Rule2021-18706
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
August 30, 2021
Effective
September 14, 2021
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-171N; Model A320-271N, -272N, and -273N airplanes; and Model A321-271N, -272N, -271NX, and -272NX airplanes. This AD was prompted by a report indicating that during inspection of the engines, two original rods installed to maintain an interface plate between the pylon and nacelle were found damaged at both rod-eye ends. This AD requires repetitive inspections of the pylon/engine interface rods for damage, and applicable corrective actions, and limits the installation of affected parts under certain conditions, 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 86 Issue 165 (Monday, August 30, 2021)</title>
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[Federal Register Volume 86, Number 165 (Monday, August 30, 2021)]
[Rules and Regulations]
[Pages 48296-48300]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2021-18706]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0719; Project Identifier MCAI-2021-00858-T;
Amendment 39-21709; AD 2021-18-08]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus SAS Model A319-171N; Model A320-271N, -272N, and -273N
[[Page 48297]]
airplanes; and Model A321-271N, -272N, -271NX, and -272NX airplanes.
This AD was prompted by a report indicating that during inspection of
the engines, two original rods installed to maintain an interface plate
between the pylon and nacelle were found damaged at both rod-eye ends.
This AD requires repetitive inspections of the pylon/engine interface
rods for damage, and applicable corrective actions, and limits the
installation of affected parts under certain conditions, 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 becomes effective September 14, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
14, 2021.
The FAA must receive comments on this AD by October 14, 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 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#a8e9ecdbe8cdc9dbc986cddddac7d8c986cddd"><span class="__cf_email__" data-cfemail="6f2e2b1c2f0a0e1c0e410a1a1d001f0e410a1a">[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 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="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No.
FAA-2021-0719.
Examining the AD Docket
You may examine the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by
searching for and locating Docket No. FAA-2021-0719; 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 AD, the mandatory
continuing airworthiness information (MCAI), 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#6231030c08031b4c30030e0a030c220403034c050d14"><span class="__cf_email__" data-cfemail="d281b3bcb8b3abfc80b3bebab3bc92b4b3b3fcb5bda4">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written data, views, or arguments
about this final rule. Send your comments to an address listed under
ADDRESSES. Include ``Docket No. FAA-2021-0719; Project Identifier MCAI-
2021-00858-T'' at the beginning of your comments. The most helpful
comments reference a specific portion of the final rule, 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
this final rule 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 final rule.
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 AD 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 AD, 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 AD. 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#9ecdfff0f4ffe7b0ccfff2f6fff0def8ffffb0f9f1e8"><span class="__cf_email__" data-cfemail="5c0f3d32363d25720e3d30343d321c3a3d3d723b332a">[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.
Background
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2021-0177, dated July 23, 2021 (EASA
AD 2021-0177) (also referred to as the Mandatory Continuing
Airworthiness Information, or the MCAI), to correct an unsafe condition
for certain Airbus SAS Model A319-171N; Model A320-271N, -272N, and -
273N airplanes; and Model A321-271N, -272N, -271NX, and -272NX
airplanes.
This AD was prompted by a report indicating that during inspection
of the engines, two original rods installed to maintain an interface
plate between the pylon and nacelle were found damaged at both rod-eye
ends. Investigation revealed that the rod damage was caused by the high
amplitude of vibrations during take-off and climb flight phases,
generated by engine-driven pump hydraulic pulsation and potential
resonance effects. The FAA is issuing this AD to address damage that
could lead to rupture of the rod-eye ends, which could result in fuel
and hydraulic pipe chafing, consequent fuel or hydraulic leakage, and
possible fire. See the MCAI for additional background information.
Related Service Information Under 1 CFR Part 51
EASA AD 2021-0177 specifies procedures for repetitive detailed
inspections for damage (e.g., hole damage, a crack, or an abnormal
deformation) of the left- and right-hand pylon/engine interface rod
ends of the rod attachment fittings, and the interface plate and upper
support brackets, a measurement of the play/gap of the pylon/engine
interface upper and lower rod ends, and applicable corrective actions
including rod replacement. EASA AD 2021-0177 also limits the
installation of affected parts if/unless inspected within the
compliance time specified. 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
These products have been approved by the aviation authority of
another country and are approved for operation in the United States.
Pursuant to the
[[Page 48298]]
FAA's bilateral agreement with this State of Design Authority, it has
notified the FAA of the unsafe condition described in the MCAI
described above. The FAA is issuing this AD after determining that the
unsafe condition described previously is likely to exist or develop on
other products of the same type design.
Requirements of This AD
This AD requires accomplishing the actions specified in EASA AD
2021-0177 described previously, 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 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,
EASA AD 2021-0177 is incorporated by reference in this AD. This AD
requires compliance with EASA AD 2021-0177 in its entirety through that
incorporation, except for any differences identified as exceptions in
the regulatory text of this AD. Using common terms that are the same as
the heading of a particular section in EASA AD 2021-0177 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
2021-0177. Service information required by EASA AD 2021-0177 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-2021-0719 after this AD is
published.
Interim Action
The FAA considers this AD interim action. If final action is later
identified, the FAA might consider further rulemaking then.
FAA's Justification and Determination of the Effective Date
Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and
comment procedures for rules when the agency, for ``good cause,'' finds
that those procedures are ``impracticable, unnecessary, or contrary to
the public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without providing notice and seeking
comment prior to issuance. Further, section 553(d) of the APA
authorizes agencies to make rules effective in less than thirty days,
upon a finding of good cause.
