Rule2021-25201
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 19, 2021
Effective
December 27, 2021
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2019-21- 10, which applied to all Airbus SAS Model A321-111, -112, -131, -211, - 212, -213, -231, and -232 airplanes. AD 2019-21-10 required a one-time eddy current conductivity measurement of certain structural parts of the outer flaps to determine if the incorrect alloy was used, and replacement if necessary. This AD continues to require a one-time eddy current conductivity measurement of certain structural parts of the outer flaps to determine if the incorrect alloy was used, and replacement if necessary; and also requires a new one-time eddy current conductivity measurement of certain other structural parts of the outer flaps to determine if the parts were properly heat treated, and replacement if necessary; and includes additional affected airplanes; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a quality control review, which determined that the wrong aluminum alloy was used to manufacture several structural parts and by the issuance of an updated list of suspected parts, including those that may have been improperly heat treated. 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 221 (Friday, November 19, 2021)</title>
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[Federal Register Volume 86, Number 221 (Friday, November 19, 2021)]
[Rules and Regulations]
[Pages 64801-64805]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2021-25201]
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Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
Federal Register / Vol. 86, No. 221 / Friday, November 19, 2021 /
Rules and Regulations
[[Page 64801]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-1029; Project Identifier MCAI-2020-01126-T;
Amendment 39-21777; AD 2021-22-04]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-21-
10, which applied to all Airbus SAS Model A321-111, -112, -131, -211, -
212, -213, -231, and -232 airplanes. AD 2019-21-10 required a one-time
eddy current conductivity measurement of certain structural parts of
the outer flaps to determine if the incorrect alloy was used, and
replacement if necessary. This AD continues to require a one-time eddy
current conductivity measurement of certain structural parts of the
outer flaps to determine if the incorrect alloy was used, and
replacement if necessary; and also requires a new one-time eddy current
conductivity measurement of certain other structural parts of the outer
flaps to determine if the parts were properly heat treated, and
replacement if necessary; and includes additional affected airplanes;
as specified in a European Union Aviation Safety Agency (EASA) AD,
which is incorporated by reference. This AD was prompted by a quality
control review, which determined that the wrong aluminum alloy was used
to manufacture several structural parts and by the issuance of an
updated list of suspected parts, including those that may have been
improperly heat treated. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective December 27, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 27,
2021.
ADDRESSES: For material incorporated by reference (IBR) in this AD,
contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone:
+49 221 8999 000; email: <a href="/cdn-cgi/l/email-protection#d29396a192b7b3a1b3fcb7a7a0bda2b3fcb7a7"><span class="__cf_email__" data-cfemail="4f0e0b3c0f2a2e3c2e612a3a3d203f2e612a3a">[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-2020-1029.
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-2020-
1029; 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, 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.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
Large Aircraft Section, International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198; phone and fax: 206-231-3223;
email: <a href="/cdn-cgi/l/email-protection#c2b1a3aca8a3bbecb0a3aeaaa3ac82a4a3a3eca5adb4"><span class="__cf_email__" data-cfemail="a4d7c5cacec5dd8ad6c5c8ccc5cae4c2c5c58ac3cbd2">[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 2020-0174, dated August 5, 2020
(EASA AD 2020-0174) (also referred to as the Mandatory Continuing
Airworthiness Information, or the MCAI), to correct an unsafe condition
for all Airbus SAS Model A318-111, -112, -121, and -122 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 2019-21-10, Amendment 39-19776 (84 FR
63794, November 19, 2019) (AD 2019-21-10). AD 2019-21-10 applied to all
Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes. The NPRM published in the Federal Register on November 20,
2020 (85 FR 74299). The NPRM was prompted by a quality control review,
which determined that the wrong aluminum alloy was used to manufacture
several structural parts and by the issuance of an updated list of
suspected parts, including those that may have been improperly heat
treated. The NPRM proposed to continue to require a one-time eddy
current conductivity measurement of certain structural parts of the
outer flaps to determine if the incorrect alloy was used, and
replacement if necessary, as specified in EASA AD 2019-0012, dated
January 24, 2019 (which corresponds to FAA AD 2019-21-10). The NPRM
also proposed to require a new one-time eddy current conductivity
measurement of certain other structural parts of the outer flaps to
determine if the parts were properly heat treated, and replacement if
necessary, and to include additional affected airplanes, as specified
in EASA AD 2020-0174.
