[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 [www.gpo.gov]
[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]]

[email protected]; 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 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 [email protected]; internet https://www.airbus.com. 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 
https://www.regulations.gov 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 [email protected]; internet 
https://www.collinsaerospace.com/support.

Examining the AD Docket

    You may examine the AD docket at https://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 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 [email protected].

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: [email protected].
    (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 [email protected].
    (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 [email protected]; internet 
https://www.collinsaerospace.com/support.

 (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 
[email protected]; internet www.easa.europa.eu. You may find this 
EASA AD on the EASA website at https://ad.easa.europa.eu.
    (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 [email protected]; internet https://www.airbus.com.
    (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 
[email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    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


