Rule2022-25509
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
November 25, 2022
Effective
December 30, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2018-03- 12, 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, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2018-03-12 required repetitive rototest inspections for cracking of the fastener holes in certain door stop fittings, and repair if necessary. This AD was prompted by new analysis by the manufacturer that resulted in optimized compliance times for the inspections. This AD continues to require repetitive rototest inspections for cracking of the fastener holes in certain door stop fittings at revised compliance times, and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 87 Issue 226 (Friday, November 25, 2022)</title>
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[Federal Register Volume 87, Number 226 (Friday, November 25, 2022)]
[Rules and Regulations]
[Pages 72369-72372]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-25509]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0503; Project Identifier MCAI-2021-01244-T;
Amendment 39-22219; AD 2022-22-04]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-03-
12, 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, -231, -232, and -233 airplanes; and Model
A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD
2018-03-12 required repetitive rototest inspections for cracking of the
fastener holes in certain door stop fittings, and repair if necessary.
This AD was prompted by new analysis by the manufacturer that resulted
in optimized compliance times for the inspections. This AD continues to
require repetitive rototest inspections for cracking of the fastener
holes in certain door stop fittings at revised compliance times, and
corrective actions if necessary, as specified in a European Union
Aviation Safety Agency (EASA) AD, which is incorporated by reference.
The FAA is issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective December 30, 2022.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 30,
2022.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2022-0503; 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#47060334072226342669223235283726692232"><span class="__cf_email__" data-cfemail="b6f7f2c5f6d3d7c5d798d3c3c4d9c6d798d3c3">[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-2022-0503.
FOR FURTHER INFORMATION CONTACT: Hye Yoon Jang, Aerospace Engineer,
Large Aircraft Section, FAA, International Validation Branch, 2200
South 216th St., Des Moines, WA 98198; telephone 817-222-5584; email
<a href="/cdn-cgi/l/email-protection#deb6a7bbf0a7b1b1b0f0b4bfb0b99eb8bfbff0b9b1a8"><span class="__cf_email__" data-cfemail="4921302c6730262627672328272e092f2828672e263f">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2021-0242, dated November 8, 2021
(EASA AD 2021-0242) (also referred to as the MCAI), to correct an
unsafe condition for certain Airbus SAS Model A318 series airplanes;
Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes;
Model A320-211, -212, -214, -215, -216, -231, -232, and -233 airplanes;
and Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes. Model A320-215 airplanes are not certificated by the FAA and
are not included on the U.S. type certificate data sheet; this AD
therefore does not include those airplanes in the applicability.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2018-03-12, Amendment 39-19185 (83 FR 5906,
February 12, 2018) (AD 2018-03-12). AD 2018-03-12 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,
-231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211,
[[Page 72370]]
-212, -213, -231, and -232 airplanes. The NPRM published in the Federal
Register on May 6, 2022 (87 FR 27032). The NPRM was prompted by reports
of fatigue damage in the structure for the door stop fittings on
certain fuselage frames, and new analysis by the manufacturer, which
resulted in optimized compliance times for the inspections. The NPRM
proposed to continue to require repetitive rototest inspections for
cracking of the fastener holes in certain door stop fittings at revised
compliance times, and corrective actions if necessary, as specified in
EASA AD 2021-0242.
The FAA is issuing this AD to address cracking at the door stop
fitting holes of fuselage frame (FR) 66 and FR68 which could result in
reduced structural integrity of the airplane. See the MCAI for
additional background information.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from one commenter, Delta Air Lines, Inc.
(DAL). The following presents the comments received on the NPRM and the
FAA's response to each comment.
Request To Revise Exception Language
DAL requested that the language in paragraph (h)(3) of the proposed
AD be revised to clearly state that the manufacturer must be contacted
only ``when cracking exceeds the limits from the applicable SRM
[structural repair manual]'' as opposed to ``if any crack is found
during any inspection'' as stated in the NPRM. DAL pointed out that
paragraph (2) of EASA AD 2021-0242 establishes requirements if a crack
is detected and identified within the limit defined in the applicable
SRM, and paragraph (3) of EASA AD 2021-0242 establishes corrective
action requirements when cracking exceeds the limits from the
applicable SRM. DAL emphasized that paragraph (h)(3) of the proposed
rule does not make that distinction and that the exception specifies
that any cracking found must be repaired before further flight. Because
of this omission and the use of the verbiage ``if any crack is found
during any inspection,'' DAL reasoned that paragraph (h)(3) of the
proposed AD indicates that it applies to all instances of cracking,
regardless of whether it exceeds SRM limits. DAL suggested that the
exception paragraph would drive operators to obtain the specified level
of approval for all crack findings from the required inspections, even
if there are SRM approved repairs that are addressed by paragraph (2)
of EASA AD 2021-0242.
The FAA agrees to clarify. Paragraph (h)(3) of this AD is included
to ensure that any cracks are repaired before further flight, and
applies only to the cracks specified in paragraph (3) of EASA AD 2021-
0242 (i.e., those found during the rototest inspections and exceeding
the applicable SRM limit). Paragraph (3) of EASA AD 2021-0242 specifies
to contact Airbus for instructions before further fight, but does not
specify that the repair must be done before further flight. Since FAA
policy does not allow flights with known cracks, an exception is needed
to clarify the compliance time. The FAA notes that paragraph (2) of
EASA AD 2021-0242 specifies accomplishing repair and corrective actions
before further flight, so a similar exception is not needed for that
action. However, the FAA agrees that clarification related to which
cracks the language in paragraph (h)(3) of this AD applies to would be
helpful. Therefore, the FAA has revised paragraph (h)(3) of this AD to
specify that the actions are required only for cracks that exceed the
applicable SRM limits.
