Rule2023-20174
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
September 19, 2023
Effective
October 24, 2023
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2020-06- 10, which applied 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 2020-06-10 required repetitive inspections for cracking of the vertical stiffeners of the left- and right-hand sides of the window frames and corrective actions if necessary. Since the FAA issued AD 2020-06-10, it was determined that certain compliance times need to be reduced. This AD retains the requirements of AD 2020-06-10, with amended compliance times, as specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference (IBR). 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 180 (Tuesday, September 19, 2023)</title>
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[Federal Register Volume 88, Number 180 (Tuesday, September 19, 2023)]
[Rules and Regulations]
[Pages 64365-64368]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2023-20174]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-1221; Project Identifier MCAI-2023-00070-T;
Amendment 39-22543; AD 2023-18-02]
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 superseding Airworthiness Directive (AD) 2020-06-
10, which applied 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 2020-06-10 required repetitive inspections for cracking of the
vertical stiffeners of the left- and right-hand sides of the window
frames and corrective actions if necessary. Since the FAA issued AD
2020-06-10, it was determined that certain compliance times need to be
reduced. This AD
[[Page 64366]]
retains the requirements of AD 2020-06-10, with amended compliance
times, as specified in a European Union Aviation Safety Agency (EASA)
AD, which is proposed for incorporation by reference (IBR). The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective October 24, 2023.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 24,
2023.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2023-1221; 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 the EASA AD 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#a7e6e3d4e7c2c6d4c689c2d2d5c8d7c689c2d2"><span class="__cf_email__" data-cfemail="b5f4f1c6f5d0d4c6d49bd0c0c7dac5d49bd0c0">[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-2023-1221.
FOR FURTHER INFORMATION CONTACT: Timothy 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#e9bd8084869d8190c7b9c7ad869e8580878ea98f8888c78e869f"><span class="__cf_email__" data-cfemail="7f2b1612100b1706512f513b1008131611183f191e1e51181009">[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 2020-06-10, Amendment 39-19879 (85 FR
17490, March 30, 2020) (AD 2020-06-10). AD 2020-06-10 applied 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 2020-06-10 required
repetitive inspections for cracking of the vertical stiffeners of the
left- and right-hand sides of the window frames and corrective actions
if necessary, as specified in EASA AD 2019-0173, dated July 18, 2019
(EASA AD 2019-0173). The FAA issued AD 2020-06-10 to address cracking
of the vertical stiffeners of the left- and right-hand sides of the
window frames, which could affect the structural integrity of the
airplane.
The NPRM published in the Federal Register on June 27, 2023 (88 FR
41518). The NPRM was prompted by AD 2023-0009, dated January 16, 2023,
issued by EASA (EASA AD 2023-0009) (also referred to as the MCAI),
which superseded EASA AD 2019-0173. Since EASA AD 2019-0173 was issued,
it was determined that certain compliance times need to be reduced,
based on further analysis. The MCAI states that, during an inspection,
cracking was found on the frame of the right-hand side sliding window
in the flight deck. This condition, if not corrected, could lead to
reduced structural integrity of the airplane.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2023-1221.
In the NPRM, the FAA proposed to retain the requirements of AD
2020-06-10, with amended compliance times, as specified in EASA AD
2023-0009. The FAA is issuing this AD to address cracking of the
vertical stiffeners of the left- and right-hand sides of the window
frames, which could affect the structural integrity of the airplane.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from one commenter, United Airlines, who
supported the NPRM without change.
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, 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 2023-0009 specifies procedures for repetitive inspections
for cracking of the vertical stiffeners of the left- and right-hand
sides of the window frame and corrective actions if necessary.
Corrective actions include modification, rework, 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.
Costs of Compliance
The FAA estimates that this AD affects 1,525 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 2020-06- 11 work-hours x $85 $0 $935 $1,425,875 per
10. per hour = $935. inspection cycle.
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* Table does not include estimated costs for reporting.
The FAA estimates that it would take about 1 work-hour per product
to comply with the reporting requirement in this AD. The average labor
rate is $85 per hour. Based on these figures, The FAA estimates the
cost of reporting the inspection results on U.S. operators to be
$129,625, or $85 per product.
The FAA estimates the following costs to do any necessary on-
condition modifications that would be required based on the results of
any required
[[Page 64367]]
actions. The FAA has no way of determining the number of aircraft that
might need this on-condition modification:
Estimated Costs of On-Condition Actions
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Cost per
Labor cost Parts cost product
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5 work-hours x $85 per hour = $425.... (*) * $425
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* The FAA has received no definitive data on which to base the parts
cost estimates for the on-condition modification specified in this AD.
The FAA has received no definitive data that would enable the
agency to provide cost estimates for the other on-condition actions
specified in this AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to take
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, and completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Send comments regarding this burden estimate
or any other aspect of this collection of information, including
suggestions for reducing this burden, to: Information Collection
Clearance Officer, Federal Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177-1524.
