Rule2022-02554
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
February 8, 2022
Effective
March 15, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2019-20- 10, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112,-113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2019-20-10 required 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 AD clarifies a certain compliance time and continues 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 incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 87 Issue 26 (Tuesday, February 8, 2022)</title>
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[Federal Register Volume 87, Number 26 (Tuesday, February 8, 2022)]
[Rules and Regulations]
[Pages 7033-7037]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-02554]
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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;
Amendment 39-21908; AD 2022-02-11]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-20-
10, which applied to certain Airbus SAS Model A318 series airplanes;
Model A319-111, -112,-113, -114, -115, -131, -132, and -133 airplanes;
Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and
Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
AD 2019-20-10 required 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 AD
clarifies a certain compliance time and continues 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 incorporated by reference.
The FAA is issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective March 15, 2022.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 15,
2022.
ADDRESSES: 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#ebaaaf98ab8e8a988ac58e9e99849b8ac58e9e"><span class="__cf_email__" data-cfemail="a4e5e0d7e4c1c5d7c58ac1d1d6cbd4c58ac1d1">[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-2021-0501.
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-2021-0501; 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 final rule, the
mandatory continuing airworthiness information (MCAI), any comments
received, and other information. The address for Docket Operations is
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
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#6d3e0c03070c14433f0c01050c032d0b0c0c430a021b"><span class="__cf_email__" data-cfemail="80d3e1eeeae1f9aed2e1ece8e1eec0e6e1e1aee7eff6">[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 2018-0289R1, dated February 10, 2021
(EASA AD 2018-0289R1) (also referred to as the MCAI), to correct an
unsafe condition for certain Airbus SAS Model A318 series airplanes;
Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes;
Model A320-211, -212, -214, -215, -216, -231, -232, and -233 airplanes;
and Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes. EASA AD 2018-0289R1 supersedes EASA AD 2018-0289 (which
corresponds to FAA AD 2019-20-10, Amendment 39-19763 (84 FR 61526,
November 13, 2019) (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.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2019-20-10. AD 2019-20-10 applied to
certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -
113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212,
-214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -
131, -211, -212, -213, -231, and -232 airplanes. The NPRM published in
the Federal Register on June 16, 2021 (86 FR 31989). The NPRM 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 NPRM proposed to 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 EASA AD 2018-0289R1.
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. See the MCAI for additional background information.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from two commenters, including Delta
Airlines (DAL) and United Airlines (UAL). The following presents the
comments received on the NPRM and the FAA's response to each comment.
[[Page 7034]]
Request To Clarify the Requirements of the Repair Design Approval Sheet
(RDAS)
DAL requested clarification for the following RDAS approval:
<bullet> Can the FAA confirm that paragraph (h)(4) of the proposed
AD allow operators to account for repairs that are approved using a
Repair and Design Approval Form (RDAF) in addition to those repairs
that are approved using RDAS? DAL commented that since 2021, the RDAS
is no longer Airbus's form of approving repair instructions and it has
been replaced by RDAF.
<bullet> Can the FAA confirm that if a repair has been approved,
``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,'' it is acceptable
to accomplish the next inspection for each repaired area affected by
using the same method of compliance? DAL commented that if this is the
case, it requests the FAA either revise paragraph (h)(4) of the
proposed AD or include an exception paragraph to the proposed AD to
explicitly makes this clear.
The FAA confirms that it accepts Airbus's EASA DOA approval in the
form of both an RDAS and an RDAF. The FAA also confirms that for
paragraph (3) of EASA AD 2018-0289R1, the next inspections are done at
the times specified in the approved method. The FAA has added paragraph
(h)(5) of this AD to specify where paragraph (3) of EASA AD 2018-0289R1
refers to accomplishing the next due inspection of each repaired
affected area ``within the compliance time as specified in, Airbus
RDAS, as applicable,'' this AD uses the applicable compliance time
specified in the repair ``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.''
Request To Revise the Compliance Time
UAL stated AD 2018-0289R1 was issued to clarify that, to determine
the compliance time for the initial inspection of an affected area, the
latest accomplishment of the airworthiness limitations item (ALI) task
for that affected area must be taken into account. UAL stated that the
initial inspection for the FR16 door stop fitting holes cannot be
accomplished within 16,800 flight cycles from ALI task 531103-01-1 if
FR20 was the only applicable side for the task at ``[airworthiness
limitations section] ALS Part 2 Rev 3'' or earlier revisions. UAL
commented that, therefore, the proposed AD may have an impact on an
airline's operation and, for FR16 only, result in immediate
non[hyphen]compliance if ALI task 531103-01-1 was accomplished at ``ALS
Part 2 Rev 3'' or earlier revisions for FR20. UAL stated that condition
``A'' in ``Table 1: Inspection Thresholds'' of AD 2018-0289R1,
specifies the inspection threshold for FR16 as 30,000 total flight
cycles and certain airplanes may be above 30,000 total flight cycles
under this condition.
