Rule2022-07859
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
April 14, 2022
Effective
May 19, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2016-17- 12, which applied to all Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2016- 17-12 required inspecting certain trimmable horizontal stabilizer actuators (THSAs) to determine the number of total flight cycles the THSA has accumulated, and replacing the THSA if necessary. Since the FAA issued AD 2016-17-12, the FAA has determined that a more restrictive airworthiness limitations is necessary for carbon friction disks on the no-back brake (NBB) of the THSA. This AD continues to require the inspections of the THSAs and replacement if necessary. This AD also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also limits the installation of affected parts under certain conditions. 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 72 (Thursday, April 14, 2022)</title>
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[Federal Register Volume 87, Number 72 (Thursday, April 14, 2022)]
[Rules and Regulations]
[Pages 22117-22122]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-07859]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0663; Project Identifier MCAI-2020-01618-T;
Amendment 39-21996; AD 2022-07-08]
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) 2016-17-
12, which applied to all Airbus SAS Model A318 series airplanes; Model
A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model
A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2016-
17-12 required inspecting certain trimmable horizontal stabilizer
actuators (THSAs) to determine the number of total flight cycles the
THSA has accumulated, and replacing the THSA if necessary. Since the
FAA issued AD 2016-17-12, the FAA has determined that a more
restrictive airworthiness limitations is necessary for carbon friction
disks on the no-back brake (NBB) of the THSA. This AD continues to
require the inspections of the THSAs and replacement if necessary. This
AD also requires revising the existing maintenance or inspection
program, as applicable, to incorporate new or more restrictive
airworthiness limitations; as specified in a European Union Aviation
Safety Agency (EASA) AD, which is incorporated by reference. This AD
also limits the installation of affected parts under certain
conditions. The FAA is issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective May 19, 2022.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 19,
2022.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
September 30, 2016 (81 FR 58823, August 26, 2016).
ADDRESSES: For EASA material incorporated by reference (IBR) in this
AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany;
telephone +49 221 8999 000; email
[[Page 22118]]
<a href="/cdn-cgi/l/email-protection#0243467142676371632c6777706d72632c6777"><span class="__cf_email__" data-cfemail="8fcecbfccfeaeefceea1eafafde0ffeea1eafa">[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>. For Airbus
service information identified in this final rule, contact Airbus SAS,
Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email <a href="/cdn-cgi/l/email-protection#402123232f352e346e212932372f3234286d252133002129322235336e232f2d"><span class="__cf_email__" data-cfemail="dcbdbfbfb3a9b2a8f2bdb5aeabb3aea8b4f1b9bdaf9cbdb5aebea9aff2bfb3b1">[email protected]</span></a>; internet <a href="https://www.airbus.com">https://www.airbus.com</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-2021-0663. For the UTC Aerospace Systems material identified in
this AD that will not be incorporated by reference, contact Collins
Aerospace, Product Support Department 13, Avenue de L'Eguillette--
Saint-Ouen L'Aumone, Boite Postale 7186 95056 Cergy Pontoise Cedex,
France; telephone 1-877-808-7575; email <a href="/cdn-cgi/l/email-protection#96f5e4f5d6f5f9fafafff8e5b8f5f9fb"><span class="__cf_email__" data-cfemail="0f6c7d6c4f6c60636366617c216c6062">[email protected]</span></a>; internet
<a href="https://www.collinsaerospace.com/support">https://www.collinsaerospace.com/support</a>.
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-2021-0663; 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#e192808f8b8098cf93808d89808fa1878080cf868e97"><span class="__cf_email__" data-cfemail="ccbfada2a6adb5e2beada0a4ada28caaadade2aba3ba">[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 2020-0270, dated December 7, 2020
(EASA AD 2020-0270) (also referred to as 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, -
133, -151N, -153N, and -171N airplanes; Model A320-211, -212, -214, -
215, -216, -231, -232, -233, -251N, -252N, -253N, -271N, -272N, and -
273N airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231,
-232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -271N, -271NX, -
272N, and -272NX 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 2016-17-12, Amendment 39-18625 (81 FR
58823, August 26, 2016) (AD 2016-17-12). AD 2016-17-12 applied to all
Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -
114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214,
-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 August 13, 2021 (86 FR 44663). Since the FAA issued AD
2016-17-12, new investigations determined that the compliance time for
removal from service and replacement of certain carbon friction disks
on the NBB of the THSA must be reduced. This replacement was required
by AD 2016-17-12. This replacement, and newly reduced compliance time,
have now been incorporated into Airbus A318/A319/A320/A321
Airworthiness Limitations Section (ALS) Part 4 Variation 7.1, dated
October 5, 2020, as ALS limitation task 274000-00004-1-E.
