Proposed Rule2022-08909
Airworthiness Directives; Airbus SAS Airplanes
Primary source
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Published
May 6, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to supersede Airworthiness Directive (AD) 2018-03-12, which applies 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 requires repetitive rototest inspections for cracking of the fastener holes in certain door stop fittings, and repair if necessary. Since the FAA issued AD 2018-03-12, new analysis by the manufacturer resulted in optimized compliance times for the inspections. This proposed AD would 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 proposed for incorporation by reference. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 87 Issue 88 (Friday, May 6, 2022)</title>
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[Federal Register Volume 87, Number 88 (Friday, May 6, 2022)]
[Proposed Rules]
[Pages 27032-27035]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-08909]
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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]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2018-03-12, which applies 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 requires repetitive rototest inspections for
cracking of the fastener holes in certain door stop fittings, and
repair if necessary. Since the FAA issued AD 2018-03-12, new analysis
by the manufacturer resulted in optimized compliance times for the
inspections. This proposed AD would 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 proposed for incorporation by reference. The FAA is
proposing this AD to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by June 21,
2022.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="https://www.regulations.gov">https://www.regulations.gov</a>. Follow the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
<bullet> Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For material that will be 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#0544417645606476642b6070776a75642b6070"><span class="__cf_email__" data-cfemail="fcbdb88fbc999d8f9dd299898e938c9dd29989">[email protected]</span></a>; internet
www.easa.europa.eu. You may find this IBR material on the EASA website
at <a href="https://ad.easa.europa.eu">https://ad.easa.europa.eu</a>. You may view this IBR 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 on the internet at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by
searching for and locating Docket No. FAA-2022-0503.
Examining the AD Docket
You may examine the AD docket on the internet at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating 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 NPRM, any comments received, and other information. The street
address for Docket Operations is listed above. Comments will be
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
Large Aircraft Section, International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198; telephone 206-231-3229; email
<a href="/cdn-cgi/l/email-protection#b8ced4d9dcd1d5d1ca96cdd4c1d9d6d7cef8ded9d996dfd7ce"><span class="__cf_email__" data-cfemail="bbcdd7dadfd2d6d2c995ced7c2dad5d4cdfbdddada95dcd4cd">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2022-0503; Project Identifier
MCAI-2021-01244-T'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
the proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
<a href="https://www.regulations.gov">https://www.regulations.gov</a>, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this proposed AD.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this
[[Page 27033]]
NPRM. Submissions containing CBI should be sent to Vladimir Ulyanov,
Aerospace Engineer, Large Aircraft Section, International Validation
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 206-
231-3229; email <a href="/cdn-cgi/l/email-protection#3f49535e5b5652564d114a53465e5150497f595e5e11585049"><span class="__cf_email__" data-cfemail="97e1fbf6f3fefafee5b9e2fbeef6f9f8e1d7f1f6f6b9f0f8e1">[email protected]</span></a>. Any commentary that the FAA
receives which is not specifically designated as CBI will be placed in
the public docket for this rulemaking.
Discussion
The FAA issued AD 2018-03-12, Amendment 39-19185 (83 FR 5906,
February 12, 2018) (AD 2018-03-12), which applies 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 requires repetitive rototest
inspections for cracking of the fastener holes in certain door stop
fittings, and repair if necessary. The FAA issued AD 2018-03-12 to
address cracking at the door stop fitting holes of fuselage frame (FR)
66 and FR68. Such cracking could result in reduced structural integrity
of the airplane due to the failure of structural components.
Actions Since AD 2018-03-12 Was Issued
Since the FAA issued AD 2018-03-12, Airbus has revised the
compliance times to accomplish the rototest inspections based on
reports from operators and new analysis.
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 Mandatory Continuing
Airworthiness Information, or 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. EASA AD
2021-0242 supersedes EASA AD 2016-0238 (which corresponds to FAA AD
2018-03-12). 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.
This proposed AD was prompted by reports of fatigue damage in the
structure for the door stop fittings on certain fuselage frames. The
FAA is proposing this AD to address cracking at the door stop fitting
holes of fuselage FR66 and FR68 which could result in reduced
structural integrity of the airplane. See the MCAI for additional
background information.