UAL commented that the side of FR16 was added to the ALI task
531103-01-1 description in ``ALS Part 2 Rev 4,'' and as stated in ``ALS
Part 2 Rev 4, Section 2 Paragraph 1(1),'' the two digit sequence number
following structural significant item number (i.e., 531103-01) changes
when the inspection area is physically different (i.e., FR16 or FR20).
UAL also commented that ``ALS Part 2 Rev 4'' did not change the ALI
task sequence number or describe any retroactive action if FR20 was the
only side previously inspected using ``ALS Part 2 Rev 3'' or earlier
revisions. UAL stated that it believes this change was overlooked in
``ALS Part 2 Rev 4,'' and as a result, operators may not have been
aware to reset the initial inspection for the ALI for FR16.
The FAA acknowledges the commenter's concern for the FR16
inspection requirement. The FAA has added paragraph (h)(6) to this AD
to include a 30-day grace period as of the effective date of this AD
for airplanes affected by condition ``A'' in ``Table 1: Inspection
Thresholds'' of AD 2018-0289R1. The 30-day grace period prevents
grounding of airplanes that are above the 30,000 total flight cycle
threshold while still allowing for an acceptable level of safety.
Regarding the change in ``ALS part 2 Rev 4,'' the FAA notes that
the description for task 531103-01 to accomplish the inspection for
FR16 and FR20 is specified in ``ALS part 2 Rev 4.'' The change related
to FR16 was also referenced in the record of revision section of ``ALS
part 2.''
Request To Clarify Alternative Method of Compliance (AMOC) Approvals
DAL requested clarification of AMOC approvals as specified in
paragraphs (i)(1)(i) and (ii) of the proposed AD. DAL commented on a
scenario where an AMOC was approved for AD 2019-20-10 for an operator's
entire fleet, which included a deviation to one of the paragraphs in
EASA AD 2018-0289 and a deviation to one of the applicable service
bulletins for correcting an error. DAL commented that because the AMOC
is applicable to the whole fleet, it is possible that the AMOC approval
applies to a manufacturer serial number that is applicable to the
compliance time specified in ``Table 1: Inspection Thresholds,'' Row B,
of EASA AD 2018-0289R1. DAL asked if this particular AMOC still applies
once the final rule becomes effective or is a new AMOC request required
for a deviation to the EASA AD requirements and for the service
bulletin correction?
The FAA agrees to provide clarification. The intent of the
paragraph (i)(1)(i) and (ii) of this AD is to ensure that existing
AMOCs are not inadvertently affected with the new inspection threshold
added in EASA AD 2018-0289R1. It is the operator's responsibility to
consult with the FAA oversight office and the office responsible for
the issuance of an AMOC if AMOC validity is impacted by ``Table 1:
Inspection Thresholds,'' Row B, of EASA AD 2018-0289R1. If an AMOC is
issued to correct service bulletin errors and it is not related to the
inspection threshold change in ``Table 1: Inspection Thresholds,'' Row
B, of EASA AD 2018-0289R1, then it would be applicable to this AD
without further evaluation. The FAA has not changed the AD in this
regard.
Requests To Include or Exclude a Reporting Requirement
UAL requested that the proposed AD include a reporting requirement
for the inspection. UAL stated that it believes no reporting to the
manufacturer is required since it is not a requirement in AD 2019-20-10
or EASA AD 2018-0289R1; however, UAL also noted that Airbus Mandatory
Bulletin A320-53-1339, Revision 01, dated April 7, 2021, contains
reporting in the ``Required for Compliance'' section of the service
bulletin.
DAL requested that the FAA add a statement to paragraph (h) of the
proposed AD exempting operators from any mandatory reporting. DAL
commented that Airbus has issued Mandatory Bulletin A320-53-1339,
Revision 01, dated April 7, 2021, and that paragraph 3.C. of the
service bulletin contains instructions to complete an ``Inspection
Report Sheet'' form and to send the completed form to Airbus. DAL
stated that paragraph 3.C.(8) of Airbus Mandatory Bulletin
[[Page 7035]]
A320-53-1339, Revision 01, dated April 7, 2021, is considered an ``RC''
paragraph, and therefore, reporting the inspection results is
considered mandatory. DAL commented that, typically, reporting is
needed from operators to determine root cause of the issue and that the
root cause of the safety concern is already addressed in previously
issued revisions of the service information.
