Rule2022-26357
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 5, 2022
Effective
January 9, 2023
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report that damage (including delamination of the work deck, and corroded and cracked retainer blocks) was found during inspection of certain galleys. This AD requires repetitive inspections of certain galleys for corrosion of trolley retainer aluminum blocks and delamination of the upper panel of the trolley compartment, and applicable corrective action, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 87 Issue 232 (Monday, December 5, 2022)</title>
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[Federal Register Volume 87, Number 232 (Monday, December 5, 2022)]
[Rules and Regulations]
[Pages 74291-74294]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-26357]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0463; Project Identifier MCAI-2021-00895-T;
Amendment 39-22245; AD 2022-24-05]
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 A318, A319, A320, and A321 series airplanes. This AD
was prompted by a report that damage (including delamination of the
work deck, and corroded and cracked retainer blocks) was found during
inspection of certain galleys. This AD requires repetitive inspections
of certain galleys for corrosion of trolley retainer aluminum blocks
and delamination of the upper panel of the trolley compartment, and
applicable corrective action, as specified in a European Union Aviation
Safety Agency (EASA) AD, which is incorporated by reference. This AD
also limits the installation of affected parts under certain
conditions. The FAA is issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective January 9, 2023.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 9,
2023.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2022-0463; 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 (IBR) 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#48090c3b082d293b29662d3d3a273829662d3d"><span class="__cf_email__" data-cfemail="edaca99ead888c9e8cc388989f829d8cc38898">[email protected]</span></a>; website easa.europa.eu. You
may find this IBR 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-2022-0463.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
Large Aircraft Section, FAA, International Validation Branch, 2200
South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3229;
email <a href="/cdn-cgi/l/email-protection#bdcbd1dcd9d4d0d4cf93c8d1c4dcd3d2cbfddbdcdc93dad2cb"><span class="__cf_email__" data-cfemail="6f19030e0b0602061d411a03160e0100192f090e0e41080019">[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
A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -
114, -115, -131, -132, -133, -151N, -153N, and -171N airplanes; Model
A320-211, -212, -214, -215, -216, -231, -232, -233, -251N, -252N, -
253N, -271N, -272N, and -273N airplanes; and Model A321-111, -112, -
131, -211, -212, -213, -231, -232, -251N, -251NX, -252N, -252NX, -253N,
-253NX, -271N, -271NX, -272N, and -272NX airplanes. The NPRM published
in the Federal Register on April 18, 2022 (87 FR 22818). The NPRM was
prompted by AD 2021-0183R1, dated September 20, 2021, issued by the
European Union Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union (referred to after
this as the MCAI). The MCAI states that damage (including delamination
of the work deck, and corroded and cracked retainer blocks) was found
during inspection of certain galleys. The FAA is proposing this AD to
detect and correct damage that could affect the galley's capability to
hold the trolley under emergency landing loads, which could lead to
trolley detachment, possibly resulting in blocking of an escape path
during an emergency exit.
In the NPRM, the FAA proposed to require repetitive inspections of
certain galleys for corrosion of trolley retainer aluminum blocks and
delamination of the upper panel of the trolley compartment, and
applicable corrective action, as specified in EASA AD 2021-0183R1. The
NPRM also proposed to limit the installation of affected parts under
certain conditions. The FAA is issuing this AD to address the unsafe
condition on these products.
[[Page 74292]]
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2022-0463.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from two commenters, including American
Airlines (AAL) and Delta Air Lines (DAL). The following presents the
comments received on the NPRM and the FAA's response to each comment.
Request for Improved Repair Instructions
AAL requested that the FAA coordinate with Safran, Airbus, and/or
EASA to discuss a repair solution more appropriate than the repair
specified in the service information referenced in the MCAI, perhaps
one that would replace a section of the entire work deck that
encompasses all of the trolley blocks with a pre-fabricated composite
and less-corrosive work deck section. AAL considered the intervals, and
in particular, the repair methods to be ill-conceived. AAL explained
that the repair is impractical and overly invasive and does not take
into consideration details of the bonded structure such as potted
inserts, cutouts for pivoting T-dividers, and adjacent structural
elements such as the stabbing assembly which is often destroyed or
damaged during a disbond process. AAL also explained that, among other
things, applying heat to bonded parts to facilitate their removal is
overly optimistic (as a solution to address the unsafe condition) and
causes damage that can lead to other unsafe conditions. AAL expressed
concerns that the scope of damage could lead to additional approvals
that would be overwhelming to the FAA, AAL, Safran, and Airbus.
