Rule2023-27115
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 12, 2023
Effective
January 16, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200 Freighter series airplanes. This AD was prompted by a widespread fatigue damage (WFD) evaluation on Airbus SAS Model A330-200 Freighter series airplanes, which found that the circumferential joint at Frame 58 (near the rear fuselage) is susceptible to WFD. This AD requires a modification to reinforce the circumferential joints at Frame 58 and, if necessary, corrective action, 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 88 Issue 237 (Tuesday, December 12, 2023)</title>
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[Federal Register Volume 88, Number 237 (Tuesday, December 12, 2023)]
[Rules and Regulations]
[Pages 86036-86039]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2023-27115]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-1723; Project Identifier MCAI-2023-00457-T;
Amendment 39-22605; AD 2023-23-03]
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 all
Airbus SAS Model A330-200 Freighter series airplanes. This AD was
prompted by a widespread fatigue damage (WFD) evaluation on Airbus SAS
Model A330-200 Freighter series airplanes, which found that the
circumferential joint at Frame 58 (near the rear fuselage) is
susceptible to WFD. This AD requires a modification to reinforce the
circumferential joints at Frame 58 and, if necessary, corrective
action, 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 January 16, 2024.
[[Page 86037]]
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 16,
2024.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2023-1723; 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 incorporated by reference 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#bcfdf8cffcd9ddcfdd92d9c9ced3ccdd92d9c9"><span class="__cf_email__" data-cfemail="bbfaffc8fbdedac8da95decec9d4cbda95dece">[email protected]</span></a>; website easa.europa.eu. You may
find this material on the EASA website at ad.easa.europa.eu.
<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. It is also available in the AD docket at
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2023-1723.
FOR FURTHER INFORMATION CONTACT: Tim 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#dda9b4b0b2a9b5a4f3adf3b9b2aab1b4b3ba9dbbbcbcf3bab2ab"><span class="__cf_email__" data-cfemail="f3879a9e9c879b8add83dd979c849f9a9d94b3959292dd949c85">[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 all Airbus SAS Model
A330-223F and -243F airplanes. The NPRM published in the Federal
Register on August 31, 2023 (88 FR 60157). The NPRM was prompted by AD
2023-0053, dated March 14, 2023, issued by EASA, which is the Technical
Agent for the Member States of the European Union (EASA AD 2023-0053)
(also referred to as the MCAI). The MCAI states that within the scope
of WFD evaluations on Model A330-200 Freighter series airplanes, it was
determined that the circumferential joint at Frame 58 (near the rear
fuselage) is susceptible to WFD. WFD, if not corrected, may lead to
crack initiation and undetected propagation, which could affect the
structural integrity of the airplane.
In the NPRM, the FAA proposed to require a modification to
reinforce the circumferential joints at Frame 58 and, if necessary,
corrective action, as specified in EASA AD 2023-0053. 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-2023-1723.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the NPRM or on the determination of
the cost to the public.
Additional Change to This AD
The FAA revised paragraph (h)(3) of this AD to clarify that if any
discrepancy other than cracking is found, operators must obtain
instructions and accomplish those instructions accordingly. If cracking
is found, operators must obtain instructions and repair the cracking
before further flight. In the NPRM, the FAA inadvertently specified
only cracking as a discrepancy; however, incorrect hole diameters are
also a possible discrepancy.
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 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.
Related Service Information Under 1 CFR Part 51
EASA AD 2023-0053 specifies procedures for a modification
(including rotating probe inspections for discrepancies and measurement
of the maximum hole diameter at any point in the fastener hole bores on
the circumferential joints) to reinforce the circumferential joints at
Frame 58 and, if any discrepancies (cracking or measurements that are
outside the acceptable hole diameters) are found, corrective action
(contacting the manufacturer for instructions and accomplishing those
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.
Explanation of Compliance Time
The compliance time for the replacement specified in this AD for
addressing WFD was established to ensure that certain structure is
replaced before WFD develops in airplanes. Standard inspection
techniques cannot be relied on to detect WFD before it becomes a hazard
to flight. The FAA will not grant any extensions of the compliance time
to complete any AD-mandated service bulletin related to WFD without
extensive new data that would substantiate and clearly warrant such an
extension.
Costs of Compliance
The FAA estimates that this AD will affect 6 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
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368 work-hours x $85 per hour = $31,280...................... $7,700 $38,980 $233,880
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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 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
[[Page 86038]]
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:
2023-23-03 Airbus SAS: Amendment 39-22605; Docket No. FAA-2023-1723;
Project Identifier CAI-2023-00457-T.
(a) Effective Date
This airworthiness directive (AD) is effective January 16, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus SAS Model A330-223F and -243F
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a widespread fatigue damage (WFD)
evaluation on Model A330-200 Freighter series airplanes, which found
that the circumferential joint at Frame 58 (near the rear fuselage)
is susceptible to WFD. The FAA is issuing this AD to address WFD in
the affected area. The unsafe condition, if not corrected, may lead
to crack initiation and undetected propagation, which could affect
the 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, European Union Aviation Safety Agency (EASA) AD
2023-0053, dated March 14, 2023 (EASA AD 2023-0053).
(h) Exceptions to EASA AD 2023-0053
(1) Where EASA AD 2023-0053 refers to its effective date, this
AD requires using the effective date of this AD.
(2) This AD does not adopt the ``Remarks'' section of EASA AD
2023-0053.
(3) Where paragraph (2) of EASA AD 2023-0053 specifies ``if,
during the accomplishment of any inspection, which is part of the
modification as required by paragraph (1) of this AD, any
discrepancy, as identified in the SB, is detected, before next
flight, contact Airbus for approved instructions and accomplish
those instructions accordingly,'' this AD requires replacing those
words with ``if, during the accomplishment of any inspection, which
is part of the modification as required by paragraph (1) of this AD,
any discrepancy other than cracking is detected, before next flight,
contact the Manager, International Validation Branch, FAA; or EASA;
or Airbus SAS's EASA Design Organization Approval (DOA) for approved
instructions and accomplish those instructions accordingly; and if
any cracking is detected, the cracking must be repaired before
further flight 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.''
(i) 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 International
Validation Branch, send it to the attention of the person identified
in paragraph (j) of this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#f8c1d5b9aeabd5b9b1aad5cfcbc8d5b9b5b7bbb89e9999d69f978e"><span class="__cf_email__" data-cfemail="80b9adc1d6d3adc1c9d2adb7b3b0adc1cdcfc3c0e6e1e1aee7eff6">[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 (i)(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.
(j) Additional Information
For more information about this AD, contact Tim 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#b8ccd1d5d7ccd0c196c896dcd7cfd4d1d6dff8ded9d996dfd7ce"><span class="__cf_email__" data-cfemail="6c18050103180415421c4208031b0005020b2c0a0d0d420b031a">[email protected]</span></a>.
(k) 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 2023-0053,
dated March 14, 2023.
(ii) [Reserved]
(3) For EASA AD 2023-0053, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#6223261122070311034c0717100d12034c0717"><span class="__cf_email__" data-cfemail="5f1e1b2c1f3a3e2c3e713a2a2d302f3e713a2a">[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 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
[[Page 86039]]
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#1b7d69357275686b7e786f7274755b757a697a357c746d"><span class="__cf_email__" data-cfemail="583e2a7631362b283d3b2c3137361836392a39763f372e">[email protected]</span></a>.
Issued on November 9, 2023.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2023-27115 Filed 12-11-23; 8:45 am]
BILLING CODE 4910-13-P
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