The NPRM was prompted by a determination that a more restrictive
airworthiness limitations is necessary for the carbon friction disks on
the NBB of the THSA. The NPRM proposed to retain the requirements of AD
2016-17-12; and also require revising the existing maintenance or
inspection program, as applicable, to incorporate a more restrictive
airworthiness limitations, as specified in EASA AD 2020-0270. The NPRM
also proposed to limit the installation of affected parts under certain
conditions.
The NPRM also specified that revising the existing maintenance or
inspection program, as applicable, to incorporate the more restrictive
airworthiness limitation would terminate the ALS limitation task
274000-00004-1-E for the THSA, as required by paragraph (i) of AD 2020-
21-10, Amendment 39-21283 (85 FR 65190, October 15, 2020) (AD 2020-21-
10). The new airworthiness limitation for ALS limitation task 274000-
00004-1-E specified in the NPRM reduces the compliance times and
expands the applicability for the task.
The FAA is issuing this AD to address premature wear of the carbon
friction disks on the no-back brake (NBB) of the THSA, which could lead
to reduced braking efficiency in certain load conditions, and, in
conjunction with the inability of the power gear train to keep the ball
screw in its last commanded position, could result in uncommanded
movements of the trimmable horizontal stabilizer and loss of control of
the airplane. See the MCAI for additional background information.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from two commenters, including Air Line
Pilots Association, International (ALPA) and United Airlines, who
supported the NPRM without change.
The FAA received additional comments from two commenters, including
Alaska Airlines (Alaska) and Delta Air Lines (Delta). The following
presents the comments received on the NPRM and the FAA's response to
each comment.
Request To Remove Paragraph (m)(7) of the Proposed AD
Alaska and Delta requested removal of paragraph (m)(7) of the
proposed AD. Alaska stated that removing paragraph (m)(7) of the
proposed AD would alleviate any confusion that would result from the
FAA's exception to the EASA AD, and would also address any burden on
U.S. operators having leased airplanes that have a return condition
that those airplanes are in compliance with both the FAA and EASA's AD.
Alaska noted that the vendor service bulletin, UTC Service Bulletin
47145-27-17, must be used for the NBB carbon disk replacement on a THSA
assembly and referred to the Accomplishment Instructions of Airbus
Service Bulletin A320-27-1242, which states to ``send to the supplier
the THSA (FIN 9CE) for modification in accordance with'' the vendor
service bulletin. Delta added that the airworthiness limitations
section (ALS) variation references the UTC service information. Delta
noted that a similar exception was not included in AD 2020-21-10,
Amendment 39-21283 (85 FR 65190, October 15, 2020) (AD 2020-21-10), so
it should not be added now. Delta also stated that paragraph (l)(2) of
the proposed AD could be affected if
[[Page 22119]]
paragraph (m)(7) of the proposed AD is removed.
The FAA disagrees. ALS limitation task 274000-00004-1-E specifies
that the replacement can be done using ``SB A320-27-1242 or VSB [vendor
service bulletin] 47145-27-17.'' The exception stated in paragraph
(m)(7) of this AD removes the allowance in ALS limitation task 274000-
00004-1-E to use only the UTC service information (``VSB 47145-27-17'')
as a means to show compliance with the requirements of this AD. The UTC
service information referred to certain information on testing and
fault isolation as a source of information, but did not require doing
those tests, which would have led to compliance being voluntary for
those actions. The Airbus service information (``SB A320-27-1242'')
contains more complete instructions for operators to comply with as
previously required in AD 2016-17-12. Although a similar exception was
not included in AD 2020-21-10 for ALS limitation task 274000-00004-1-E,
the FAA has determined that this exception is necessary and must be
included for the purposes of enforcing the AD requirements for U.S.-
registered operators. As part of the rulemaking process for FAA ADs
that correspond to ADs issued by other States of Design, the FAA
determines if the MCAI ADs adequately address the identified unsafe
condition or if exceptions are needed in order to address the unsafe
condition. The FAA has not changed this AD in this regard.
