83 FR 16251 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 73 (April 16, 2018)

We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318 and A319 series airplanes; Model A320-211, A320-212, A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes; and Model A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321- 231, and A321-232 airplanes. This proposed AD was prompted by reports of missing assembly hardware on the trimmable horizontal stabilizer actuator (THSA). This proposed AD would require repetitive inspections and checks of the lower and upper THSA attachments and applicable related investigative and corrective actions; a one-time inspection of the THSA lower attachment and replacement as applicable; and, for certain airplanes, activation of the electrical load sensing device (ELSD) and concurrent modifications. We are proposing this AD to address the unsafe condition on these products.

[Federal Register Volume 83, Number 73 (Monday, April 16, 2018)]
[Proposed Rules]
[Pages 16251-16256]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2018-07656]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0298; Product Identifier 2017-NM-179-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A318 and A319 series airplanes; Model A320-211, A320-212, 
A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes; and 
Model A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-
231, and A321-232 airplanes. This proposed AD was prompted by reports 
of missing assembly hardware on the trimmable horizontal stabilizer 
actuator (THSA). This proposed AD would require repetitive inspections 
and checks of the lower and upper THSA attachments and applicable 
related investigative and corrective actions; a one-time inspection of 
the THSA lower attachment and replacement as applicable; and, for 
certain airplanes, activation of the electrical load sensing device 
(ELSD) and concurrent modifications. We are proposing this AD to 
address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by May 31, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     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.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For Airbus service information identified in this NPRM, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email [email protected]; internet http://www.airbus.com.
    For United Technologies Corporation Aerospace Systems (UTAS) 
service information identified in this AD, contact United Technologies 
Corporation Aerospace Systems (UTAS): Goodrich Corporation, Actuation 
Systems, Stafford Road, Fordhouses, Wolverhampton WV10 7EH, England; 
phone: +44 (0) 1902 624938; fax: +44 (0) 1902 788100; email: 
[email protected]; internet: http://www.goodrich.com/TechPubs.
    You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th Street, Des Moines, WA. For 
information on the availability of this material at the FAA, call 206-
231-3195.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0298; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this NPRM, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket Operations 
office (telephone 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th Street, Des Moines, WA 98198; phone and fax: 206-231-3223.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0298; 
Product Identifier 2017-NM-179-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM based on 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0237, dated December 4, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A318 
and A319 series airplanes; Model A320-211, A320-212, A320-214, A320-
216, A320-231, A320-232, A320-233 airplanes; and Model A321-111, A321-
112, A321-131, A321-211, A321-212, A321-213, A321-231, and A321-232 
airplanes. The MCAI states:

    The Trimmable Horizontal Stabilizer Actuator (THSA) of Airbus 
A320 Family aeroplanes has been rig-tested to check secondary load 
path behaviour in case of primary load path failure. In that 
configuration, the loads are transferred to the secondary load path, 
which should jam, preventing any Trimmable Horizontal Stabilizer 
motion. The test results showed that the secondary load path did not 
jam as expected, preventing detection of the primary load path 
failure. To verify the integrity of the THSA primary load path and 
the correct installation of the THSA, Airbus issued Service Bulletin 
(SB) A320-27-1164, later revised multiple times, and SB A320-
27A1179, and EASA issued AD 2006-0223 [which corresponds to FAA AD 
2007-06-02, Amendment 39-14983 (72 FR 12072, March 15, 2007) (``AD 
2007-06-02'')], AD 2007-0178 [which corresponds to FAA AD 2008-09-
16, Amendment 39-15497 (73 FR 24160, May 2, 2008)(``AD 2008-09-
16'')], AD 2008-0150, and AD 2014-0147, each AD superseding the 
previous one, requiring one-time and repetitive inspections.
    Since EASA AD 2014-0147 was issued, Airbus designed a new 
device, called Electrical Load Sensing Device (ELSD), to introduce a 
new mean of THSA upper secondary load path engagement detection. 
Consequently, Airbus issued several SBs (Airbus SB A320-27-1245, 
A320-27-1246, and A320-27-1247, depending on aeroplane 
configuration) providing instructions to install the wiring 
provision for ELSD installation and to install ELSD on the THSA, and 
SB A320-27-1248, providing instructions to activate the ELSD. Airbus 
also revised SB A320-27-1164, now at Revision 13, including 
instructions applicable for aircraft equipped with ELSD.
    Furthermore, following a visual inspection of the THSA, an 
operator reported that the THSA was found with a bush missing, 
inducing torqueing of the THSA lower attachment primary bolt against 
the THSA lug, which resulted in the application of a transverse 
force on the lug.

