[Federal Register Volume 88, Number 230 (Friday, December 1, 2023)]
[Rules and Regulations]
[Pages 83813-83817]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-26404]



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 Rules and Regulations
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  Federal Register / Vol. 88, No. 230 / Friday, December 1, 2023 / 
Rules and Regulations  

[[Page 83813]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-1409; Project Identifier MCAI-2022-01645-T; 
Amendment 39-22610; AD 2023-23-08]
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) 2019-07-
05, which applied to all 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 
2019-07-05 required repetitive inspections for cracking of the 10VU 
rack fitting lugs and repair of any cracking. This AD continues to 
require the requirements of AD 2019-07-05, with reduced compliance 
times and removes airplanes having a certain modification from the 
applicability. This AD was prompted by a determination that certain 
repetitive inspection intervals need to be revised. The FAA is issuing 
this AD to address the unsafe condition on these products.

DATES: This AD is effective January 5, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 5, 
2024.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2023-1409; 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:
     For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile 
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 
96; fax +33 5 61 93 44 51; email airbus.com">account.airworth-eas@airbus.com; 
website airbus.com.
     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. It is also available at 
regulations.gov under Docket No. FAA-2023-1409.

FOR FURTHER INFORMATION CONTACT: Timothy Dowling, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
telephone 206-231-3667; email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2019-07-05, Amendment 39-19616 (84 FR 
16386, April 19, 2019; corrected May 10, 2019 (84 FR 20542)) (AD 2019-
07-05). AD 2019-07-05 applied to all 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 2019-07-05 required repetitive inspections for 
cracking of the 10VU rack fitting lugs, and repair of any cracking. The 
FAA issued AD 2019-07-05 to address reading difficulties of flight-
critical information displayed to the flightcrew during a critical 
phase of flight, such as an approach or takeoff, which could result in 
loss of airplane control at an altitude insufficient for recovery.
    The NPRM published in the Federal Register on July 13, 2023 (88 FR 
44740). The NPRM was prompted by AD 2022-0266, dated December 22, 2022, 
issued by the European Union Aviation Safety Agency (EASA), which is 
the Technical Agent for the Member States of the European Union (EASA 
AD 2022-0266) (also referred to as the MCAI). The MCAI states that 
during an unscheduled maintenance operation on an A330 airplane, the 
10VU rack was removed for access, and cracks were discovered on 10VU 
rack side fittings on lugs 1, 3, and 4. As a similar design is 
installed on A320 family airplanes, a sampling review was done to 
determine the possible fleet impact. The result showed that several 
airplanes had cracked or broken 10VU rack side fittings. This 
condition, if not detected and corrected, could lead to a high 
vibration level on the primary flight and navigation displays during 
critical flight phases (take-off and landing), possibly creating 
reading difficulties for the crew.
    In the NPRM, the FAA proposed to continue to require repetitive 
inspections for cracking of the 10VU rack fitting lugs, and repair of 
any cracking. In the NPRM, the FAA also proposed to require reduced 
compliance times and to remove airplanes having a certain modification 
from the applicability. The FAA is issuing this AD to address reading 
difficulties of flight-critical information displayed to the flightcrew 
during a critical phase of flight, such as an approach or takeoff, 
which could result in loss of airplane control at an altitude 
insufficient for recovery.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2023-1409.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from Air Line Pilots Association, 
International (ALPA), who supported the NPRM without change.
    The FAA received additional comments from United Airlines (United). 
The following presents United's comments received on the NPRM and the 
FAA's response to each comment.

