[Federal Register Volume 86, Number 154 (Friday, August 13, 2021)]
[Proposed Rules]
[Pages 44663-44668]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-17091]


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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]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2016-17-12, which applies 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 requires 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 new or more restrictive airworthiness limitations are necessary. 
This proposed AD would require 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 proposed for incorporation 
by reference. The FAA is proposing this AD to address the unsafe 
condition on these products.

DATES: The FAA must receive comments on this proposed AD by September 
27, 2021.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
    <bullet> Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For EASA material that will be 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#58191c2b183d392b39763d2d2a372839763d2d"><span class="__cf_email__" data-cfemail="6f2e2b1c2f0a0e1c0e410a1a1d001f0e410a1a">[email protected]</span></a>; internet 
www.easa.europa.eu. You may find this IBR material on the EASA website 
at https://ad.easa.europa.eu. For Airbus service information identified 
in this proposed AD, 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#3f5e5c5c504a514b115e564d48504d4b57125a5e4c7f5e564d5d4a4c115c5052"><span class="__cf_email__" data-cfemail="e786848488928993c9868e95908895938fca828694a7868e95859294c984888a">[email protected]</span></a>; internet https://www.airbus.com. You 
may view this IBR material at the FAA, Airworthiness Products Section, 
Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 206-
231-3195. It is also available in the AD docket on the internet at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2021-0663. For the UTC Aerospace Systems material identified in 
this proposed 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#771405143714181b1b1e19045914181a"><span class="__cf_email__" data-cfemail="4c2f3e2f0c2f23202025223f622f2321">[email protected]</span></a>; internet https://www.collinsaerospace.com/support.

Examining the AD Docket

    You may examine the AD docket on the internet at https://

[[Page 44664]]

www.regulations.gov 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 NPRM, any comments received, and other information. The street 
address for Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
Large Aircraft Section, International Validation Branch, FAA, 2200 
South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223; 
email <a href="/cdn-cgi/l/email-protection#7300121d19120a5d01121f1b121d331512125d141c05"><span class="__cf_email__" data-cfemail="7300121d19120a5d01121f1b121d331512125d141c05">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2021-0663; Project Identifier 
MCAI-2020-01618-T'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
the proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this proposed AD.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to 
Sanjay Ralhan, Aerospace Engineer, Large Aircraft Section, 
International Validation Branch, FAA, 2200 South 216th St., Des Moines, 
WA 98198; telephone and fax 206-231-3223; email <a href="/cdn-cgi/l/email-protection#7506141b1f140c5b0714191d141b351314145b121a03"><span class="__cf_email__" data-cfemail="6e1d0f00040f17401c0f02060f002e080f0f40090118">[email protected]</span></a>. 
Any commentary that the FAA receives which is not specifically 
designated as CBI will be placed in the public docket for this 
rulemaking.

Background

    The FAA issued AD 2016-17-12, Amendment 39-18625 (81 FR 58823, 
August 26, 2016) (AD 2016-17-12), for 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 requires inspecting certain THSAs to determine 
the number of total flight cycles the THSA has accumulated, and 
replacing the THSA if necessary. The FAA issued AD 2016-17-12 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.

Actions Since AD 2016-17-12 Was Issued

    Since the FAA issued AD 2016-17-12, new investigations determined 
that the compliance time for removal from service and replacement of 
certain THSA NBB disks must be reduced. This task was required by AD 
2016-17-12, and the task 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. 
The FAA has therefore determined that new or more restrictive 
airworthiness limitations are necessary.
    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 Mandatory Continuing 
Airworthiness Information, or the MCAI), to correct an unsafe condition 
for all Airbus SAS Model A318-111, -112, -121, and -122 airplanes; 
Model A319-111, -112, -113, -114, -115, -131, -132, -133, -151N, -153N, 
and -171N airplanes; Model A320-211, -212, -214, -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.
    Airplanes with an original airworthiness certificate or original 
export certificate of airworthiness issued after October 5, 2020, must 
comply with the airworthiness limitations specified as part of the 
approved type design and referenced on the type certificate data sheet. 
However, Airbus A318/A319/A320/A321 Airworthiness Limitations Section 
(ALS) Part 4 Variation 7.1 specifies that replacements can be 
accomplished in accordance with certain service information, while this 
proposed AD would require accomplishing those replacements in 
accordance with certain service information. To ensure all maintenance 
or inspection programs incorporate the revised task, including the 
revised replacement requirements, this proposed AD would therefore 
require all operators to revise their existing maintenance or 
inspection program to include either the revised task including the 
revised provisions for replacement, or the revised provisions for 
replacement, depending on when the original airworthiness certificate 
or original export certificate of airworthiness was issued.
    EASA AD 2020-0270 specifies that it requires a task (limitation) 
already required by EASA AD 2020-0034, dated February 25, 2020 (which 
corresponds to FAA AD 2020-21-10, Amendment 39-21283 (85 FR 65190, 
October 15, 2020) (AD 2020-21-10)) and invalidates (terminates) prior 
instructions for that task. This proposed AD would terminate the ALS 
limitation for task 274000-00004-1-E for the THSAs, as required by 
paragraph (i) of AD 2020-21-10, for Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, -
133, -151N, and -153N airplanes; Model A320-211, -212, -214, -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; with an original airworthiness certificate or 
original export certificate of airworthiness issued on or before 
November 7, 2019, only.