[[Page 16252]]

    Prompted by several other identical findings, Airbus released 
Alert Operator Transmission (AOT) A27N010-17 to provide instructions 
for inspection and associated corrective actions.
    For the reasons described above, this AD retains the 
requirements of EASA AD 2014-0147, which is superseded, and requires 
installation of ELSD on the THSA, ELSD activation, and a one-time 
inspection to verify the bush presence on the THSA lower attachment.

    The unsafe condition is uncontrolled movement of the horizontal 
stabilizer as a result of the latent (undetected) failure of the THSA's 
primary load path and consequent loss of control of the airplane.
    The required actions include repetitive inspections and checks of 
the lower and upper THSA attachments and applicable related 
investigative and corrective actions; a one-time inspection of the THSA 
lower attachment and replacement as applicable; and, for certain 
airplanes, activation of the ELSD and concurrent modifications.
    Related investigative actions include an inspection of the upper 
THSA attachment, an inspection of the lower attachment, and a check of 
the upper and lower clearance between the secondary nut trunnion and 
the junction plate. Corrective actions include replacement of the THSA 
and repair.
    You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0298.

Relationship Between Proposed AD and AD 2007-06-02 and AD 2008-09-16

    Accomplishment of the certain proposed actions would terminate all 
requirements of AD 2007-06-02 and AD 2008-09-16.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Alert Operators Transmission (AOT) A27N010-17, 
Revision 01, dated October 17, 2017, including AOT Appendix_A27N010-17. 
This service information describes the procedure for a one-time general 
visual inspection of the THSA lower attachment to measure the gap 
between the THSA lower attachment tab washer and attachment plates and 
replacement of the THSA lower attachment if the measured gap is less 
than 0.5 mm. The replacement includes doing an inspection of the THSA 
parts to confirm the bushing is missing and applicable corrective 
actions (i.e., repair).
    Airbus has issued Service Bulletin A320-27-1164, Revision 13, dated 
August 8, 2016. This service information describes procedures for a 
general visual inspection of the upper THSA attachments for correct 
installation, cracks, damage and metallic particles; a general visual 
inspection of the upper attachment for correct installation; a check of 
the clearance between secondary nut trunnions and junction plates and 
correct installation of the lower THSA attachment; a general visual 
inspection of the THSA ball screw to check for the absence of dents; 
and applicable related investigative and corrective actions.
    Airbus has issued Service Bulletin A320-27-1245, Revision 00, dated 
March 6, 2017. This service information describes the procedure to 
modify the wiring provisions for the ELSD.
    Airbus has issued Service Bulletin A320-27-1246, Revision 01, dated 
November 4, 2016. This service information describes the procedures to 
adapt the wiring provision of the ELSD and THSA to accommodate the 
correct installation of the ELSD.
    Airbus has issued Service Bulletin A320-27-1247, Revision 00, dated 
March 6, 2017. This service information describes the procedure to 
modify the upper attachment secondary load path of the THSA to 
accommodate the correct installation of the ELSD.
    Airbus has issued Service Bulletin A320-27-1248, Revision 00, dated 
March 6, 2017. This service information describes the procedure to 
activate the ELSD.
    UTAS has issued United Technologies Corporation (UTC) Aerospace 
Systems Repair Instructions RF-DSC-1361-17, Version 00, including 
Appendix A, dated May 24, 2017. This service information describes 
repair instructions to follow if the bushing is missing as specified in 
AOT A27N010-17, Revision 01, dated October 17, 2017.
    This service information 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 our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 1,180 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
            Action                      Labor cost             Parts cost     Cost per product      operators
----------------------------------------------------------------------------------------------------------------
Inspections, Check,             Up to 59 work-hours x $85   Up to $15,353...  Up to $20,368...  Up to
 Activation, and Modifications.  per hour = $5,015.                                              $24,034,240.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed 
inspections. We have no way of determining the number of aircraft that 
might need this replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                 Action                              Labor cost                 Parts cost      Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement.............................  11 work-hours x $85 per hour =             $240,000           $240,935
                                           $935.
----------------------------------------------------------------------------------------------------------------


