Airworthiness Directives; Airbus SAS Airplanes

[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 [www.gpo.gov]
[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 regulations.gov 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 [email protected]; 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 
regulations.gov 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 [email protected].

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 regulations.gov 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
----------------------------------------------------------------------------------------------------------------
2 work-hours x $85 per hour = $170 per                 $0  $170 per inspection cycle.  $242,250 per inspection
 galley, per inspection cycle.                                                          cycle.
----------------------------------------------------------------------------------------------------------------

    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
------------------------------------------------------------------------
                                                             Cost per
            Labor cost                   Parts cost           product
------------------------------------------------------------------------
40 work-hours x $85 per hour =     Minimal..............          $3,400
 $3,400.
------------------------------------------------------------------------

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: [email protected]. 
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 [email protected].

(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 
[email protected]; 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 
[email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    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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