[[Page 44665]]

    This proposed AD was prompted by a determination that new or more 
restrictive airworthiness limitations are necessary. The FAA is 
proposing 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. 
See the MCAI for additional background information.

Model A320-216 Airplanes

    The Airbus SAS Model A320-216 was U.S. type certificated on 
December 19, 2016. Before that date, any EASA ADs that affected Model 
A320-216 airplanes were included in the U.S. type certificate as part 
of the Required Airworthiness Actions List (RAAL). One or more Model 
A320-216 airplanes have subsequently been placed on the U.S. Register, 
and will now be included in FAA AD actions. For Model A320-216 
airplanes, the requirements that correspond to AD 2016-17-12 were 
mandated by the MCAI via the RAAL. Although that RAAL requirement is 
still in effect, for continuity and clarity the FAA has identified 
Model A320-216 airplanes in paragraph (c) of this proposed AD; the MCAI 
that is specified in paragraph (l) in this proposed AD includes 
restated requirements, which would therefore apply to those airplanes.

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.
    Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS) 
Part 4 Variation 7.1, dated October 5, 2020, describes a task for 
removal from service and replacement of certain THSA NBB disks.
    This proposed AD would also require 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.

FAA's Determination and Requirements of This Proposed AD

    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 the State of Design Authority, 
the FAA has been notified of the unsafe condition described in the MCAI 
and service information referenced above. The FAA is proposing this AD 
because the FAA has evaluated all pertinent information and determined 
an unsafe condition exists and is likely to exist or develop on other 
products of the same type design.

Proposed AD Requirements

    This proposed AD would retain the requirements of AD 2016-17-12. 
This proposed AD would also require revising the existing maintenance 
or inspection program, as applicable, to incorporate new or more 
restrictive airworthiness limitations, which are specified in EASA AD 
2020-0270 described previously, as proposed for incorporation by 
reference. Any differences with EASA AD 2020-0270 are identified as 
exceptions in the regulatory text of this AD.
    This proposed AD would require revisions to certain operator 
maintenance documents to include new actions (e.g., inspections). 
Compliance with these actions is required by 14 CFR 91.403(c). For 
airplanes that have been previously modified, altered, or repaired in 
the areas addressed by this proposed AD, the operator may not be able 
to accomplish the actions described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must request 
approval for an alternative method of compliance according to paragraph 
(p)(1) of this proposed AD.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA developed a process to use certain civil aviation 
authority (CAA) ADs as the primary source of information for compliance 
with requirements for corresponding FAA ADs. The FAA has been 
coordinating this process with manufacturers and CAAs. As a result, the 
FAA proposes to incorporate EASA AD 2020-0270 by reference in the FAA 
final rule. This proposed AD would, therefore, require compliance with 
EASA AD 2020-0270 in its entirety through that incorporation, except 
for any differences identified as exceptions in the regulatory text of 
this proposed AD. Using common terms that are the same as the heading 
of a particular section in EASA AD 2020-0270 does not mean that 
operators need comply only with that section. For example, where the AD 
requirement refers to ``all required actions and compliance times,'' 
compliance with this AD requirement is not limited to the section 
titled ``Required Action(s) and Compliance Time(s)'' in EASA AD 2020-
0270. Service information required by EASA AD 2020-0270 for compliance 
will be available at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2021-0663 after the FAA final rule is 
published.

