AD 2024-0170 does not define ``average flight
time'' for determining the short range (SR) and long (RC) airplanes,
this AD defines ``average flight time'' as the total accumulated
flight hours, counted from takeoff to touchdown, divided by the
total accumulated flight cycles as of December 20, 2017 (the
effective date of AD 2017-23-04).
(4) Where paragraph (1) of EASA AD 2024-0170 specifies to
accomplish all applicable corrective actions and modify the stringer
joint couplings, this AD requires accomplishing the applicable
corrective actions and modification before further flight after the
inspection.
(5) Where the referenced material in EASA AD 2024-0170 specifies
inspecting for damage, this AD defines damage as cracking.
(6) This AD does not adopt the ``Remarks'' section of EASA AD
2024-0170.
(i) 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 (j) 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, 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 (i)(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.
(j) Additional Information
For more information about this AD, contact Aaron Nguyen,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; phone: 817-222-5134; email: [email protected].
(k) 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 2024-0170,
dated August 26, 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]. 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 20264]]
Issued on May 6, 2025.
Victor Wicklund,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-08331 Filed 5-12-25; 8:45 am]
BILLING CODE 4910-13-P