Request To Include a New Exception
DAL requested that the FAA include an additional exception to the
proposed AD that clarifies the ``contact Airbus'' language in
paragraphs (5.2) and (6) of EASA AD 2021-0242. DAL noted that
paragraphs (5.2) and (6) of EASA AD 2021-0242 require contacting
Airbus, and reasoned that an exception similar to that in paragraph
(h)(3) of the proposed AD would be needed. DAL pointed out that the
language used in paragraphs (5.2) and (6) of EASA AD 2021-0242 is
related to providing credit for actions that have been accomplished,
rather than providing a corrective action like in paragraph (3) of EASA
AD 2021-0242, so different language would be needed. DAL provided
suggested wording, and stated that its proposed exception would ensure
that the same actions are mandated at all instances where EASA AD 2021-
0242 requires contacting the manufacturer.
The FAA agrees to clarify. Paragraph (j)(2) of this AD already
specifies what actions to take in instances where the EASA AD or
related service information specifies to contact the manufacturer. As
explained previously, paragraph (h)(3) of this AD is needed to clarify
the compliance time for crack repair, rather than simply clarifying who
to contact for instructions. Therefore, an additional exception is not
needed and this AD has not been changed regarding this issue.
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
comment 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 2021-0242 specifies procedures for rototest inspections for
cracking of the fastener holes in the airframe structure for the door
stop fittings installation in FR66 and FR68, and corrective actions.
Corrective actions include repair or modification of fastener holes at
door stop locations. 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 1,084 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspections................ Up to 25 work-hours x $0 Up to $2,125......... Up to $2,303,500.
$85 per hour =
$2,125.
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[[Page 72371]]
The FAA estimates the following costs to do any necessary on-
condition modifications 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 modifications:
Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
Labor cost Parts cost Cost per product
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Up to 27 work-hours x $85 per $610 Up to $2,905.
hour = $2,295.
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The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
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) AD 2018-03-12, Amendment 39-
19185 (83 FR 5906, February 12, 2018) (AD 2018-03-12); and
0
b. Adding the following new AD:
2022-22-04 Airbus SAS: Amendment 39-22219; Docket No. FAA-2022-0503;
Project Identifier MCAI-2021-01244-T.
(a) Effective Date
This airworthiness directive (AD) is effective December 30,
2022.
(b) Affected ADs
This AD replaces AD 2018-03-12, Amendment 39-19185 (83 FR 5906,
February 12, 2018) (AD 2018-03-12).
(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 2021-0242, dated November 8, 2021 (EASA AD 2021-0242).
(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) Reason
This AD was prompted by reports of fatigue damage in the
structure for the door stop fittings on certain fuselage frames, and
new analysis by the manufacturer, which resulted in optimized
compliance times for the inspections. The FAA is issuing this AD to
address cracking at the door stop fitting holes of fuselage frame
(FR) 66 and FR68, which could result in reduced 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 2021-0242.
(h) Exceptions to EASA AD 2021-0242
(1) Where EASA AD 2021-0242 refers to its effective date, this
AD requires using the effective date of this AD.
(2) The ``Remarks'' section of EASA AD 2021-0242 does not apply
to this AD.
(3) Where paragraph (3) of EASA AD 2021-0242 specifies ``if,
during any inspection as required by paragraph (1) of this [EASA]
AD, a crack is detected and identified exceeding the limit defined
in the applicable SRM [structural repair manual]'' to ``contact
Airbus for approved instructions for corrective action and
accomplish those instructions accordingly,'' replace those phrases
with the following phrase: ``if any cracking is found and exceeding
the limit defined in the applicable SRM, the cracking must be
repaired before further flight using a method approved by the
Manager, Large Aircraft Section, 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.''
(4) Where paragraphs (2), (3), (5), and (5.1) of EASA AD 2021-
0242 specify limits or actions in ``the applicable SRM'' or ``the
SRM,'' for purposes of this AD, replace those phrases with the
following phrase: ``the applicable SRM as specified in the
instructions of the inspection SB.''
(i) No Reporting Requirement
Although the service information referenced in EASA AD 2021-0242
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
[[Page 72372]]
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#01382c4057522c4048532c3632312c404c4e42416760602f666e77"><span class="__cf_email__" data-cfemail="132a3e5245403e525a413e2420233e525e5c50537572723d747c65">[email protected]</span></a>.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(ii) AMOCs approved previously for AD 2018-03-12 are approved as
AMOCs for the corresponding provisions of EASA AD 2021-0242 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, Large Aircraft
Section, 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) Related Information
For more information about this AD, contact Hye Yoon Jang,
Aerospace Engineer, Large Aircraft Section, FAA, International
Validation Branch, 2200 South 216th St., Des Moines, WA 98198;
telephone 817-222-5584; email <a href="/cdn-cgi/l/email-protection#5931203c7720363637773338373e193f3838773e362f"><span class="__cf_email__" data-cfemail="3f57465a114650505111555e51587f595e5e11585049">[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 2021-0242,
dated November 8, 2021.
(ii) [Reserved]
(3) For EASA AD 2021-0242, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#f1b0b582b194908290df9484839e8190df9484"><span class="__cf_email__" data-cfemail="5b1a1f281b3e3a283a753e2e29342b3a753e2e">[email protected]</span></a>; internet 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#e78195c98e8994978284938e8889a789869586c9808891"><span class="__cf_email__" data-cfemail="ef899dc186819c9f8a8c9b868081af818e9d8ec1888099">[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 October 20, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-25509 Filed 11-23-22; 8:45 am]
BILLING CODE 4910-13-P
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