Proposed Rule2021-12603
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
June 16, 2021
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to supersede Airworthiness Directive (AD) 2019-20-10, 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, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2019-20-10 requires repetitive rototest inspections of the holes at the door stop fittings for any cracking, and corrective actions if necessary. Since the FAA issued AD 2019-20-10, a clarification of a certain compliance time for the rototest inspection was added. This proposed AD would clarify a certain compliance time and continue to require repetitive rototest inspections of the holes at the door stop fittings for any cracking, and repair 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 86 Issue 114 (Wednesday, June 16, 2021)</title>
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[Federal Register Volume 86, Number 114 (Wednesday, June 16, 2021)]
[Proposed Rules]
[Pages 31989-31992]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2021-12603]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0501; Project Identifier MCAI-2021-00168-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)
2019-20-10, 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, -216, -231, -232, and -233
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and
-232 airplanes. AD 2019-20-10 requires repetitive rototest inspections
of the holes at the door stop fittings for any cracking, and corrective
actions if necessary. Since the FAA issued AD 2019-20-10, a
clarification of a certain compliance time for the rototest inspection
was added. This proposed AD would clarify a certain compliance time and
continue to require repetitive rototest inspections of the holes at the
door stop fittings for any cracking, and repair 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 August 2,
2021.
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: Deliver to Mail address above 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#4100053201242032206f2434332e31206f2434"><span class="__cf_email__" data-cfemail="bafbfec9fadfdbc9db94dfcfc8d5cadb94dfcf">[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-2021-0501.
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-2021-
0501; 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.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
Large Aircraft Section, International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223;
email <a href="/cdn-cgi/l/email-protection#cf9caea1a5aeb6e19daea3a7aea18fa9aeaee1a8a0b9"><span class="__cf_email__" data-cfemail="3467555a5e554d1a6655585c555a745255551a535b42">[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-2021-0501; Project Identifier
MCAI-2021-00168-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 NPRM. Submissions containing CBI should be sent to
Sanjay Ralhan, Aerospace Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200 South 216th St., Des Moines,
WA 98198; telephone and fax 206-231-3223; email <a href="/cdn-cgi/l/email-protection#a7f4c6c9cdc6de89f5c6cbcfc6c9e7c1c6c689c0c8d1"><span class="__cf_email__" data-cfemail="2576444b4f445c0b7744494d444b654344440b424a53">[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.
[[Page 31990]]
Background
The FAA issued AD 2019-20-10, Amendment 39-19763 (84 FR 61526,
November 13, 2019) (AD 2019-20-10), 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, -216, -231,
-232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes. AD 2019-20-10 requires repetitive
rototest inspections of the holes at the door stop fittings for any
cracking, and corrective actions if necessary. The FAA issued AD 2019-
20-10 to address cracking of the web holes at the door stop fittings,
which could affect the structural integrity of the airplane.
Actions Since AD 2019-20-10 Was Issued
Since the FAA issued AD 2019-20-10, a clarification of the initial
compliance time for the rototest inspection, related to the
incorporation of certain airworthiness limitations (ALI) tasks has been
added. Certain airworthiness limitations (ALI) tasks referenced in EASA
AD 2018-0289, dated December 21, 2018 (which corresponds to FAA AD
2019-20-10) were initially applicable only to the left- and right-hand
door stop fitting holes at position 1 or 7 at fuselage frame (FR)20,
and, at a later stage, were made applicable to the left- and right-hand
door stop fitting holes at position 1 or 7 at fuselage FR16. An
operator reported a possible misunderstanding of the compliance time in
EASA AD 2018-0289. Therefore, EASA determined that the compliance time
language related to accomplishment of those ALI tasks needed to be
clarified.
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2018-0289R1, dated February 10, 2021
(EASA AD 2018-0289R1) (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
2018-0289R1 supersedes EASA AD 2018-0289 (which corresponds to FAA AD
2019-20-10). 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 a report that cracks were detected
on FR16 and FR20 web holes and passenger door intercostal fitting holes
at the door stop fitting locations. The FAA is proposing this AD to
address cracking of the web holes at the door stop fittings, which
could affect the structural integrity of the airplane. See the MCAI for
additional background information.
Explanation of Retained Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2019-20-10, this proposed AD would retain all of the
requirements of AD 2019-20-10. Those requirements are referenced in
EASA AD 2018-0289R1, which, in turn, is referenced in paragraph (g) of
this proposed AD.
Related Service Information Under 1 CFR Part 51
EASA AD 2018-0289R1 describes procedures for repetitive rototest
inspections of the holes at the door stop fittings for any cracking and
repair if necessary. 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 2018-0289R1 described previously, as incorporated by
reference, except for any differences identified as exceptions in the
regulatory text of this AD.