[[Page 83814]]

Request To Revise Compliance Time

    United requested revising the proposed AD to add a grace period for 
the reduced compliance times of the repetitive inspections. United 
stated that it accomplished the initial inspections on most of the 
fleet and already scheduled the repetitive inspections within the 
20,000-flight-cycle or 40,000-flight-hour interval specified in AD 
2019-07-05. United pointed out that the repetitive interval is reduced 
to 10,000 flight cycles or 20,000 flight hours in the proposed AD. 
United suggested a grace period of 20,000 flight cycles or 40,000 
flight hours for the first repeat inspection and then 10,000 flight 
cycles or 20,000 flight hours for the following repeat inspections.
    The FAA does not agree with the commenter's request to provide a 
grace period. In developing an appropriate compliance time for this 
action, the FAA considered the recommendations of the manufacturer and 
EASA, the urgency associated with the subject unsafe condition, the 
availability of required parts, and the practical aspect of 
accomplishing the required repair within a period of time that 
corresponds to the normal scheduled maintenance for most affected 
operators. The compliance times are not expected to ground any 
airplanes upon the effective date of this AD. United has not provided 
data for the FAA to consider. However, under the provisions of 
paragraph (l)(1) of this AD, the FAA will consider requests for 
approval of an extension of the compliance time if sufficient data are 
submitted to substantiate that the new compliance time would provide an 
acceptable level of safety. The FAA has not changed this AD in this 
regard.

Request To Allow Flight With Known Cracking

    United requested that the FAA revise the proposed AD to align more 
closely with EASA AD 2022-0266; Airbus Service Bulletin A320-92-1087, 
Revision 04, dated May 16, 2022; and Airbus Service Bulletin A320-92-
1119, Revision 02, dated May 16, 2022. United stated that these 
documents allow further flights up to 5,000 flight cycles, 10,000 
flight hours, or 24 months, whichever occurs first, after any finding 
of cracking on a single 10VU lug. The proposed AD would require repair 
before further flight for any number of lugs found to have cracking.
    The FAA generally does not allow flights with known cracking. 
Therefore, the FAA requires repairing known cracks before further 
flight (although the FAA might make exceptions in certain cases of 
unusual need, as discussed below). This is based on the fact that such 
damaged airplanes do not conform to the FAA-certificated type design 
and, therefore, are not airworthy until a properly approved repair is 
made. While the FAA recognizes that repair deferrals might be necessary 
at times, the FAA intends to minimize adverse human factors relating to 
the lack of reliability of long-term repetitive inspections, which 
might reduce the safety of the type-certificated design if such repair 
deferrals are practiced routinely.
    As noted above, the FAA might allow an exception to these 
requirements in certain cases, if there is an unusual need for a 
temporary deferral and if the temporary fix will maintain an adequate 
level of safety. Unusual needs include such circumstances as legitimate 
difficulty in acquiring parts to accomplish repairs. Under such 
conditions, the FAA might allow a temporary deferral of the repair, 
subject to a stringent inspection program acceptable to the FAA. The 
FAA acknowledges that the manufacturer has specified inspection 
intervals that are intended to allow continued operation with known 
cracks, and to prevent the need for extensive repairs. However, since 
the FAA is not aware of any unusual need for repair deferral in regard 
to this AD, the FAA has not evaluated these inspection intervals.
    The FAA considers the compliance times in this AD to be adequate to 
allow operators to acquire parts to have on hand in the event that a 
crack is detected during inspection. Therefore, the FAA has determined 
that, due to the safety implications and consequences associated with 
such cracking, any 10VU lug that is found to be cracked must be 
repaired or modified before further flight. The FAA has not changed 
this AD in this regard.

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, 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

    The FAA reviewed Airbus Service Bulletins A320-92-1087, Revision 
04, dated May 16, 2022; and A320-92-1119, Revision 02, dated May 16, 
2022. This service information specifies procedures for repetitive 
inspections for cracking of the 10VU rack fitting lugs, and repair of 
any cracking. These documents are distinct since they apply to 
different airplane configurations. This service information 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 461 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
----------------------------------------------------------------------------------------------------------------
Inspections (retained actions from AD   2 work-hours x $85 per                $0            $170         $78,370
 2019-07-05).                            hour = $170.
----------------------------------------------------------------------------------------------------------------

    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 $85 
per product.
    The FAA estimates the following costs to do any necessary repairs 
that would be required based on the results of the inspection. The FAA 
has no way of determining the number of aircraft that might need these 
repairs:

[[Page 83815]]



                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
83 work-hours x $85 per hour = $7,055.          $9,140          $16,195
------------------------------------------------------------------------

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

    The FAA determined that 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) 2019-07-05, Amendment 39-19616 
(84 FR 16386, April 19, 2019; corrected May 10, 2019 (84 FR 20542)); 
and
0
b. Adding the following new AD:

2023-23-08 Airbus SAS: Amendment 39-22610; Docket No. FAA-2023-1409; 
Project Identifier MCAI-2022-01645-T.