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
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) 2020-06-10, Amendment 39-19879
(85 FR 17490, March 30, 2020); and
0
b. Adding the following new AD:
2023-18-02 Airbus SAS: Amendment 39-22543; Docket No. FAA-2023-1221;
Project Identifier MCAI-2023-00070-T.
(a) Effective Date
This airworthiness directive (AD) is effective October 24, 2023.
(b) Affected ADs
This AD replaces AD 2020-06-10, Amendment 39-19879 (85 FR 17490,
March 30, 2020) (AD 2020-06-10).
(c) Applicability
This AD applies to Airbus SAS Model airplanes specified in
paragraphs (c)(1) through (4) of this AD, certificated in any
category, as identified in European Union Aviation Safety Agency
(EASA) AD 2023-0009, dated January 16, 2023 (EASA AD 2023-0009).
(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 of cracking found on the frame
of the right-hand side sliding window in the flight deck, and a
determination that certain compliance times need to be reduced. The
FAA is issuing this AD to address cracking of the vertical
stiffeners of the left- and right-hand sides of the window frames,
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, EASA AD 2023-0009.
(h) Exceptions to EASA AD 2023-0009
(1) Where EASA AD 2023-0009 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where EASA AD 2023-0009 refers to August 1, 2019 (the
effective date of EASA AD 2019-0173), this AD requires using May 4,
2020 (the effective date of AD 2020-06-10).
(3) This AD does not adopt the ``Remarks'' section of EASA AD
2023-0009.
(4) Paragraph (3) of EASA AD 2023-0009 specifies to report
inspection results to Airbus within a certain compliance time. For
this AD, report inspection results (in case of findings only) at the
applicable time
[[Page 64368]]
specified in paragraph (h)(4)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 90 days after the inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 90 days after the effective date
of this AD.
(5) Where paragraph (5) of EASA AD 2023-0009 specifies credit
for certain actions, this AD provides credit for using the torque
values specified in Section 13 of the Airbus technical adaptations
(TAs) identified in paragraphs (h)(5)(i) through (vi) of this AD,
when installing a certain eccentric referenced in ``Airbus SB A320-
53-1402 original issue'' or ``Airbus SB A320-53-1403 original
issue,'' as specified in the applicable TA, before the effective
date of this AD.
(i) Airbus TA 80662272/007/2019, Issue 1, dated August 29, 2019.
(ii) Airbus TA 80662272/008/2019, Issue 1, dated August 29,
2019.
(iii) Airbus TA 80662272/009/2019, Issue 1, dated August 29,
2019.
(iv) Airbus TA 80662272/010/2019, Issue 1, dated August 29,
2019.
(v) Airbus TA 80696258/006/2019, Issue 1, dated October 29,
2019.
(vi) Airbus TA 80696258/007/2019, Issue 1, dated October 29,
2019.
(6) Where Table 1 of EASA AD 2023-0009 specifies configurations,
replace the text ``post SB'' with ``post embodiment of SB'' and
replace the text ``pre SB'' with ``pre embodiment of SB.''
(i) Special Flight Permit
Special flight permits, as described in 14 CFR 21.197 and
21.199, may be issued to operate the airplane to a location where
the requirements of this AD can be accomplished, but concurrence by
the Manager, International Validation Branch, FAA, is required
before issuance of the special flight permit.
(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#1b22365a4d48365a5249362c282b365a5654585b7d7a7a357c746d"><span class="__cf_email__" data-cfemail="734a5e3225205e323a215e4440435e323e3c30331512125d141c05">[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 2020-06-10 are approved as
AMOCs for the corresponding provisions of EASA AD 2023-0009 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
paragraph (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; telephone 206-231-3667; email
<a href="/cdn-cgi/l/email-protection#f1a5989c9e859988dfa1dfb59e869d989f96b1979090df969e87"><span class="__cf_email__" data-cfemail="adf9c4c0c2d9c5d483fd83e9c2dac1c4c3caedcbcccc83cac2db">[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 2023-0009,
dated January 16, 2023.
(ii) [Reserved]
(3) For EASA AD 2023-0009, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#b7f6f3c4f7d2d6c4d699d2c2c5d8c7d699d2c2"><span class="__cf_email__" data-cfemail="1e5f5a6d5e7b7f6d7f307b6b6c716e7f307b6b">[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 service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email <a href="/cdn-cgi/l/email-protection#dabca8f4b3b4a9aabfb9aeb3b5b49ab4bba8bbf4bdb5ac"><span class="__cf_email__" data-cfemail="e08692ce898e9390858394898f8ea08e819281ce878f96">[email protected]</span></a>, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued on September 1, 2023.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2023-20174 Filed 9-18-23; 8:45 am]
BILLING CODE 4910-13-P
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