The FAA agrees to clarify. EASA AD 2018-0289R1 does not include a
reporting requirement that is separate from the reporting to address an
unsafe condition (inspection findings); however EASA AD 2018-0289R1
allows the use of later-approved revisions of the service information,
which includes Airbus Mandatory Service Bulletin A320-53-1339, Revision
01, dated April 7, 2021. Airbus Mandatory Service Bulletin A320-53-
1339, Revision 01, dated April 7, 2021, specifies reporting is
necessary if the cracked intercostal(s) are replaced according to
repair instruction R53113118. The FAA would also like to clarify that
requirements to contact manufacturer to obtain method of compliance
does not require specific reporting requirements and must be complied
with.
The FAA has added paragraph (h)(7) of this AD to clarify that the
reporting specified in paragraph 3.C.(8) of the inspection service
bulletin referenced in EASA AD 2018-0289R1, is required only if the
cracked intercostal(s) have been replaced using repair instruction
R53113118.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety requires adopting this AD as
proposed. Except for minor editorial changes, and any other changes
described previously, this AD is adopted as proposed in the NPRM. None
of the changes will increase the economic burden on any operator.
Accordingly, the FAA is issuing this AD to address the unsafe condition
on these products.
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.
Costs of Compliance
The FAA estimates that this AD affects 1,528 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 33 work-hours x $85 per $0 $2,805 $3,447,345
2019[dash]20[dash]10 (1,229 hour = $2,805.
airplanes).
Inspections........................... 33 work-hours x $85 per 0 2,805 4,286,040
hour = $2,805.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary on-
condition actions 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
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
51 work-hours x $85 per hour = $4,335 (repair).............................. $350 $4,685
1 work-hours x $85 per hour = $85 (reporting)............................... 0 85
----------------------------------------------------------------------------------------------------------------
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 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
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.
[[Page 7036]]
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive (AD) AD 2019-20-10, Amendment 39-
19763 (84 FR 61526, November 13, 2019); and
0
b. Adding the following new AD:
2022-02-11 Airbus SAS: Amendment 39-21908; Docket No. FAA-2021-0501;
Project Identifier MCAI-2021-00168-T.
(a) Effective Date
This airworthiness directive (AD) is effective March 15, 2022.
(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.''
(5) Where paragraph (3) of EASA AD 2018-0289R1 refers to
accomplishing the next due inspection of each repaired affected area
``within the compliance time as specified in, Airbus RDAS, as
applicable,'' for this AD use the applicable compliance time
specified in the repair ``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.''
(6) Where condition ``A'' in Table 1 of EASA AD 2018-0289R1
specifies a compliance time of ``Before exceeding 30[,]000 FC since
aeroplane first flight,'' this AD requires, for the inspection at
frame 16 only, a compliance time of ``Before exceeding 30,000 flight
cycles since airplane's first flight, or within 30 days after the
effective date of this AD, whichever occurs later.''
(7) If the actions in paragraph 3.C.(8) of the inspection
service bulletin referenced in EASA AD 2018-0289R1 specifies to
report all findings, this AD requires reporting if only the cracked
intercostal(s) that have been replaced using repair instruction
R53113118. Report results at the applicable time specified in
paragraph (h)(7)(i) or (ii) of this AD. If operators have reported
findings as part of obtaining any corrective actions approved by
Airbus SAS's European Aviation Safety Agency (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 30 days after the effective date
of 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#ead3c7abbcb9c7aba3b8c7ddd9dac7aba7a5a9aa8c8b8bc48d859c"><span class="__cf_email__" data-cfemail="1e27335f484d335f574c33292d2e335f53515d5e787f7f30797168">[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: 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
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#085b6966626971265a6964606966486e6969266f677e"><span class="__cf_email__" data-cfemail="560537383c372f7804373a3e37381630373778313920">[email protected]</span></a>.
[[Page 7037]]
(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.
(i) European Union Aviation Safety Agency (EASA) AD 2018-0289R1,
dated February 10, 2021.
(ii) [Reserved]
(3) For 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#4c0d083f0c292d3f2d6229393e233c2d622939"><span class="__cf_email__" data-cfemail="c68782b586a3a7b5a7e8a3b3b4a9b6a7e8a3b3">[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#c1a7b3efa8afb2b1a4a2b5a8aeaf81afa0b3a0efa6aeb7"><span class="__cf_email__" data-cfemail="9ef8ecb0f7f0edeefbfdeaf7f1f0def0ffecffb0f9f1e8">[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 January 10, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-02554 Filed 2-7-22; 8:45 am]
BILLING CODE 4910-13-P
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on February 8, 2022.
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.