Rule2024-05494
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 18, 2024
Effective
April 22, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2018-14- 09, which applied to certain Airbus SAS Model A318 series airplanes; Model A319 series 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 2018-14-09 required repetitive inspections for cracking of the fastener holes in certain fuselage frames, and depending on airplane configuration, provides an optional terminating action to the repetitive inspections. This AD was prompted by reports of early cracking on the four holes of the crossbeam splicing at certain fuselage frames (FR). This AD continues to require the actions in AD 2018-14-09 at modified compliance times, requires further inspections, and provides optional terminating actions for certain airplanes; as specified in 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
<html>
<head>
<title>Federal Register, Volume 89 Issue 53 (Monday, March 18, 2024)</title>
</head>
<body><pre>
[Federal Register Volume 89, Number 53 (Monday, March 18, 2024)]
[Rules and Regulations]
[Pages 19231-19234]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-05494]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-2144; Project Identifier MCAI-2023-00898-T;
Amendment 39-22683; AD 2024-04-04]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-14-
09, which applied to certain Airbus SAS Model A318 series airplanes;
Model A319 series 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 2018-14-09 required repetitive
inspections for cracking of the fastener holes in certain fuselage
frames, and depending on airplane configuration, provides an optional
terminating action to the repetitive inspections. This AD was prompted
by reports of early cracking on the four holes of the crossbeam
splicing at certain fuselage frames (FR). This AD continues to require
the actions in AD 2018-14-09 at modified compliance times, requires
further inspections, and provides optional terminating actions for
certain airplanes; as specified in 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 April 22, 2024.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 22,
2024.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2023-2144; 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#2d6c695e6d484c5e4c0348585f425d4c034858"><span class="__cf_email__" data-cfemail="e0a1a493a085819381ce8595928f9081ce8595">[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 that is incorporated by
reference 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-2023-2144.
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#c0b4a9adafb4a8b9eeb0eea4afb7aca9aea780a6a1a1eea7afb6"><span class="__cf_email__" data-cfemail="eb9f8286849f8392c59bc58f849c8782858cab8d8a8ac58c849d">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2018-14-09, Amendment 39-19329 (83 FR
34034, July 19, 2018) (AD 2018-14-09). AD 2018-14-09 applied to certain
Airbus SAS Model A318 series airplanes; Model A319 series 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 2018-14-09 required repetitive inspections for cracking of the
fastener holes in certain fuselage frames, and depending on airplane
configuration, provides an optional terminating action to the
repetitive inspections. The FAA issued AD 2018-14-09 to address
cracking at two upper rows of fasteners of the crossbeam splicing at
frame (FR)16 and FR20, on both the left-hand (LH) and right-hand (RH)
sides, which can result in reduced structural integrity of the airplane
due to the failure of structural components.
The NPRM published in the Federal Register on November 6, 2023 (88
FR 76147). The NPRM was prompted by AD 2023-0150, dated July 20, 2023
(EASA AD 2023-0150) (also referred to as the MCAI), issued by EASA,
which is the Technical Agent for the Member States of the European
Union. The MCAI states that repetitive inspections were instituted due
to reports of cracks on the four holes of the crossbeam splicing at
FR16 and FR20 on both LH and RH sides. Following further assessments,
the need was determined for additional inspections, reduced
[[Page 19232]]
compliance times, and an additional terminating action option.
In the NPRM, the FAA proposed to continue to require repetitive
inspections for cracking of the fastener holes in certain fuselage
frames, and depending on airplane configuration, to provide an optional
terminating action to the repetitive inspections, as specified in EASA
AD 2023-0150. 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-2023-2144.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from American Airlines and United
Airlines. The following presents the comments received on the NPRM and
the FAA's response.
Request To Allow Previously Issued Alternative Methods of Compliance
(AMOCs)
American Airlines and United Airlines requested that the proposed
AD be changed to allow the use of previously issued AMOCs including
global AMOC AIR-731-23-00448, dated September 19, 2023, for certain
actions of AD 2018-14-09 that are retained in this AD.
The FAA agrees and has redesignated paragraph (j)(1) of the
proposed AD as paragraphs (j)(1) and (j)(1)(i) of this AD and has added
paragraph (j)(1)(ii) of this AD to allow the use of applicable
previously issued AMOCs.
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, considered the
comments received, 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 2023-0150 specifies procedures for repetitive rototest
inspections for cracking of the holes in certain fuselage frames and
crossbeams and applicable corrective actions (including repairing
cracking and replacing fasteners); and, for certain airplanes,
procedures for modifying the airplane, including cold working
instructions in certain fuselage frames and crossbeams, which would
terminate the inspections (optional terminating action). 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.
Costs of Compliance
The FAA estimates that this AD affects 1,680 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.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2018-14-09.... 31 work-hours x $85 per $0 $2,635 $4,426,800
hour = $2,635.