(a) Effective Date

    This airworthiness directive (AD) is effective January 5, 2024.

(b) Affected ADs

    This AD replaces AD 2019-07-05, Amendment 39-19616 (84 FR 16386, 
April 19, 2019; corrected May 10, 2019 (84 FR 20542)) (AD 2019-07-
05).

(c) Applicability

    This AD applies to the Airbus SAS airplanes identified in 
paragraphs (c)(1) through (4) of this AD, certificated in any 
category, all manufacturer serial numbers, except those on which 
Airbus modification 157335 has been embodied in production.
    (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 92, Electric and 
electronic common installation.

(e) Unsafe Condition

    This AD was prompted by a report of cracks found during 
maintenance inspections on certain 10VU rack fitting lugs, and a 
determination that certain compliance times need to be revised. The 
FAA is issuing this AD to address reading difficulties of flight-
critical information displayed to the flightcrew during a critical 
phase of flight, such as an approach or takeoff, which could result 
in loss of airplane control at an altitude insufficient for 
recovery.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Definitions, With No Changes

    This paragraph restates the definitions of paragraph (g) of AD 
2019-07-05, with no changes. For the purpose of this AD, Group 1 
airplanes are in a pre-Airbus Modification 35869 configuration, and 
Group 2 airplanes are in a post-Airbus Modification 35869 
configuration.

(h) Retained Repetitive Inspections, With Reduced Inspection Intervals 
and Revised Service Information

    This paragraph restates the requirements of paragraph (h) of AD 
2019-07-05, with reduced inspection intervals and revised service 
information.
    (1) For Group 1 airplanes: At the later of the times specified 
in Figure 1 to paragraph (h)(1) of this AD, do a detailed inspection 
for cracking of the 10VU rack fitting lugs, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-92-1087, 
Revision 04, dated May 16, 2022. Repeat the inspection thereafter at 
intervals not to exceed 10,000 flight cycles or 20,000 flight hours, 
whichever occurs first.

Figure 1 to Paragraph (h)(1)--Initial Inspection Compliance Time for 
Group 1 Airplanes

[[Page 83816]]

[GRAPHIC] [TIFF OMITTED] TR01DE23.000

    (2) For Group 2 airplanes: At the later of the times specified 
in Figure 2 to paragraph (h)(2) of this AD, do a detailed inspection 
for cracking of the 10VU rack fitting lugs, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-92-1119, 
Revision 02, dated May 16, 2022. Repeat the inspection thereafter at 
intervals not to exceed 10,000 flight cycles or 20,000 flight hours, 
whichever occurs first.

Figure 2 to Paragraph (h)(2)--Initial Inspection Compliance Time for 
Group 2 Airplanes
[GRAPHIC] [TIFF OMITTED] TR01DE23.001

(i) Retained Repair, With Revised Service Information

    This paragraph restates the requirements of paragraph (i) of AD 
2019-07-05, with revised service information. If any crack is found 
during any inspection required by paragraph (h)(1) or (2) of this 
AD: Before further flight, do a repair in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-92-1087, 
Revision 04, dated May 16, 2022 (for Group 1 airplanes); or Airbus 
Service Bulletin A320-92-1119, Revision 02, dated May 16, 2022 (for 
Group 2 airplanes); as applicable. Repair of a 10VU rack fitting lug 
does not terminate the repetitive inspections required by paragraphs 
(h)(1) and (2) of this AD.