Model A320-216 Airplanes
The Airbus SAS Model A320-216 was U.S. type certificated on
December 19, 2016. Before that date, any EASA ADs that affected Model
A320-216 airplanes were included in the U.S. type certificate as part
of the Required Airworthiness Actions List (RAAL). One or more Model
A320-216 airplanes have subsequently been placed on the U.S. Register,
and will now be included in FAA AD actions. For Model A320-216
airplanes, the requirements that correspond to AD 2018-03-12 were
mandated by the MCAI via the RAAL. Although that RAAL requirement is
still in effect, for continuity and clarity the FAA has identified
Model A320-216 airplanes in paragraph (c) of this proposed AD; the MCAI
that is specified in paragraph (g) in this proposed AD includes
retained requirements, which would therefore apply to those airplanes.
Explanation of Retained Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2018-03-12, this proposed AD would retain all of the
requirements of AD 2018-03-12. Those requirements are referenced in
EASA AD 2021-0242, which, in turn, is referenced in paragraph (g) of
this proposed AD.
Related Service Information Under 1 CFR Part 51
EASA AD 2021-0242 describes 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.
FAA's Determination and Requirements of This Proposed AD
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 the State of Design Authority,
the FAA has been notified of the unsafe condition described in the MCAI
referenced above. The FAA is proposing this AD because the FAA
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in EASA AD 2021-0242 described previously, as incorporated by
reference, except for any differences identified as exceptions in the
regulatory text of this proposed AD.
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA developed a process to use some civil aviation
authority (CAA) ADs as the primary source of information for compliance
with requirements for corresponding FAA ADs. The FAA has been
coordinating this process with manufacturers and CAAs. As a result, the
FAA proposes to incorporate EASA AD 2021-0242 by reference in the FAA
final rule. This proposed AD would, therefore, require compliance with
EASA AD 2021-0242 in its entirety through that incorporation, except
for any differences identified as exceptions in the regulatory text of
this proposed AD. Using common terms that are the same as the heading
of a particular section in EASA AD 2021-0242 does not mean that
operators need comply only with that section. For example, where the AD
requirement refers to ``all required actions and compliance times,''
compliance with this AD requirement is not limited to the section
titled ``Required Action(s) and Compliance Time(s)'' in EASA AD 2021-
0242. Service information required by EASA AD 2021-0242 for compliance
will be available at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and
locating Docket No. FAA-2022-0503 after the FAA final rule is
published.
Costs of Compliance
The FAA estimates that this proposed AD affects 1,084 airplanes of
U.S. registry. The FAA estimates the following costs to comply with
this proposed AD:
[[Page 27034]]
Estimated Costs for Required Actions
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Action Labor cost Parts cost Cost per product Cost on U.S. operators
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Inspections.................. Up to 25 work- $0 Up to $2,125.......... Up to $2,303,500.
hours x $85
per hour =
$2,125.
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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
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
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Up to 27 work-hours x $85 per hour = $610 $2,905
$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 proposed 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
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(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 Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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) 2018-03-12, Amendment 39-19185
(83 FR 5906, February 12, 2018); and
0
b. Adding the following new AD:
Airbus SAS: Docket No. FAA-2022-0503; Project Identifier MCAI-2021-
01244-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by June 21, 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 any
crack is found during any inspection to ``contact Airbus for
approved instructions for corrective actions and accomplish those
instructions accordingly,'' this AD requires if any cracking is
found, 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
[[Page 27035]]
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) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Large Aircraft Section, 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 Large Aircraft Section, International Validation Branch, send it
to the attention of the person identified in paragraph (k)(2) of
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#172e3a5641443a565e453a2024273a565a58545771767639707861"><span class="__cf_email__" data-cfemail="f1c8dcb0a7a2dcb0b8a3dcc6c2c1dcb0bcbeb2b1979090df969e87">[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): For any service information
referenced in EASA AD 2021-0242 that contains RC procedures and
tests: Except as required by paragraph (j)(2) of this AD, RC
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
(1) For information about 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#cf8e8bbc8faaaebcaee1aababda0bfaee1aaba"><span class="__cf_email__" data-cfemail="3170754271545042501f5444435e41501f5444">[email protected]</span></a>; internet www.easa.europa.eu. You
may find this EASA AD on the EASA website at <a href="https://ad.easa.europa.eu">https://ad.easa.europa.eu</a>. 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. This material may be
found in the AD docket on the internet at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No. FAA-
2022-0503.
(2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, Large Aircraft Section, International
Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198;
telephone 206-231-3229; email <a href="/cdn-cgi/l/email-protection#97e1fbf6f3fefafee5b9e2fbeef6f9f8e1d7f1f6f6b9f0f8e1"><span class="__cf_email__" data-cfemail="7c0a101d181511150e520910051d12130a3c1a1d1d521b130a">[email protected]</span></a>.
Issued on April 21, 2022.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022-08909 Filed 5-5-22; 8:45 am]
BILLING CODE 4910-13-P
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