Therefore, AAL asked the FAA to consider a more comprehensive repair
approach in lieu of incorporating by reference EASA AD 2021-0183R1. AAL
proposed a repair that would involve trimming and replacing a section
of the entire work deck that encompasses all of the trolley blocks. The
FAA does not agree. The FAA has not received revised service
information that would address AAL's concerns and waiting for revised
service information would delay the actions required to address the
specified unsafe condition. In addition, EASA's response to a similar
comment in the associated EASA proposed AD (PAD) explains that it is in
the interest of safety to start the inspection campaign with the
available instructions, rather than delaying that, pending the
development and approval of a new repair. As stated in the NPRM, this
AD action has been identified as interim action pending the potential
development of a final action. However, under the provisions of
paragraph (j)(1) of this AD, the FAA will consider requests for
approval of an alternative method of compliance (AMOC) if sufficient
data are submitted to substantiate that the method would provide an
acceptable level of safety. The FAA has not changed this AD in this
regard.
Request for Revised Cost Estimate
AAL requested the proposed AD be revised to include repair cost
estimations in the on-condition cost estimate. AAL stated that its
prior operational experience shows that an operator should expect an
average workscope greater than an inspection, likely including retainer
block replacement.
The FAA agrees to revise the cost estimate for on-condition
actions. The estimate has been revised to include a worst-case scenario
of 40 work-hours per airplane for the intermediate repair of replacing
all retaining blocks.
Request for Delay of AD Issuance
DAL requested delaying AD issuance until new or revised service
information is published. DAL stated that the next revisions of the
service information referenced in EASA AD 2021-0183R1 would contain the
following corrections and add-ons: a final fix for Galley G2A, G4x, and
G5; revision of the ``Quick Fix'' adhesive reference from DP100FR to
DP100; and the addition of a missing figure in the instructions for
installing doublers when doing the panel skin restoration.
The FAA disagrees. Although a later revision was issued, the later
revision did not include updated instructions for the galleys. The FAA
does not consider that delaying this action for the final fix is
warranted since sufficient service information currently exists to
address the unsafe condition until the final fix is identified and
published. As stated previously, the FAA might consider further
rulemaking once a final action is developed, approved, and available.
However, under the provisions of paragraph (j)(1) of this AD, the FAA
will consider requests for an AMOC if such final action is submitted.
The FAA has not changed this AD in this regard.
Requests To Extend Compliance Time
DAL requested extending the initial inspection grace period from 12
months after the effective date of the AD to 24 months. DAL stated that
during conversations with Airbus, DAL was not provided with a definite
answer on whether sufficient parts or materials would be available to
support repairs within a 12-month timeline. AAL also expressed concerns
about obtaining replacement parts from Safran in a timely manner.
The FAA disagrees to extend this compliance time. The FAA
considered the recommendations of EASA and the manufacturer, the
availability of parts and the safety implications, and determined that
the 12-month grace period, as proposed, will provide an adequate level
of safety. However, under the provisions of paragraph (j)(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 extension would provide an acceptable level of safety. The FAA has
not changed this AD in this regard.
Request To Address Damage Found During Post-Repair Inspection
DAL requested that the proposed AD be revised to specify the
follow-on corrective action necessary to address damage found during
inspections done after an ``Intermediate Fix'' was accomplished. DAL
noted that after an ``Intermediate Fix'' has been accomplished, the
service information states that the next inspection may be postponed up
to 36 months after the repair action, but if that inspection has
findings of damage, no repair instructions are specified.
The FAA agrees that no repair instructions are specified for
findings of damage. Since no repair instructions are specified, the FAA
has added paragraph (h)(4) of this AD to specify contacting EASA, the
FAA, or Airbus's SAS EASA Design Organization Approval (DOA) for
approval of repair instructions.
Request To Address Existing Repairs on Inspection Area
DAL requested that the FAA add an exception in paragraph (h) of the
proposed AD that addresses a related plan of action, explains whether
an AMOC is required for existing repairs in the inspection area, or
states that existing repairs that are permanent terminate the
repetitive inspection.
The FAA agrees to clarify. AMOCs provide an alternative method of
compliance to the methods required to be used in the associated AD. An
AMOC is issued only after an AD has been issued and only after data are
provided to show that the proposed solution is complete and addresses
the unsafe condition. However, once this AD is published, any person
may request approval of an AMOC under the
[[Page 74293]]
provisions of paragraph (j)(1) of this AD. Operators with an existing
repair in the inspection area may submit information on the repair for
consideration as a possible terminating action. 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, 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 2021-0183R1 specifies procedures for repetitive general
visual inspections of certain galleys for discrepancies including
corrosion of trolley retainer aluminum blocks and delamination of upper
panel of trolley compartment, and corrective action. Corrective actions
include repeating the inspection at an earlier interval, repairing the
trolley compartment upper panel, and limiting trolley weight. 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.