[[Page 16253]]

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition repairs specified in this proposed 
AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this NPRM is 2120-
0056. The paperwork cost associated with this NPRM has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this NPRM is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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.
    We are 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.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

Regulatory Findings

    We 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. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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 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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2018-0298; Product Identifier 2017-NM-179-AD.

(a) Comments Due Date

    We must receive comments by May 31, 2018.

(b) Affected ADs

    This AD affects AD 2007-06-02, Amendment 39-14983 (72 FR 12072, 
March 15, 2007) (``AD 2007-06-02'') and AD 2008-09-16, Amendment 39-
15497 (73 FR 24160, May 2, 2008) (``AD 2008-09-16'').

(c) Applicability

    This AD applies to Airbus Model A318-111, A318-112, A318-121, 
and A318-122 airplanes; Model A319-111, A319-112, A319-113, A319-
114, A319-115, A319-131, A319-132, and A319-133 airplanes; Model 
A320-211, A320-212, A320-214, A320-216, A320-231, A320-232, and 
A320-233 airplanes; and Model A321-111, A321-112, A321-131, A321-
211, A321-212, A321-213, A321-231, and A321-232 airplanes; 
certificated in any category, all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
controls.

(e) Reason

    This AD was prompted by reports of missing assembly hardware on 
the trimmable horizontal stabilizer actuator (THSA). We are issuing 
this AD to address uncontrolled movement of the horizontal 
stabilizer as a result of the latent (undetected) failure of the 
THSA's primary load path and consequent loss of control of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Repetitive Actions: Lower THSA Attachment

    Before exceeding 20 months since airplane first flight, or since 
airplane first flight following last THSA replacement, or within 20 
months after the last inspection of the lower THSA attachment as 
specified in the instructions of Airbus Service Bulletin A320-27-
1164, Revision 02 up to Revision 09, whichever occurs latest, do the 
actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this 
AD concurrently, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-27-1164, Revision 13, dated August 
8, 2016, Repeat the actions thereafter at intervals not to exceed 20 
months.
    (1) Check the clearance between the secondary nut trunnions and 
the junction plates at the lower THSA attachment.
    (2) Do a general visual inspection of the lower THSA attachment 
for correct installation of attachment parts.
    (3) Do a general visual inspection of the ball screw for dents.

(h) Repetitive Inspections: Upper THSA Attachment

    Before exceeding 10 months since airplane first flight, or since 
airplane first flight following last THSA replacement, or within 10 
months after the last inspection of the upper THSA attachment as 
specified in the instructions of Airbus Service Bulletin A320-27-
1164, Revision 02 up to Revision 09, whichever occurs latest, do the 
actions specified in paragraphs (h)(1) and (h)(2) of this AD 
concurrently, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-27-1164, Revision 13, dated August 8, 
2016. Repeat the inspections thereafter at intervals not to exceed 
10 months.
    (1) Do a general visual inspection of the upper THSA attachment 
for correct installation, cracks, damage, and metallic particles.
    (2) Do a general visual inspection of the upper attachment for 
correct installation of attachment parts.