Airworthiness Limitation ADs Using the New Process

    The FAA's process of incorporating by reference MCAI ADs as the 
primary source of information for compliance with corresponding FAA ADs 
has been limited to certain MCAI ADs (primarily those with service 
bulletins as the primary source of information for accomplishing the 
actions required by the FAA AD). However, the FAA is now expanding the 
process to include MCAI ADs that require a change to airworthiness 
limitation documents, such as airworthiness limitation sections.
    For these ADs that incorporate by reference an MCAI AD that changes 
airworthiness limitations, the FAA requirements are unchanged. 
Operators must revise the existing maintenance or inspection program, 
as applicable, to incorporate the information specified in the new 
airworthiness limitation document. The airworthiness limitations must 
be followed according to 14 CFR 91.403(c) and 91.409(e).
    The previous format of the airworthiness limitation ADs included a 
paragraph that specified that no alternative actions (e.g., 
inspections) or intervals may be used unless the actions or intervals 
are approved as an alternative method of compliance (AMOC) in 
accordance with the procedures specified in the AMOCs paragraph under 
``Other FAA Provisions.'' This new format includes a ``New Provisions 
for Alternative Actions and Intervals'' paragraph that does not 
specifically refer to AMOCs, but operators may still request an AMOC to 
use an alternative actions or intervals.

Costs of Compliance

    The FAA estimates that this proposed AD affects 1,630 airplanes of 
U.S. registry. The FAA estimates the following costs to comply with 
this proposed AD:

[[Page 44666]]



                                     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 proposed 
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

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would 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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

Airbus SAS: Docket No. FAA-2021-0663; Project Identifier MCAI-2020-
01618-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by September 27, 2021.

(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).

(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 new or more 
restrictive airworthiness limitations are necessary. The FAA is 
issuing this AD to address premature wear of the carbon friction 
disks on the no-back brake (NBB) of the trimmable horizontal 
stabilizer actuator (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.

[[Page 44667]]

(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 
``thresholds'' as incorporated by the requirements of paragraph (3) 
of EASA AD 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 Note 1 in the service information referenced in EASA AD 2020-
0270 specifies ``NBB carbon disc replacement can be accomplished in 
accordance with SB A320-27-1242 or VSB 47145-27-17,'' for this AD 
use ``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 ALS 
limitation task 274000-00004-1-E for the THSA, as required by 
paragraph (i) of AD 2020-21-10, for Model A318-111, -112, -121, and 
-122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, 
-133, -151N, and -153N airplanes; Model A320-211, -212, -214, -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,

[[Page 44668]]

-271NX, -272N, and -272NX airplanes; with an original airworthiness 
certificate or original export certificate of airworthiness issued 
on or before November 7, 2019, only.

(p) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Large Aircraft Section, International Validation Branch, FAA, has 
the authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or responsible Flight 
Standards Office, as appropriate. If sending information directly to 
the Large Aircraft Section, International Validation Branch, send it 
to the attention of the person identified in paragraph (q)(4) of 
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#7e47533f282d533f372c53494d4e533f33313d3e181f1f50191108"><span class="__cf_email__" data-cfemail="ba8397fbece997fbf3e8978d898a97fbf7f5f9fadcdbdb94ddd5cc">[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 EASA AD 2020-0270 that are 
required by paragraph (l) 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 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#a4e5e0d7e4c1c5d7c58ac1d1d6cbd4c58ac1d1"><span class="__cf_email__" data-cfemail="0140457241646072602f6474736e71602f6474">[email protected]</span></a>; internet www.easa.europa.eu. You may find this 
EASA AD on the EASA website at https://ad.easa.europa.eu.
    (2) For Airbus service information identified in this proposed 
AD, 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#2c4d4f4f43594258024d455e5b435e584401494d5f6c4d455e4e595f024f4341"><span class="__cf_email__" data-cfemail="1f7e7c7c706a716b317e766d68706d6b77327a7e6c5f7e766d7d6a6c317c7072">[email protected]</span></a>; 
internet https://www.airbus.com.
    (3) For UTC Aerospace Systems material identified in this 
proposed AD, 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#2c4f5e4f6c4f43404045425f024f4341"><span class="__cf_email__" data-cfemail="f7948594b794989b9b9e9984d994989a">[email protected]</span></a>; internet https://www.collinsaerospace.com/support.
    (4) You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 2200 South 216th St., 
Des Moines, WA. For information on the availability of this material 
at the FAA, call 206-231-3195. This material may be found in the AD 
docket on the internet at https://www.regulations.gov by searching 
for and locating Docket No. FAA-2021-0663.
    (5) 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#e497858a8e859dca9685888c858aa4828585ca838b92"><span class="__cf_email__" data-cfemail="097a6867636870277b6865616867496f6868276e667f">[email protected]</span></a>.

    Issued on August 5, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-17091 Filed 8-12-21; 8:45 am]
BILLING CODE 4910-13-P


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