Request To Revise Paragraph (b) of the Proposed AD
Delta requested that paragraph (b) of the proposed AD be revised
from replacing AD 2016-17-12 to affecting AD 2016-17-12, and
subsequently remove paragraphs (g) through (k) of the proposed AD that
would retain AD 2016-17-12 requirements and then revise the terminating
action paragraph to state that doing the actions of the proposed AD
would terminate all requirements of AD 2016-17-12. Delta believed the
changes would simplify the AD and clarify how to comply with the
proposed requirements.
The FAA disagrees. In this case, the FAA determined that the
supersedure method used in this AD would be the most effective for AD
2016-17-12 because the existing actions and the new changes related to
those actions are within the same AD. The FAA has not changed this AD
in this regard.
Request To Revise the Applicability
Delta requested that the applicability specified in paragraph (c)
of the proposed AD be revised to affect only airplanes that have an
original airworthiness certificate or original export airworthiness
certificate issued on or before the date of the airworthiness
limitations publication required. Delta pointed out that the FAA has
published ADs with the requested language because airplanes with a
later date are delivered with the required publication. Delta stated
that for compliance with AD 2016-17-12, it needed to request an
alternative method of compliance (AMOC) to use later revisions of the
referenced airworthiness limitation documents because that AD did not
have a cut-off date. Delta also stated that if its request for
paragraph (c) of the proposed AD is granted, then the wording for
paragraph (l) of the proposed AD would also be affected.
The FAA agrees that in most ADs that affect airworthiness
limitations and reference airworthiness publications, the publication's
date is used as a means of defining or limiting the group of airplanes
based on its latest type design requirements. However, in this case,
changing paragraph (c) of this AD would conflict with the requirements
of AD 2016-17-12, which applied to all airplanes. Paragraph (c) of this
AD has not been changed in this regard. However, the FAA has added
paragraph (p)(1)(ii) to this AD to clarify the previously approved
AMOCs for AD 2016-17-12 are approved as AMOCs to the corresponding
retained requirements of this AD.
Request To Revise Paragraph (o) of the Proposed AD
Delta stated that the terminating action statement in paragraph (o)
of the proposed AD should be deleted because paragraph (k) of the
affected AD, AD 2020-21-10, contains a provision to allow alternative
actions and intervals if approved by certain provisions in EASA AD
2020-0034, dated February 25, 2020. Delta also pointed out that the
task specified in paragraph (o) of the proposed AD is only for certain
airplanes, so those airplanes should be listed in paragraph (o) of the
proposed AD.
The FAA disagrees with the statement that paragraph (o) of this AD
should be deleted. The terminating action statement in paragraph (o) of
this AD provides relief to operators, and avoids duplication and
possible conflicting requirements. If paragraph (o) of this AD is
removed, there would be two FAA ADs in effect that would require the
same task and operators would be required to show compliance with both
ADs for the same task with variable requirements. Paragraph (k) of AD
2020-21-10 provides provisions for alternative actions and intervals
for paragraph (i) of AD 2020-21-10, but does not mandate the
alternative method. The FAA has changed paragraph (o) of this AD to
remove reference to the models and to the issuance date of original
airworthiness certificate or original export certificate of
airworthiness as not all models referenced in paragraph (o) of the
proposed AD are in AD 2020-21-10. The models and the issuance date of
the original airworthiness certificate or original export certificate
of airworthiness specified in AD 2020-21-10 do not need to be
referenced in paragraph (o) of this AD.
Request To Revise Process for Requiring Airworthiness Limitations
Delta suggested that the FAA consider revising FAA regulations to
incorporate a requirement for commercial operators to incorporate and
use new revisions of airworthiness limitation (AWL) or ALS documents
within a certain time after those revisions are published. Delta
believed that this change to the regulations would eliminate the need
to issue ADs, simplify airworthiness limitations requirements for
operators, and reduce operator taskloads in determining if they are in
compliance with ADs or need to request an AMOC. Delta stated that there
are usually two or three ADs a year that are published on ALS tasks for
Model A320 airplanes.
While the FAA understands the commenter's concern, current FAA
regulations require incorporating the latest ALS included in the type
design of the airplane, such as 14 CFR 91.403(c) and 91.409(e). ADs are
the only viable method to mitigate risk identified in a product when
its type design did not require incorporation of the latest ALS
document, as applicable, by mandating subsequent ALS revisions or
variations at the applicable thresholds. The FAA's regulatory
requirements are promulgated via notice-and-comment rulemaking as
required by the Administrative Procedure Act (APA), and the public can
petition for rulemaking pursuant to 14 CFR part 11.