----------------------------------------------------------------------------------------------------------------
Estimated Costs for Optional Actions
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
28 work-hours x $85 per hour = $2,380. $3,020 $5,400
------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any
required or optional actions. The FAA has no way of determining the
number of aircraft that might need this on-condition action:
Estimated Costs of On-Condition Replacements
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
14 work-hours x $85 per hour = $1,190. $50 $1,240
------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs 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 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
[[Page 19233]]
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:
0
a. Removing Airworthiness Directive (AD) 2018-14-09, Amendment 39-19329
(83 FR 34034, July 19, 2018); and
0
b. Adding the following new AD:
2024-04-04 Airbus SAS: Amendment 39-22683; Docket No. FAA-2023-2144;
Project Identifier MCAI-2023-00898-T.
(a) Effective Date
This airworthiness directive (AD) is effective April 22, 2024.
(b) Affected ADs
This AD replaces AD 2018-14-09, Amendment 39-19329 (83 FR 34034,
July 19, 2018) (AD 2018-14-09).
(c) Applicability
This AD applies to Airbus SAS Model A318-111, -112, -121, and -
122 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; certificated in any category, all
manufacturer serial numbers, except the airplanes specified in
paragraphs (c)(1) through (3) of this AD.
(1) Airplanes on which Airbus SAS modification 161255 has been
embodied in production.
(2) Model A319 series airplanes on which Airbus SAS
modifications 28238, 28162, and 28342 have been concurrently
embodied in production.
(3) Model A318 series airplanes on which Airbus SAS modification
39195 has been embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of early cracking on the four
holes of the crossbeam splicing at certain fuselage frames (FR). The
FAA is issuing this AD to address cracking at two upper rows of
fasteners of the crossbeam splicing at FR16 and FR20, on both the
left-hand (LH) and right-hand (RH) sides. The unsafe condition, if
not addressed, could result in reduced structural integrity of the
airplane due to the failure of structural components.
(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
2023-0150, dated July 20, 2023 (EASA AD 2023-0150).
(h) Exceptions to EASA AD 2023-0150
(1) Where EASA AD 2023-0150 refers to ``28 July 2016 [the
effective date of EASA AD 2016-0139],'' this AD requires using
August 23, 2018 (the effective date of AD 2018-14-09).
(2) Where EASA AD 2023-0150 refers to its effective date, this
AD requires using the effective date of this AD.
(3) Where rows B and C of the ``Threshold'' column in Table 1 of
EASA AD 2023-0150 refer to ``54 800 FH,'' for this AD, replace that
text with ``54 900 FH.''
(4) Where paragraph (5) of EASA AD 2023-0150 refers to ``valid
within the EASA system,'' for this AD, replace that text with
``approved by the FAA, EASA, Airbus SAS's EASA Design Organization
Approval (DOA), or an EASA DOA (other than Airbus SAS's EASA DOA).''
(5) Where paragraph (5) of EASA AD 2023-0150 specifies ``contact
that design approval holder (DAH) for assessment and repair
instructions, obtain EASA AMOC approval and accomplish those
instructions accordingly, as applicable,'' for this AD, replace that
text with ``modify the repair 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.''
(6) Where the service information referenced in paragraphs (8)
and (9) of EASA AD 2023-0150 refers to actions when an existing hole
diameter is ``more than or equal to the minimum starting hole
diameter,'' for this AD, replace that text with ``more than or equal
to the maximum starting hole diameter.''
(7) This AD does not adopt the ``Remarks'' section of EASA AD
2023-0150.
(i) No Reporting Requirement
Although the service information referenced in EASA AD 2023-0150
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 International
Validation Branch, send it to the attention of the person identified
in paragraph (k) of this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#566f7b1700057b171f047b6165667b171b19151630373778313920"><span class="__cf_email__" data-cfemail="a1988ce0f7f28ce0e8f38c9692918ce0eceee2e1c7c0c08fc6ced7">[email protected]</span></a>.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(ii) AMOCs approved previously for AD 2018-14-09 are approved as
AMOCs for the corresponding provisions of EASA AD 2023-0150 that are
required by paragraph (g) of this AD.
(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
paragraphs (i) and (j)(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.
(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#d9adb0b4b6adb1a0f7a9f7bdb6aeb5b0b7be99bfb8b8f7beb6af"><span class="__cf_email__" data-cfemail="f7839e9a98839f8ed987d99398809b9e9990b7919696d9909881">[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.
[[Page 19234]]
(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 2023-0150,
dated July 20, 2023.
(ii) [Reserved]
(3) For EASA AD 2023-0150, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#1150556251747062703f7464637e61703f7464"><span class="__cf_email__" data-cfemail="92d3d6e1d2f7f3e1f3bcf7e7e0fde2f3bcf7e7">[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 that is incorporated by reference
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#80e6f2aee9eef3f0e5e3f4e9efeec0eee1f2e1aee7eff6"><span class="__cf_email__" data-cfemail="abcdd985c2c5d8dbcec8dfc2c4c5ebc5cad9ca85ccc4dd">[email protected]</span></a>.
Issued on March 11, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-05494 Filed 3-15-24; 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 March 18, 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.