The FAA is issuing this AD to address structural parts that may not
meet the certified life limit, which could result in failure of the
flap trailing edge and reduced controllability of the airplane. See the
MCAI for additional background information.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the NPRM and the FAA's response to each comment.
[[Page 64802]]
Request To Include All Required Airplanes in the SUMMARY of the NPRM
Bradley Schrock requested the FAA include the additional required
Airbus Model airplanes in the SUMMARY section of the NPRM. The
commenter pointed out that the additional models could easily be
overlooked if the reader were to only read the SUMMARY of the NPRM.
The FAA does not agree to revise the SUMMARY of this final rule.
Operators are required to follow the applicability of the AD, which is
specified in paragraph (c) of this AD. While the SUMMARY of this final
rule doesn't specify all airplanes affected by this AD, it does specify
that the FAA is adding airplanes to the applicability. Additionally, in
the Background section of this final rule, the FAA has included all
airplane models that are affected by this AD. Further, the SUMMARY
section is a preamble requirement for all documents published in the
Federal Register and must follow drafting requirements prescribed by
the Office of the Federal Register (OFR). The SUMMARY section briefly
provides context for the document within the Federal Register/CFR
publication system; it does not summarize the content of the document.
Adding the requested airplane models does not follow the OFR's
requirements for the SUMMARY section. The FAA has not changed this
final rule in this regard.
Request To Revise Compliance Statement in Paragraph (f) of the Proposed
AD for Model A321 Airplanes
Delta Air Lines (DAL) requested that the FAA revise the compliance
statement in paragraph (f) of the proposed AD for Model A321 airplanes.
DAL suggested that paragraph (f) of the NPRM be revised to read:
``Comply with this AD within the compliance times specified, unless
already done. For A321 operators, the earliest date that compliance may
have occurred is 29MAY2020 (the issuance date of [EASA] PAD 19-
100R1).'' DAL pointed out that the suspected parts are line replaceable
units (LRUs) with off-wing Instructions for Continued Airworthiness,
and that these parts comprise a pool of rotable parts. DAL then
specified that no revision of the service information referenced in
EASA AD 2020-0174 has included the serial numbers of outer flap tabs.
DAL stated that EASA AD 2020-0174 allows the use of any revision of the
service information for the determination of these suspected parts.
Further, DAL argued that, for Model A321 operators, the use of any
service information revision for determination of suspected part
applicability is inadequate for the identification of suspected outer
flap tabs. DAL asserted that before May 29, 2020, comparison with the
outer flap serial number lists within the service information
referenced in EASA AD 2020-0174 could allow inadvertent exclusion of an
outer flap tab that is included in the quality escape population.
The FAA does not agree to revise the compliance statement in
paragraph (f) of this AD. As stated previously, EASA AD 2020-0174 takes
precedence over the service information referenced therein and this AD
requires using EASA AD 2020-0174 for determining suspected parts. EASA
AD 2020-0174 specifies using the service information only for
accomplishing the required inspections and not for identifying the
suspected parts. The FAA has determined EASA AD 2020-0174 addresses the
unsafe condition on the universe of suspected parts. Further, the FAA
has determined that the information provided by EASA and the
manufacturer is adequate information for accomplishing the required
actions. The FAA has not changed this AD regarding this issue.
Request To Add Exception To Clarify the Definition of Suspected
Improperly Heat Treated (IHT) Parts
DAL requested that the FAA revise the NPRM to include an exception
to EASA AD 2020-0174 to clarify the definition of suspected IHT parts
for Model A321 airplanes. DAL specified that, for Model A321 airplanes,
the suspected IHT parts are constituent parts of the outer flap tabs,
not the outer flaps as defined in EASA AD 2020-0174. DAL mentioned that
if not clarified, the definition could introduce confusion for
operators of Model A321 airplanes.
The FAA does not agree to include an exception to EASA AD 2020-
0174. Appendix 2 of EASA AD 2020-0174 refers to the airplane
manufacturer serial numbers, flap serial numbers, and the flap tab part
numbers, based on the airplane configuration at the time of delivery to
the first operator. Therefore, the FAA has determined that, even though
the definition specified in EASA AD 2020-0174 does not explicitly state
that, for Model A321 airplanes the suspected IHT parts are constituent
to the outer flap tabs, the information necessary to make that
determination is already included in Appendix 2 of EASA AD 2020-0174,
which the definition references. The FAA has not changed this AD
regarding this issue.