Interim Action
The FAA considers that this AD is an interim action. If final
action is later identified, the FAA might consider further rulemaking
then.
Costs of Compliance
The FAA estimates that this AD affects 1,425 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product Cost on U.S. operators
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2 work-hours x $85 per hour = $170 per $0 $170 per inspection cycle. $242,250 per inspection
galley, per inspection cycle. cycle.
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The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any
required actions. The FAA has no way of determining the number of
aircraft that might need these on-condition actions:
Estimated Costs of On-Condition Actions
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Cost per
Labor cost Parts cost product
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40 work-hours x $85 per hour = Minimal.............. $3,400
$3,400.
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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 adding the following new airworthiness
directive:
2022-24-05 Airbus SAS: Amendment 39-22245; Docket No. FAA-2022-0463;
Project Identifier MCAI-2021-00895-T.
(a) Effective Date
This airworthiness directive (AD) is effective January 9, 2023.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus SAS Model airplanes identified in
paragraphs (c)(1) through (4) of this AD, certificated in any
category.
(1) Model A318-111, -112, -121, and -122 airplanes.
[[Page 74294]]
(2) Model A319-111, -112, -113, -114, -115, -131, -132, -133, -
151N, -153N, and -171N airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -
252N, -253N, -271N, -272N, and -273N airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, -232, -
251N, -251NX, -252N, -252NX, -253N, -253NX, -271N, -271NX, -272N,
and -272NX airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 25, Equipment/
Furnishings.
(e) Unsafe Condition
This AD was prompted by a report that damage (including
delamination of work deck, and corroded and cracked retainer blocks)
was found during inspection of certain galleys. The FAA is issuing
this AD to detect and correct damage that could affect the galley's
capability to hold the trolley under emergency landing loads, which
could lead to trolley detachment, possibly resulting in blocking of
an escape path during an emergency exit.
(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
2021-0183R1, dated September 20, 2021 (EASA AD 2021-0183R1).
(h) Exceptions to EASA AD 2021-0183R1
(1) Where EASA AD 2021-0183R1 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where EASA AD 2021-0183R1 refers to ``18 August 2021,'' this
AD requires using the effective date of this AD.
(3) The ``Remarks'' section of EASA AD 2021-0183R1 does not
apply to this AD.
(4) Where EASA AD 2021-0183R1 does not specify corrective action
after a post-repair inspection that has findings of damage, this AD
requires obtaining repair instructions before further flight from
the FAA, EASA, or Airbus SAS's EASA Design Organization Approval
(DOA) and accomplishing those actions accordingly. If approved by
the DOA, the approval must include the DOA-authorized signature.
(i) No Reporting Requirement
Although the service information referenced in EASA AD 2021-
0183R1 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 manager,
International Validation Branch, mail it to the address identified
in paragraph (k) of this AD or email to: <a href="/cdn-cgi/l/email-protection#10293d5146433d5159423d2723203d515d5f53507671713e777f66"><span class="__cf_email__" data-cfemail="97aebad6c1c4bad6dec5baa0a4a7bad6dad8d4d7f1f6f6b9f0f8e1">[email protected]</span></a>.
If mailing information, also submit information by email. 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
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 Vladimir Ulyanov,
Aerospace Engineer, Large Aircraft Section, FAA, International
Validation Branch, 2200 South 216th St., Des Moines, WA 98198;
telephone and fax 206-231-3229; email <a href="/cdn-cgi/l/email-protection#6e18020f0a0703071c401b02170f0001182e080f0f40090118"><span class="__cf_email__" data-cfemail="8bfde7eaefe2e6e2f9a5fee7f2eae5e4fdcbedeaeaa5ece4fd">[email protected]</span></a>.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference 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 2021-0183R1,
dated September 20, 2021.
(ii) [Reserved]
(3) For EASA AD 2021-0183R1, contact EASA, Konrad-Adenauer-Ufer
3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#7534310635101406145b1000071a05145b1000"><span class="__cf_email__" data-cfemail="b7f6f3c4f7d2d6c4d699d2c2c5d8c7d699d2c2">[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 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#6204104c0b0c11120701160b0d0c220c0310034c050d14"><span class="__cf_email__" data-cfemail="bfd9cd91d6d1cccfdadccbd6d0d1ffd1decdde91d8d0c9">[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 November 9, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-26357 Filed 12-2-22; 8:45 am]
BILLING CODE 4910-13-P
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