[[Page 16254]]

(i) Related Investigative and Corrective Actions

    If, during any action required by paragraph (g) or (h) of this 
AD, any discrepancy is detected (e.g., any installation deviation, 
cracking, damage, metallic particle, or dent is found), before 
further flight, accomplish all applicable related investigative and 
corrective actions in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1164, Revision 13, 
dated August 8, 2016; except as required by paragraph (o)(1) of this 
AD.

(j) Reporting Requirements for Actions Required by Paragraphs (g) and 
(h) of This AD

    In case of any findings during any action required by paragraph 
(g) or (h) of this AD, report the inspection results to Airbus using 
the applicable ``Inspection Reporting Sheet'' of Airbus Service 
Bulletin A320-27-1164, Revision 13, dated August 8, 2016, at the 
applicable time specified in paragraph (j)(1) or (j)(2) of this AD. 
If operators have reported findings as part of obtaining any 
corrective actions approved by the EASA Design Organization Approval 
(DOA), operators are not required to report those findings as 
specified in this paragraph.
    (1) If the inspection or check was done on or after the 
effective date of this AD: Submit the report within 30 days after 
the inspection.
    (2) If the inspection or check was done before the effective 
date of this AD: Submit the report within 30 days after the 
effective date of this AD.

(k) One-Time Inspection and Replacement

    For airplanes on which the THSA has been replaced or reinstalled 
since the date of issuance of the original certificate of 
airworthiness or the date of issuance of the original export 
certificate of airworthiness: Within 6 months after the effective 
date of this AD, accomplish a detailed inspection of the THSA lower 
attachment gap clearances, in accordance with the instructions of 
Airbus Alert Operators Transmission (AOT) A27N010-17, Revision 01, 
dated October 17, 2017, including AOT Appendix_A27N010-17. If the 
measured gap is less than 0.5 mm, before further flight, replace the 
THSA, including doing an inspection of the THSA parts to confirm the 
bushing is missing and applicable corrective actions, in accordance 
with the instructions of Airbus AOT A27N010-17, Revision 01, dated 
October 17, 2017, including AOT Appendix_A27N010-17; and United 
Technologies Corporation (UTC) Aerospace Systems Repair Instructions 
RF-DSC-1361-17, Version 00, including Appendix A, dated May 24, 
2017, as applicable, except as required by paragraph (o)(2) of this 
AD.

(l) Definition of Groups

    For the purpose of this AD: Group 1 airplanes are those that, on 
the effective date of this AD, do not have the electrical load 
sensing device (ELSD) activated. Group 2 airplanes are those that, 
on the effective date of this AD, have the ELSD activated.

(m) Activation and Concurrent Modification

    For Group 1 airplanes (see paragraph (l) of this AD): Do the 
actions specified in paragraphs (m)(1) and (m)(2) of this AD.
    (1) Within 4 years after the effective date of this AD, activate 
the ELSD of the THSA on the airplane, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-27-1248, 
Revision 00, dated March 6, 2017.
    (2) Concurrently with or before the activation of the ELSD 
required by paragraph (m)(1) of this AD, modify the airplane, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-27-1245, Revision 00, dated March 6, 2017; or Airbus 
Service Bulletin A320-27-1246, Revision 01, dated November 4, 2016; 
as applicable.

(n) Concurrent Requirement for Airplanes Equipped With THSAs That Do 
Not Have ELSDs

    For an airplane equipped with a THSA having a part number listed 
in Figure 1 to paragraphs (n), (p), and (q) of this AD: Concurrently 
with or before the activation required by paragraph (m)(1) of this 
AD, modify the airplane, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1247, Revision 00, 
dated March 6, 2017.