(j) Reporting Requirement

    At the applicable time specified in paragraph (j)(1) or (2) of 
this AD: Submit a report of findings (positive and negative) of each 
inspection required by paragraph (h) of this AD to Airbus Service 
Bulletin Reporting Online Application on Airbus World (airbus.com) 
or in accordance with B. ``Reporting Sheet'' of the Appendix of 
Airbus Service Bulletin A320-92-1087, Revision 04, dated May 16, 
2022 (for Group 1 airplanes); or Airbus Service Bulletin A320-92-
1119, Revision 02, dated May 16, 2022 (for Group 2 airplanes); as 
applicable.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 90 days after the inspection.
    (2) 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.

(k) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (h)(1) and (i) of this AD, if those actions were 
performed before May 24, 2019 (the effective date of AD 2019-07-05), 
using Airbus Service Bulletin A320-92-1087, dated March 28, 2011, 
which is not incorporated by reference in this AD; or Airbus Service 
Bulletin A320-92-1087, Revision 01, dated May 17, 2011, which is not 
incorporated by reference in this AD; or Airbus Service Bulletin 
A320-92-1087, Revision 02, dated November 25, 2014, which was 
incorporated by reference in AD 2016-19-14.
    (2) This paragraph provides credit for actions required by 
paragraphs (h)(1) and (i) of this AD, if those actions were 
performed before the effective date of this AD, using Airbus Service 
Bulletin A320-92-1087, Revision 03, dated July 31, 2017, which was 
incorporated by reference in AD 2019-07-05.
    (3) This paragraph provides credit for actions required by 
paragraphs (h)(2) and (i) of this AD, if those actions were 
performed before the effective date of this AD, using Airbus Service 
Bulletin A320-92-1119, dated July 28, 2017, which was incorporated 
by reference in AD 2019-07-05; or Airbus Service Bulletin A320-92-
1119, Revision 01, dated August 5, 2019, which is not incorporated 
by reference in this AD.
    (4) This paragraph provides credit for the reporting required by 
paragraph (j)(2) of this AD, if that action was performed before the 
effective date of this AD in accordance with the instructions of 
Airbus Service Bulletin A320A-92-1087, Revision 03, dated July 31, 
2017 (for Group 1 airplanes); or Airbus Service Bulletin A320-92-
1119, dated July 28, 2017 (for Group 2 airplanes); as applicable; 
except where Figure A-FAAAA, Sheet 02, of Appendix 01, ``Inspection 
Report,'' of Airbus Service Bulletin A320-92-1087, Revision 03, 
dated July 31, 2017; and Figure A-FAAAA, Sheet 02, of Appendix 01, 
``Inspection Report,'' of Airbus Service Bulletin A320-92-1119, 
dated July 28, 2017; specifies sending removed lugs to Airbus for 
investigation, that action is not required by this AD. Airbus 
Service Bulletin

[[Page 83817]]

A320A-92-1087, Revision 03, dated July 31, 2017; and Airbus Service 
Bulletin A320-92-1119, dated July 28, 2017; were incorporated by 
reference in AD 2019-07-05.

(l) Additional AD Provisions

    (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 manager of the 
International Validation Branch, mail it to the address identified 
in paragraph (m)(2) of this AD or email to: [email protected]. If mailing information, also submit information by 
email.
    (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) Global AMOC AIR-676-19-305, dated July 29, 2019, approved 
as an AMOC for AD 2019-07-05, is approved as an AMOC for the 
corresponding provisions 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 the European Union Aviation Safety Agency 
(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 (l)(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.

(m) Additional Information

    (1) Refer to European Union Aviation Safety Agency (EASA) AD 
2022-0266, dated December 22, 2022, for related information. This 
EASA AD may be found in the AD docket at regulations.gov under 
Docket No. FAA-2023-1409.
    (2) For more information about this AD, contact Timothy Dowling, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone 206-231-3667; email 
[email protected].
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(3) and (4) of this AD.

(n) 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) Airbus Service Bulletin A320-92-1087, Revision 04, dated May 
16, 2022.
    (ii) Airbus Service Bulletin A320-92-1119, Revision 02, dated 
May 16, 2022.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email airbus.com">account.airworth-eas@airbus.com; website 
airbus.com.
    (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 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].

    Issued on November 16, 2023.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2023-26404 Filed 11-30-23; 8:45 am]
BILLING CODE 4910-13-P