Request To Include Additional Service Information for Determining
Affected Parts
DAL requested that the FAA revise the NPRM to include Airbus In-
Service Information (ISI) Document 57.50.00022, which DAL stated
includes outer flap and outer flap tab part number definitions for the
serial numbers defined in Appendix 1 and Appendix 2 of EASA AD 2020-
0174. DAL pointed out that Appendix 1 and Appendix 2 of EASA AD 2020-
0174 do not contain any outer flap or outer flap tab (Model A321) part
numbers, instead specifying the suspected part population by LRU serial
number. DAL also mentioned that Airbus does not consider the Model A321
flap tab serial numbers to be Aircraft Inspection Report (AIR)
recordable within each airplane's delivery records. DAL implied that
most operators would have difficulty tracing outer flap tab serial
numbers to specific airplane manufacturer serial numbers. DAL also
stated that there has been enough operator demand for clarification
from the manufacturer that Airbus released ISI 57.50.00022. DAL noted
that ISI 57.50.00022 is not referenced in the service information
specified by EASA AD 2020-0174.
The FAA disagrees with the request. This AD is based on EASA AD
2020-0174, which is based on the configuration of the airplane at the
time of delivery (as indicated in Notes 2 and 3 of EASA AD 2020-0174).
It is not possible for the FAA to know all of the operator-specific
part numbers and serial numbers installed on all of the airplanes
affected by this AD or EASA AD 2020-0174. Therefore, it is the
operator's responsibility to track these parts, so that they can
identify discrepant parts as defined in the EASA AD and apply
appropriate corrective actions. If an operator's fleet configuration,
including part tracking system, does not allow compliance with the
requirements of this AD, then that operator must present a customized
plan for AD compliance for the applicable airplane with a request for
an alternative method of compliance (AMOC) under the provisions of
paragraph (i)(1) of this AD. It is impractical for the FAA to customize
an AD in a way that meets operator's specific requirements for
compliance. The FAA has not changed this AD regarding this issue.
Request To Include an Exception to the Method of Compliance
DAL requested that the FAA add an exception to include a statement
that,
[[Page 64803]]
for demonstration of compliance with Paragraph (5) of EASA AD 2020-
0174, the part serial number does not need to be positively identified,
provided that it can be determined that the part is serviceable using
the definition provided in EASA AD 2020-0174. DAL mentioned that the
service information specified in EASA AD 2020-0174 does not contain
part numbers for suspected parts, and instead the only part numbers
within the service information appendices are the part numbers of
potentially discrepant structural parts, which on Model A321 airplanes
are not serialized. DAL pointed out that verbatim application of the
service information might cause improper evaluation of parts for
applicability of the suspected part definition. DAL continued to point
out that the service information conflicts with EASA AD 2020-0174, and
that EASA AD 2020-0174 bounds the suspected outer flap tab population
by outer flap tab serial number in Appendix 2 of EASA AD 2020-0174. DAL
then pointed out that verbatim application of the service information
on Model A321 airplanes could introduce the possibility that the
inspection of an outer flap tab with potentially discrepant internal
structure is not completed.
The FAA does not agree to include the requested exception. This AD
requires EASA AD 2020-0174, which is based on the configuration of an
airplane at the time of delivery. As specified in EASA AD 2020-0174, if
a serial number cannot be identified, then that part is defined as a
suspected part. EASA AD 2020-0174 takes precedence over any
instructions specified in the service information it references.
Therefore, operators can comply with the requirements of this AD.
However, once this AD is published, any person may present sufficient
data and rationale and request approval of an AMOC under the provisions
of paragraph (i)(1) of this AD. The FAA has not changed this AD
regarding this issue.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule as proposed, except for minor
editorial changes. The FAA has determined that these minor changes:
<bullet> Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
<bullet> Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
EASA AD 2020-0174 describes procedures for a one-time eddy current
conductivity measurement of certain structural parts of the outer flaps
to determine if the incorrect alloy was used, and replacement if
necessary; and a one-time eddy current conductivity measurement of
certain other structural parts of the outer flaps to determine if the
parts were properly heat treated, and replacement 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.
Costs of Compliance
The FAA estimates that this AD affects 63 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 6 work-hours x $85 per $0 $510 $32,130
2019[dash]21[dash]10. hour = $510.
