Rule2022-27399
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
December 19, 2022
Effective
January 23, 2023
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2020-18- 04, which applied to Airbus SAS Model A350-941 and -1041 airplanes. AD 2020-18-04 required a one-time health check of the slat power control unit (PCU) torque sensing unit (TSU) for discrepancies, and corrective actions if necessary; a detailed inspection of the left-hand (LH) and right-hand (RH) slat transmission systems for discrepancies, and corrective actions if necessary; and LH and RH track 12 slat gear rotary actuator (SGRA) water drainage and vent plug cleaning (which includes an inspection for moisture). This AD was prompted by a determination that requiring modification of the PCU by replacing each affected slat PCU with a serviceable PCU (one having a different part number) is necessary. This AD continues to require the actions required by AD 2020-18-04, and also requires modification (replacement of each affected slat PCU with a slat PCU having a different part number), and revising the limitations on the installation of affected parts; 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 242 (Monday, December 19, 2022)</title>
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[Federal Register Volume 87, Number 242 (Monday, December 19, 2022)]
[Rules and Regulations]
[Pages 77497-77500]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-27399]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0833; Project Identifier MCAI-2021-00245-T;
Amendment 39-22258; AD 2022-25-02]
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) 2020-18-
04, which applied to Airbus SAS Model A350-941 and -1041 airplanes. AD
2020-18-04 required a one-time health check of the slat power control
unit (PCU) torque sensing unit (TSU) for discrepancies, and corrective
actions if necessary; a detailed inspection of the left-hand (LH) and
right-hand (RH) slat transmission systems for discrepancies, and
corrective actions if necessary; and LH and RH track 12 slat gear
rotary actuator (SGRA) water drainage and vent plug cleaning (which
includes an inspection for moisture). This AD was prompted by a
determination that requiring modification of the PCU by replacing each
affected slat PCU with a serviceable PCU (one having a different part
number) is necessary. This AD continues to require the actions required
by AD 2020-18-04, and also requires modification (replacement of each
affected slat PCU with a slat PCU having a different part number), and
revising the limitations on the installation of affected parts; 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 January 23, 2023.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 23,
2023.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2021-0833; 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.
Material Incorporated by Reference:
<bullet> For EASA material incorporated by reference 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#1a5b5e695a7f7b697b347f6f68756a7b347f6f"><span class="__cf_email__" data-cfemail="b0f1f4c3f0d5d1c3d19ed5c5c2dfc0d19ed5c5">[email protected]</span></a>; website easa.europa.eu. You
may find this material on the EASA website at ad.easa.europa.eu.
<bullet> 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="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2021-0833.
FOR FURTHER INFORMATION CONTACT: Dat Le, Aerospace Engineer, Large
Aircraft Section, FAA, International Validation Branch, 2200 South
216th St., Des Moines, WA 98198; telephone 516-228-7317; email
<a href="/cdn-cgi/l/email-protection#6c080d18421a4200092c0a0d0d420b031a"><span class="__cf_email__" data-cfemail="482c293c663e66242d082e2929662f273e">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2020-18-04, Amendment 39-21225 (85 FR
54896, September 3, 2020) (AD 2020-18-04). AD 2020-18-04 applied to all
Airbus SAS Model A350-941 and -1041 airplanes. AD 2020-18-04 required a
one-time health check of the slat PCU TSU for discrepancies, and
corrective actions if necessary; a detailed inspection of the LH and RH
slat transmission systems for discrepancies, and corrective actions if
necessary; and LH and RH track 12 SGRA water drainage and vent plug
cleaning (which includes an inspection for moisture). The FAA issued AD
2020-18-04 to address a slat system jam during landing phase which
could lead to a double shaft disconnection or rupture, potentially
causing one or more slat surfaces to be no longer connected to either
the slat wing tip brake or the slat PCU, possibly resulting in reduced
control of the airplane.
The NPRM published in the Federal Register on September 30, 2021
(86 FR 54136). The NPRM was prompted by AD 2021-0053R1, dated April 19,
2021, issued by European Union Aviation Safety Agency (referred to
after this as the MCAI). The MCAI states that since EASA AD 2020-
0163R1, dated August 7, 2020 (which corresponds to FAA AD 2020-18-04),
was issued, EASA received information that prompted it to add a
requirement for repetitive TSU health checks, introduce a definition of
serviceable part to clarify actions that have to be accomplished on
affected parts, and remove a requirement for a water drainage and vent
plug cleaning of the LH and RH track 12 SGRA.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2021-0833.
In the NPRM, the FAA proposed to remove a requirement for water
drainage and vent plug cleaning of the SGRA, require repetitive health
checks of the slat PCU TSU, a detailed visual inspection of the slat
transmission systems, and corrective actions if necessary, as specified
in EASA AD 2020-0163R1.