Explanation of Change to Paragraph (m)(7) of the Proposed AD
The FAA has revised paragraph (m)(7) of this AD to clarify the
location of the Note and to revise the format.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety requires
[[Page 22120]]
adopting this AD as proposed. Except for minor editorial changes and
any other change 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 2020-0270 describes new or more restrictive airworthiness
limitations for airplane structures and safe life limits.
This AD also requires Airbus Service Bulletin A320-27-1242,
Revision 01, dated February 4, 2016, which the Director of the Federal
Register approved for incorporation by reference as of September 30,
2016 (81 FR 58823, August 26, 2016).
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 1,630 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 2016-17-12 1 work-hour x $85 per $0 $85 $81,515
(959 airplanes). hour = $85.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting/revising the existing maintenance or inspection program.
The FAA has determined that revising the existing maintenance or
inspection program takes an average of 90 work-hours per operator,
although the agency recognizes that this number may vary from operator
to operator. Since operators incorporate maintenance or inspection
program changes for their affected fleet(s), the FAA has determined
that a per-operator estimate is more accurate than a per-airplane
estimate.
The FAA estimates the total cost per operator for the new actions
to be $7,650 (90 work-hours x $85 per work-hour).
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
----------------------------------------------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
21 work-hours x $85 per hour = $1,785......................................... $26,500 $28,285
----------------------------------------------------------------------------------------------------------------
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,
(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) 2016-17-12, Amendment 39-18625
(81 FR 58823, August 26, 2016); and
0
b. Adding the following new AD:
2022-07-08 Airbus SAS: Amendment 39-21996; Docket No. FAA-2021-0663;
Project Identifier MCAI-2020-01618-T.
(a) Effective Date
This airworthiness directive (AD) is effective May 19, 2022.
(b) Affected ADs
(1) This AD replaces AD 2016-17-12, Amendment 39-18625 (81 FR
58823, August 26, 2016) (AD 2016-17-12).
(2) This AD affects AD 2020-21-10, Amendment 39-21283 (85 FR
65190, October 15, 2020) (AD 2020-21-10).
[[Page 22121]]
(c) Applicability
This AD applies to all Airbus SAS airplanes, certificated in any
category, identified in paragraphs (c)(1) through (7) of this AD.
(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.
(5) Model A319-151N, -153N, and -171N airplanes.
(6) Model A320-251N, -252N, -253N, -271N, -272N, and -273N
airplanes.
(7) Model A321-251N, -251NX, -252N, -252NX, -253N, -253NX, -
271N, -271NX, -272N, and -272NX airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 05, Time Limits/
Maintenance Checks; 27, Flight Controls.
(e) Reason
This AD was prompted by a determination that a more restrictive
airworthiness limitation is necessary for the carbon friction disks
on the no-back brake (NBB) of the trimmable horizontal stabilizer
actuator (THSA). The FAA is issuing this AD to address premature
wear of the carbon friction disks on the NBB of the THSA, which
could lead to reduced braking efficiency in certain load conditions,
and, in conjunction with the inability of the power gear train to
keep the ball screw in its last commanded position, could result in
uncommanded movements of the trimmable horizontal stabilizer and
loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection To Determine THSA Part Number and Accumulated
Total Flight Cycles, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2016-17-12, with no changes. For airplanes identified in paragraphs
(c)(1) through (4) of this AD: No later than each date specified in
paragraphs (g)(1) through (5) of this AD, inspect the THSA to
determine if it has a part number (P/N) 47145-(XXX), and, if any
THSA P/N 47145-(XXX) is found, determine the total number of flight
cycles accumulated since the THSA's first installation on an
airplane, or since the most recent NBB replacement, whichever is
later. A review of airplane delivery or maintenance records is
acceptable in lieu of this inspection if the part number of the THSA
can be conclusively determined from that review. In case maintenance
records concerning the most recent NBB disk replacement are
unavailable or incomplete, the total flight cycles accumulated since
first installation of the THSA on an airplane apply. Accomplishing
the maintenance or inspection program revision required by paragraph
(l) of this AD terminates the requirements of this paragraph.
(1) As of September 30, 2016 (the effective date of AD 2016-17-
12): The THSA flight-cycle limit (since first installation on an
airplane, or since the most recent NBB replacement, whichever is
later) is 40,000 total flight cycles.