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies foregoing notice and comment prior to adoption of this rule
because rupture of the rod-eye ends could result in fuel and hydraulic
pipe chafing, consequent fuel or hydraulic leakage, and possible fire.
Accordingly, notice and opportunity for prior public comment are
impracticable and contrary to the public interest pursuant to 5 U.S.C.
553(b)(3)(B).
In addition, the FAA finds that good cause exists pursuant to 5
U.S.C. 553(d) for making this amendment effective in less than 30 days,
for the same reasons the FAA found good cause to forego notice and
comment.]
Regulatory Flexibility Act (RFA)
The requirements of the RFA do not apply when an agency finds good
cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and
comment. Because the FAA has determined that it has good cause to adopt
this rule without notice and comment, RFA analysis is not required.
Costs of Compliance
The FAA estimates that this AD affects 204 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
----------------------------------------------------------------------------------------------------------------
Up to 6 work-hours x $85 per hour $0 Up to $510........... Up to $104,040.
= Up to $510.
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* Table does not include estimated costs for reporting
The FAA estimates that it takes about 1 work-hour per product to
comply with the reporting requirement in this AD. The average labor
rate is $85 per hour. Based on these figures, the FAA estimates the
cost of reporting the inspection results on U.S. operators to be
$17,340, or $85 per product.
Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
Labor cost Parts cost Cost per product
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Up to 8 work-hours x $85 per $0 Up to $680.
hour = Up to $680.
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The FAA has received no definitive data on which to base the cost
estimates for the other on-condition corrective actions for the
operational check specified in this AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to take
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, and completing and reviewing the
collection of information. All responses to this collection of
[[Page 48299]]
information are mandatory. Send comments regarding this burden estimate
or any other aspect of this collection of information, including
suggestions for reducing this burden, to: Information Collection
Clearance Officer, Federal Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177-1524.
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, and
(2) Will not affect intrastate aviation in Alaska.
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:
2021-18-08 Airbus SAS: Amendment 39-21709; Docket No. FAA-2021-0719;
Project Identifier MCAI-2021-00858-T.
(a) Effective Date
This airworthiness directive (AD) is effective September 14,
2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model A319-171N; Model A320-271N,
-272N, and -273N airplanes; and Model A321-271N, -272N, -271NX, and
-272NX airplanes; certificated in any category; as identified in
European Union Aviation Safety Agency (EASA) AD 2021-0177, dated
July 23, 2021 (EASA AD 2021-0177).
(d) Subject
Air Transport Association (ATA) of America Code 29, Hydraulic
Power.
(e) Unsafe Condition
This AD was prompted by a report indicating that during
inspection of the engines, two original rods installed to maintain
an interface plate between the pylon and nacelle were found damaged
at both rod-eye ends. The FAA is issuing this AD to address damage
that could lead to rupture of the rod-eye ends, which could result
in fuel and hydraulic pipe chafing, consequent fuel or hydraulic
leakage, and possible fire.
(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 2021-0177.
(h) Exceptions and Clarifications to EASA AD 2021-0177
(1) Where EASA AD 2021-0177 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where paragraph (2) of EASA AD 2021-0177 specifies a
compliance time for the initial detailed inspection for Group 2
airplanes, this AD requires initial compliance at the later of the
times specified in paragraphs (h)(2)(i) and (ii) of this AD.
Remaining provisions of paragraph (2) of EASA AD 2021-0177 that are
not specifically referenced in this paragraph remain fully
applicable and must be complied with.
(i) Before exceeding 750 total flight hours, but no earlier than
650 total flight hours, since either manufacture of the airplane or
embodiment of Airbus Service Bulletin A320-29-1189, as applicable.
(ii) Within 750 flight hours after the effective date of this
AD.
(3) The ``Remarks'' section of EASA AD 2021-0177 does not apply
to this AD.
(i) Additional 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) of this
AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#6f56422e393c422e263d42585c5f422e22202c2f090e0e41080019"><span class="__cf_email__" data-cfemail="546d7915020779151d06796367647915191b17143235357a333b22">[email protected]</span></a>.
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, 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 2021-0177 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
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#c794a6a9ada6bee995a6abafa6a987a1a6a6e9a0a8b1"><span class="__cf_email__" data-cfemail="bfecded1d5dec691edded3d7ded1ffd9dede91d8d0c9">[email protected]</span></a>.
(k) 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 2021-0177,
dated July 23, 2021.
(ii) [Reserved]
(3) For information about EASA AD 2021-0177, contact EASA,
Konrad-Adenauer-Ufer
[[Page 48300]]
3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#4d0c093e0d282c3e2c6328383f223d2c632838"><span class="__cf_email__" data-cfemail="06474275466367756728637374697667286373">[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>.
(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#83e5f1adeaedf0f3e6e0f7eaecedc3ede2f1e2ade4ecf5"><span class="__cf_email__" data-cfemail="e58397cb8c8b96958086918c8a8ba58b849784cb828a93">[email protected]</span></a>, or go to: <a href="https://www.archives.gov/federal-register/cfr/ibr-locations.html">https://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued on August 24, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-18706 Filed 8-26-21; 11:15 am]
BILLING CODE 4910-13-P
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