The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 to supersede AD 2020-18-04. The SNPRM published
in the Federal Register on June 1, 2022 (87 FR 33076) (the SNPRM). The
SNPRM was prompted by EASA issuance of AD 2021-0275, dated December 10,
2021, (EASA AD 2021-0275), which determined that requiring modification
of the PCU by replacing each affected slat PCU with a serviceable PCU
(one having a different part number) is necessary, and clarified the
limitations related to when an affected slat PCU may be installed on an
airplane. In the SNPRM, the FAA proposed to require modification
(replacement of each affected slat PCU with a slat PCU having a
different part number), requiring an inspection report, and revising
the limitations on the installation of affected parts. The FAA is
issuing this AD to address a slat system jam during landing, which
could lead to a double shaft disconnection/rupture, potentially causing
one or more
[[Page 77498]]
slat surfaces to be no longer connected to either the slat wing tip
brake or the slat PCU, possibly resulting in reduced control of the
airplane.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from Delta Air Lines (Delta). The
following presents the comments received on the SNPRM and the FAA's
response to each comment.
Request for Removing the Initial Health Check Requirement
Delta requested that the terminating action (modification of the
PCU) specified in paragraph (6) of EASA AD 2021-0275 for the repetitive
health checks in paragraph (4) of EASA AD 2021-0275 be extended to the
initial health check specified in paragraph (2) of EASA AD 2021-0275
too. Delta noted that it seems that the health checks are intended only
for those slats that have not been modified. Delta stated that for a
modified PCU, a detailed inspection (as specified in paragraph (1) of
EASA AD 2021-0275) is required and that an initial health check would
not reveal further information or instruction. Delta added that the
detailed inspection and initial health check have the same compliance
time. Delta recommended revising paragraph (h) of the proposed AD (in
the SNPRM) to permit the terminating action to be used for the initial
health check too.
The FAA agrees to the request for the reasons that Delta provided.
The FAA has revised paragraph (h) of this AD to provide terminating
action for the initial health check.
Request for Removal of the Reporting Requirement
Delta requested removing the requirement to send inspection reports
to Airbus. Delta pointed out that Airbus provided a modification that
terminates inspection requirements. Delta noted also that if there are
findings that require a request for repair instruction, the operator
would need to provide details of the discrepancies before receiving
repair instructions. Delta recommended revising paragraph (h) of
proposed AD (in the SNPRM) to remove the reporting requirement and
state that reporting is not required.
The FAA agrees with the request for the reasons stated. The FAA has
revised paragraph (h) of this AD and the Cost of Compliance and Related
Service Information Under 1 CFR part 51 sections of this AD
accordingly; and added paragraph (i) to this AD to state that
inspection reports are not required.
Conclusion
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 this State of Design Authority, it
has notified the FAA of the unsafe condition described in the MCAI
referenced above. The FAA reviewed the relevant data, considered the
comments received, and determined that air safety requires adopting
this AD as proposed. Accordingly, the FAA is issuing this AD to address
the unsafe condition on this product. Except for minor editorial
changes, and any other changes described previously, this AD is adopted
as proposed in the SNPRM. None of the changes will increase the
economic burden on any operator.
Related Service Information Under 1 CFR Part 51
EASA AD 2021-0275 specifies procedures for repetitive health checks
of the slat PCU TSU for discrepancies, and corrective actions
(replacement) if necessary; a detailed visual inspection of the LH and
RH slat transmission systems for discrepancies, and corrective actions
(repair) if necessary; and a modification of the PCU (replacement of
each slat PCU having part number (P/N) 4785A0000-04 or 4785A0000-05
with a slat PCU having P/N 4785A0000-06), which terminates the health
checks. EASA AD 2021-0275 also specifies limitations for installing
affected slat PCUs. 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.
Interim Action
The preamble to AD 2020-18-04 explains that the FAA considers those
requirements ``interim action'' and that the manufacturer is developing
a final action to address the unsafe condition. That AD explains that
the FAA might consider further rulemaking if a final action is
identified. The same explanation was in the preamble of the NPRM. Since
the FAA issued AD 2020-18-04 and the NPRM, the manufacturer has
developed a modification to the PCU, and the FAA has determined that
further rulemaking is indeed necessary; this AD follows from that
determination.
Costs of Compliance
The FAA estimates that this AD affects 15 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 40 work-hours x $85 per hour = Up $275,300 Up to $278,700............ Up to $4,180,500.
to $3,400.
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs 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.
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.
[[Page 77499]]
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,
(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 2020-18-04, Amendment 39-21225 (85
FR 54896, September 3, 2020); and
0
b. Adding the following new airworthiness directive:
2022-25-02 Airbus SAS: Amendment 39-22258; Docket No. FAA-2021-0833;
Project Identifier MCAI-2021-00245-T.
(a) Effective Date
This airworthiness directive (AD) is effective January 23, 2023.
(b) Affected ADs
This AD replaces AD 2020-18-04, Amendment 39-21225 (85 FR 54896,
September 3, 2020) (AD 2020-18-04).