(2) As of December 31, 2016: The THSA flight-cycle limit (since
first installation on an airplane, or since the most recent NBB
replacement, whichever is later) is 36,000 total flight cycles.
(3) As of December 31, 2017: The THSA flight-cycle limit (since
first installation on an airplane, or since the most recent NBB
replacement, whichever is later) is 33,600 total flight cycles.
(4) As of December 31, 2018: The THSA flight-cycle limit (since
first installation on an airplane, or since the most recent NBB
replacement, whichever is later) is 31,600 total flight cycles.
(5) As of December 31, 2019: The THSA flight-cycle limit (since
first installation on an airplane, or since the most recent NBB
replacement, whichever is later) is 30,000 total flight cycles.
(h) Retained Replacements, With No Changes
This paragraph restates the requirements of paragraph (h) of AD
2016-17-12, with no changes. For airplanes identified in paragraphs
(c)(1) through (4) of this AD: For airplanes with any THSA P/N
47145-(XXX), do the replacements required by paragraphs (h)(1) and
(2) of this AD. Accomplishing the maintenance or inspection program
revision required by paragraph (l) of this AD terminates the
requirements of this paragraph.
(1) No later than each date specified in paragraphs (g)(1)
through (5) of this AD, replace all THSA that have reached or
exceeded on each date the corresponding number of flight cycles
specified in paragraphs (g)(1) through (5) of this AD. Do the
replacement in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-27-1242, Revision 01, dated February 4,
2016. Affected THSAs must be replaced with serviceable THSAs.
(2) As of each date specified in paragraphs (g)(1) through (5)
of this AD, and before exceeding the flight cycle limit
corresponding to each date, as applicable: Replace each THSA with a
serviceable THSA, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A320-27-1242, Revision 01, dated February
4, 2016.
(i) Retained Definition of Serviceable THSA, With No Changes
This paragraph restates the definition of paragraph (i) of AD
2016-17-12, with no changes. For airplanes identified in paragraphs
(c)(1) through (4) of this AD: For the purposes of this AD, a
serviceable THSA is a THSA that has not exceeded the applicable
flight-cycle limits, as specified paragraphs (g)(1) through (5) of
this AD, since first installation of the THSA on an airplane or
since last NBB replacement, whichever is later.
Note 1 to paragraph (i): Guidance for NBB disk replacement can
be found in UTC Aerospace Systems Service Bulletin 47145-27-17,
Revision 1, dated July 21, 2015.
(j) Retained Parts Installation Limitation, With No Changes
This paragraph restates the provisions of paragraph (j) of AD
2016-17-12, with no changes. For airplanes identified in paragraphs
(c)(1) through (4) of this AD: As of each date specified in
paragraphs (g)(1) through (5) of this AD, as applicable, only
installation of a serviceable THSA P/N 47145-(XXX) is allowed on an
airplane. Accomplishing the maintenance or inspection program
revision required by paragraph (l) of this AD terminates the
requirements of this paragraph.
(k) Retained Credit for Previous Actions, With No Changes
This paragraph restates the requirements of paragraph (k) of AD
2016-17-12, with no changes. For airplanes identified in paragraphs
(c)(1) through (4) of this AD: This paragraph provides credit for
actions required by paragraph (h) of this AD, if those actions were
performed before September 30, 2016 (the effective date of AD 2016-
17-12), using Airbus Service Bulletin A320-27-1242, dated February
9, 2015.
(l) New Maintenance or Inspection Program Revision
(1) For the airplanes identified in paragraph (c) of this AD
with an original airworthiness certificate or original export
certificate of airworthiness issued on or before October 5, 2020,
except as specified in paragraph (m) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, European Union Aviation Safety Agency (EASA) AD
2020-0270, dated December 7, 2020 (EASA AD 2020-0270). Accomplishing
the maintenance or inspection program revision required by this
paragraph terminates the requirements of paragraphs (g), (h), and
(j) of this AD.
(2) For the airplanes identified in paragraph (c) of this AD
with an original airworthiness certificate or original export
certificate of airworthiness issued after October 5, 2020, revise
the existing maintenance or inspection program, as applicable, to
incorporate the provision specified in paragraph (m)(7) of this AD.
(m) Exceptions to EASA AD 2020-0270
(1) Where EASA AD 2020-0270 refers to its effective date, this
AD requires using the effective date of this AD.
(2) The requirements specified in paragraphs (1) and (2) of EASA
AD 2020-0270 do not apply to this AD.