New actions........................... 5 work-hours x $85 per 0 425 26,775
hour = $425.
----------------------------------------------------------------------------------------------------------------
* 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
$5,355, or $85 per product.
The FAA has received no definitive data on which to base the cost
estimates for the on-condition replacement specified in this AD.
According to the manufacturer, some or all of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators. The FAA does not control warranty coverage for
affected operators. As a result, the FAA has included all known costs
in the cost estimate.
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 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 current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the
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
[[Page 64804]]
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.
Adoption of 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) 2019-21-10, Amendment 39-19776
(84 FR 63794, November 19, 2019); and
0
b. Adding the following new AD:
2021-22-04 Airbus SAS: Amendment 39-21777; Docket No. FAA-2020-1029;
Project Identifier MCAI-2020-01126-T.
(a) Effective Date
This airworthiness directive (AD) is effective December 27,
2021.
(b) Affected ADs
This AD replaces AD 2019-21-10, Amendment 39-19776 (84 FR 63794,
November 19, 2019) (AD 2019-21-10).
(c) Applicability
This AD applies to all Airbus SAS airplanes identified in
paragraphs (c)(1) through (4) of this AD, certificated in any
category.
(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 57, Wings.
(e) Reason
This AD was prompted by a quality control review, which
determined that the wrong aluminum alloy was used to manufacture
several structural parts and by the issuance of an updated list of
suspected parts, including those that may have been improperly heat
treated. The FAA is issuing this AD to address structural parts that
may not meet the certified life limit, which could result in failure
of the flap trailing edge and reduced controllability 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, European Union Aviation Safety Agency (EASA) AD
2020-0174, dated August 5, 2020 (EASA AD 2020-0174).
(h) Exceptions to EASA AD 2020-0174
(1) Where EASA AD 2020-0174 refers to its effective date, this
AD requires using the effective date of this AD.
(2) The ``Remarks'' section of EASA AD 2020-0174 does not apply
to this AD.
(3) Where paragraphs (7) and (8) of EASA AD 2020-0174 mandate a
parts installation limitation, this AD requires the following parts
installation limitation: From the effective date of this AD, only
serviceable parts as defined in EASA AD 2020-0174 are allowed to be
installed on any airplane.
(4) Where any service information referenced in EASA AD 2020-
0174 specifies reporting, this AD requires reporting all inspection
results at the applicable time specified in paragraph (h)(4)(i) or
(ii) of this AD. If operators have reported findings as part of
obtaining any corrective actions approved by Airbus SAS's EASA
Design Organization Approval (DOA), operators are not required to
report those findings as specified in this paragraph.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 90 days after the effective date
of this AD.
(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) of this
AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#3c05117d6a6f117d756e110b0f0c117d71737f7c5a5d5d125b534a"><span class="__cf_email__" data-cfemail="370e1a7661641a767e651a0004071a767a78747751565619505841">[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 DOA. If approved by the DOA, the approval must include
the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraphs (h)(4) and (i)(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.
(4) Paperwork Reduction Act Burden Statement: 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 current 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 be 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 information are mandatory as
required by this AD. 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.
(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; phone and
fax: 206-231-3223; email: <a href="/cdn-cgi/l/email-protection#b5c6d4dbdfd4cc9bc7d4d9ddd4dbf5d3d4d49bd2dac3"><span class="__cf_email__" data-cfemail="5526343b3f342c7b2734393d343b153334347b323a23">[email protected]</span></a>.
(k) 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.
[[Page 64805]]
(i) European Union Aviation Safety Agency (EASA) AD 2020-0174,
dated August 5, 2020.
(ii) [Reserved]
(3) For EASA AD 2020-0174, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; phone: +49 221 8999 000; email:
<a href="/cdn-cgi/l/email-protection#6d2c291e2d080c1e0c4308181f021d0c430818"><span class="__cf_email__" data-cfemail="7b3a3f083b1e1a081a551e0e09140b1a551e0e">[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. 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-2020-1029.
(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#c8aebae6a1a6bbb8adabbca1a7a688a6a9baa9e6afa7be"><span class="__cf_email__" data-cfemail="5533277b3c3b26253036213c3a3b153b3427347b323a23">[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 October 13, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021-25201 Filed 11-18-21; 8:45 am]
BILLING CODE 4910-13-P
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</html>Indexed from Federal Register on November 19, 2021.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.