(c) Applicability
This AD applies to all Airbus SAS Model A350-941 and -1041
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Reason
This AD was prompted by a report of a slat system jam during
landing, the determination that health checks must be repetitive to
monitor torque sensor unit (TSU) wear, and the development of a
modification that terminates the health checks. The FAA is issuing
this AD to address a slat system jam during landing, which could
lead to a double shaft disconnection/rupture, potentially causing
one or more slat surfaces to be no longer connected to either the
slat wing tip brake or the slat power control unit (PCU), possibly
resulting in reduced control 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
2021-0275, dated December 10, 2021 (EASA AD 2021-0275).
(h) Exceptions to EASA AD 2021-0275
(1) Where EASA AD 2021-0275 refers to March 11, 2021 (the
effective date of EASA AD 2021-0053, dated February 25, 2021), this
AD requires using the effective date of this AD.
(2) Where paragraph (2) of EASA AD 2021-0275 specifies
compliance times for accomplishment of certain actions, replace the
text ``but not exceeding the compliance time for the repeat health
check as determined in accordance with the instructions of AOT
[Alert Operators Transmission] A27P015-20, or AOT A27P016-20,'' with
``but within the applicable compliance time specified in paragraph
4.2.3.1 of AOT A27P015-20; or 4.2.2.2.2 or 4.2.2.3.2 of AOT A27P016-
20; as applicable.''
(3) Where paragraph (4) of EASA AD 2021-0275 specifies
``Appendix 5 of the AOT,'' use ``the Appendix labeled TSU Condition
Check Flowchart of the AOT.''
(4) Where note 2 of EASA AD 2021-0275 states that the
certificate of release accompanying a replacement part ``will
clarify,'' use ``may be used to clarify.''
(5) The ``Remarks'' section of EASA AD 2021-0275 does not apply
to this AD.
(6) Where EASA AD 2021-0275 refers to its effective date, this
AD requires using the effective date of this AD.
(7) Where paragraph (7) of EASA AD 2021-0275 states that the
modification specified in paragraph (6) of EASA AD 2021-0275 is
terminating action for paragraph (4) of EASA AD 2021-0275, this AD
considers accomplishing the modification specified in paragraph (6)
of EASA AD 2021-0275 to also be terminating action for the initial
health check specified in paragraph (2) of EASA AD 2021-0275.
(i) No Reporting Requirement
Although the service information referenced in EASA AD 2021-0275
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
(j) 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 (k) of this
AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#ab9286eafdf886eae2f9869c989b86eae6e4e8ebcdcaca85ccc4dd"><span class="__cf_email__" data-cfemail="9ea7b3dfc8cdb3dfd7ccb3a9adaeb3dfd3d1dddef8ffffb0f9f1e8">[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): Except as required by
paragraph (j)(2) of this AD, if any service information referenced
in EASA AD 2021-0275 contains paragraphs that are labeled as RC, the
instructions in RC paragraphs, including subparagraphs under an RC
paragraph, must be done to comply with this AD; any paragraphs,
including subparagraphs under those paragraphs, that are not
identified as RC are recommended. The instructions in paragraphs,
including subparagraphs under those paragraphs, 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 instructions identified as RC can
be done and the airplane can be put back in an airworthy condition.
Any substitutions or changes to instructions identified as RC
require approval of an AMOC.
(k) Additional Information
For more information about this AD, contact Dat Le, Aerospace
Engineer, Large Aircraft Section, FAA, International Validation
Branch, 2200 South 216th St., Des Moines, WA 98198; telephone 516-
228-7317; email <a href="/cdn-cgi/l/email-protection#cbafaabfe5bde5a7ae8badaaaae5aca4bd"><span class="__cf_email__" data-cfemail="9df9fce9b3ebb3f1f8ddfbfcfcb3faf2eb">[email protected]</span></a>.
(l) 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.
(3) The following service information was approved for IBR on
January 23, 2023.
(i) European Union Aviation Safety Agency (EASA) AD 2021-0275,
dated December 10, 2021.
[[Page 77500]]
(ii) [Reserved]
(4) For EASA AD 2021-0275, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#68292c1b280d091b09460d1d1a071809460d1d"><span class="__cf_email__" data-cfemail="a4e5e0d7e4c1c5d7c58ac1d1d6cbd4c58ac1d1">[email protected]</span></a>; website easa.europa.eu. You may find this EASA
AD on the EASA website at ad.easa.europa.eu.
(5) 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.
(6) 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#accade82c5c2dfdcc9cfd8c5c3c2ecc2cddecd82cbc3da"><span class="__cf_email__" data-cfemail="c3a5b1edaaadb0b3a6a0b7aaacad83ada2b1a2eda4acb5">[email protected]</span></a>, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued on November 28, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-27399 Filed 12-16-22; 8:45 am]
BILLING CODE 4910-13-P
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