(3) Paragraph (3) of EASA AD 2020-0270 specifies revising ``the
approved AMP'' within 12 months after its effective date, but this
AD requires revising the existing maintenance or inspection program,
as applicable, within 90 days after the effective date of this AD.
(4) The initial compliance time for doing the tasks specified in
paragraph (3) of EASA AD 2020-0270 is at the applicable
``limitations'' as incorporated by the requirements of paragraph (3)
of EASA AD
[[Page 22122]]
2020-0270, or within 90 days after the effective date of this AD,
whichever occurs later.
(5) The provisions specified in paragraph (4) of EASA AD 2020-
0270 do not apply to this AD.
(6) The ``Remarks'' section of EASA AD 2020-0270 does not apply
to this AD.
(7) For all airplanes identified in paragraph (c) of this AD:
Where the Note for Item 274000-00004-1-E of Section 4-1 in the
service information referenced in EASA AD 2020-0270 specifies ``NBB
carbon disc replacement'' instructions, for this AD, replace the
text ``NBB carbon disc replacement can be accomplished in accordance
with SB A320-27-1242 or VSB 47145-27-17,'' with ``NBB carbon disk
replacement must be accomplished in accordance with SB A320-27-
1242.''
(n) New Provisions for Alternative Actions and Intervals
After the existing maintenance or inspection program has been
revised as required by paragraph (l) of this AD, no alternative
actions (e.g., inspections) or intervals are allowed unless they are
approved as specified in the provisions of the ``Ref. Publications''
section of EASA AD 2020-0270.
(o) Terminating Action for Certain Requirements of AD 2020-21-10
Accomplishing the actions required by this AD terminates the
airworthiness limitations section (ALS) limitation task 274000-
00004-1-E for the THSA, as required by paragraph (i) of AD 2020-21-
10.
(p) 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 (q)(1) of
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#4e77630f181d630f071c63797d7e630f03010d0e282f2f60292138"><span class="__cf_email__" data-cfemail="0a33274b5c59274b4358273d393a274b4745494a6c6b6b246d657c">[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 2016-17-12 are approved as
AMOCs for the corresponding provisions of paragraphs (g) through (j)
of this AD
(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 (p)(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.
(q) Related Information
(1) 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#7b081a15111a0255091a17131a153b1d1a1a551c140d"><span class="__cf_email__" data-cfemail="cebdafa0a4afb7e0bcafa2a6afa08ea8afafe0a9a1b8">[email protected]</span></a>.
(2) For UTC Aerospace Systems service information identified in
this AD that is not incorporated by reference, contact Collins
Aerospace, Product Support Department 13, Avenue de L'Eguillette--
Saint-Ouen L'Aumone, Boite Postale 7186 95056 Cergy Pontoise Cedex,
France; telephone 1-877-808-7575; email <a href="/cdn-cgi/l/email-protection#e2819081a2818d8e8e8b8c91cc818d8f"><span class="__cf_email__" data-cfemail="a0c3d2c3e0c3cfccccc9ced38ec3cfcd">[email protected]</span></a>; internet
<a href="https://www.collinsaerospace.com/support">https://www.collinsaerospace.com/support</a>.
(r) 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
May 19, 2022.
(i) European Union Aviation Safety Agency (EASA) AD 2020-0270,
dated December 7, 2020.
(ii) [Reserved]
(4) The following service information was approved for IBR on
September 30, 2016 (81 FR 58823, August 26, 2016).
(i) Airbus Service Bulletin A320-27-1242, Revision 01, dated
February 4, 2016.
(ii) [Reserved]
(5) For EASA AD 2020-0270, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#3f7e7b4c7f5a5e4c5e115a4a4d504f5e115a4a"><span class="__cf_email__" data-cfemail="8fcecbfccfeaeefceea1eafafde0ffeea1eafa">[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>.
(6) For Airbus service information, contact Airbus SAS,
Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93
44 51; email <a href="/cdn-cgi/l/email-protection#5c3d3f3f33293228723d352e2b332e283471393d2f1c3d352e3e292f723f3331"><span class="__cf_email__" data-cfemail="f697959599839882d8979f84819984829edb939785b6979f84948385d895999b">[email protected]</span></a>; internet <a href="https://www.airbus.com">https://www.airbus.com</a>.
(7) 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.
(8) 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 March 18, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-07859 Filed 4-13-22; 8:45 am]
BILLING CODE 4910-13-P
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