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA initially worked with Airbus and EASA to develop a
process to use certain EASA ADs as the primary source of information
for compliance with requirements for corresponding FAA ADs. The FAA has
since coordinated with other manufacturers and civil aviation
authorities (CAAs) to use this process. As a result, EASA AD 2018-
0289R1 will be incorporated by reference in the FAA final rule. This
proposed AD would, therefore, require compliance with EASA AD 2018-
0289R1 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 the EASA AD 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 the EASA AD. Service
information specified in EASA AD 2018-0289R1 that is required for
compliance with EASA AD 2018-0289R1 will be available on the internet
at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No.
FAA-2021-0501 after the FAA final rule is published.
Costs of Compliance
The FAA estimates that this proposed AD affects 1,528 airplanes of
U.S. registry. The FAA estimates the following costs to comply with
this proposed AD:
Estimated Costs for Required Actions
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Retained actions from AD 2019-20-10 33 work-hours x $85 per $0 $2,805 $3,447,345
(1,229 airplanes). hour = $2,805.
Inspections........................... 33 work-hours x 85 per 0 2,805 4,286,040
hour = 2,805.
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The FAA estimates the following costs to do any necessary on-
condition action 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 this on-condition action:
Estimated Costs of On-Condition Actions
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Cost per
Labor cost Parts cost product
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51 work-hours x $85 per hour = $4,335... $350 $4,685
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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
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) Would not affect intrastate aviation in Alaska, and
(3) Would 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) 2019-20-10, Amendment 39-19763
(84 FR 61526, November 13, 2019), and
0
b. Adding the following new AD:
Airbus SAS: Docket No. FAA-2021-0501; Project Identifier MCAI-2021-
00168-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by August 2, 2021.
(b) Affected ADs
This AD replaces AD 2019-20-10, Amendment 39-19763 (84 FR 61526,
November 13, 2019) (AD 2019-20-10).
(c) Applicability
This AD applies to Airbus SAS 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 2018-
0289R1, dated February 10, 2021 (EASA AD 2018-0289R1).
(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 a report that cracks were detected on
frame (FR)16 and FR20 web holes and passenger door intercostal
fitting holes at the door stop fitting locations, and a
determination that a certain compliance time needs to be clarified.
The FAA is issuing this AD to address cracking of the web holes at
the door stop fittings, which could affect the 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 2018-0289R1.
(h) Exceptions to EASA AD 2018-0289R1
(1) Where EASA AD 2018-0289R1 refers to its effective date, this
AD requires using the effective date of this AD.
(2) The ``Remarks'' section of EASA AD 2018-0289R1 does not
apply to this AD.
(3) Where Table 1 of EASA AD 2018-0289R1 refers to a compliance
time ``after 31 May 2017,'' this AD requires using a compliance time
after May 31, 2018 (the effective date of task 531103-01-1 in ``ALS
Part 2 rev. 6'').
(4) Where paragraphs (3) and (6) of EASA AD 2018-0289R1 refers
to actions that have been done ``in accordance with Airbus Repair
Design Approval Sheet (RDAS),'' this AD includes repair done ``in
accordance with 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.''
(i) 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 (j)(2) of
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#162f3b5740453b575f443b2125263b575b59555670777738717960"><span class="__cf_email__" data-cfemail="84bda9c5d2d7a9c5cdd6a9b3b7b4a9c5c9cbc7c4e2e5e5aae3ebf2">[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 2019-20-10 are approved as
AMOCs for the corresponding provisions of EASA AD 2018-0289R1 that
are required by paragraph (g) of this AD, except for those airplanes
having a compliance time specified in ``Table 1:
[[Page 31992]]
Inspection Thresholds,'' Row B, of EASA AD 2018-0289R1.
(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 2018-0289R1 that contains RC procedures and
tests: Except as required by paragraph (i)(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.
(j) Related Information
(1) For information about EASA AD 2018-0289R1, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221
8999 000; email <a href="/cdn-cgi/l/email-protection#bffefbccffdadeccde91dacacdd0cfde91daca"><span class="__cf_email__" data-cfemail="aaebeed9eacfcbd9cb84cfdfd8c5dacb84cfdf">[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-
2021-0501.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, Large Aircraft Section, International Validation
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3223; email <a href="/cdn-cgi/l/email-protection#6b380a05010a1245390a07030a052b0d0a0a450c041d"><span class="__cf_email__" data-cfemail="83d0e2ede9e2faadd1e2efebe2edc3e5e2e2ade4ecf5">[email protected]</span></a>.
Issued on June 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-12603 Filed 6-15-21; 8:45 am]
BILLING CODE 4910-13-P
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