[[Page 16255]]

[GRAPHIC] [TIFF OMITTED] TP16AP18.025

(o) Exceptions to Service Information

    (1) Where Airbus Service Bulletin A320-27-1164, Revision 13, 
dated August 8, 2016, specifies to contact Airbus for appropriate 
action, and specifies that action as ``RC'' (Required for 
Compliance): Before further flight, accomplish corrective actions in 
accordance with the procedures specified in paragraph (v)(2) of this 
AD.
    (2) Where Airbus AOT A27N010-17, Revision 01, dated October 17, 
2017, specifies to contact Airbus for appropriate action: Before 
further flight, accomplish corrective actions in accordance with the 
procedures specified in paragraph (v)(2) of this AD.

(p) Parts Installation

    Do not install on any airplane a THSA with a part number listed 
in Figure 1 to paragraphs (n), (p), and (q) of this AD and do not 
deactivate the ELSD at the times specified in paragraph (p)(1) or 
(p)(2) of this AD, as applicable.
    (1) Group 1 airplanes (see paragraph (l) of this AD): After 
modification of the airplane as required by paragraph (m)(1) of this 
AD.
    (2) Group 2 airplanes (see paragraph (l) of this AD): From the 
effective date of this AD.

(q) Method of Compliance

    An airplane on which Airbus modification 155955 has been 
embodied in production is considered compliant with paragraphs 
(m)(1), (m)(2), and (n) of this AD, provided that it is determined 
that no THSA with a part number listed in Figure 1 to paragraphs 
(n), (p), and (q) of this AD is installed on that airplane, and that 
the ELSD remains activated. A review of airplane maintenance records 
is acceptable to make this determination, provided those records can 
be relied upon for that purpose.

(r) Airplanes Not Affected by the Requirements of Paragraph (k) of This 
AD

    The inspection required by paragraph (k) of this AD is not 
required for airplanes on which the THSA has been installed as 
specified in the instructions of Airbus A320 Airplane Maintenance 
Manual (AMM) 27-44-51-400-001, dated May 2017, or subsequent.

(s) Credit for Previous Actions

    (1) This paragraph provides credit for initial actions required 
by paragraphs (g), (h), (i), and (j) of this AD, if those actions 
were performed before the effective date of this AD using the Airbus 
Service Bulletin A320-27-1164, Revision 10, dated March 2017, 2014; 
Revision 11, dated December 15, 2014; or Revision 12, dated March 
23, 2016.
    (2) This paragraph provides credit for actions required by 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using Airbus AOT A27N010-17, dated March 
27, 2017.
    (3) This paragraph provides credit for actions required by 
paragraph (m)(2) of this AD, if those actions were performed before 
the effective date of this AD using Airbus Service Bulletin A320-27-
1246, dated March 20, 2015.

(t) No Terminating Action for Repetitive Inspections in This AD

    Accomplishment on an airplane of the one-time inspection and 
replacement, as applicable, specified in paragraph (k) of this AD 
and the modifications specified in paragraphs (m)(1), (m)(2), and 
(n) of this AD,

[[Page 16256]]

as applicable, do not constitute terminating action for the 
repetitive inspections required by paragraphs (g) and (h) of this AD 
for that airplane.

(u) Terminating Action for Other FAA ADs

    Accomplishing the initial actions required by paragraphs (g) and 
(h) of this AD, and accomplishing the applicable actions required by 
paragraphs (i) and (j) of this AD, terminates all requirements of AD 
2007-06-02 and AD 2008-09-16.

(v) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards 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 local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Section, send it to the attention of 
the person identified in paragraph (x)(2) of this AD. Information 
may be emailed to: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or the European Aviation 
Safety Agency (EASA); or Airbus's EASA DOA. If approved by the DOA, 
the approval must include the DOA-authorized signature.
    (3) Paperwork Reduction Act Burden Statement: A federal agency 
may not conduct or sponsor, and a person is not required to respond 
to, nor shall a person be subject to a penalty for failure to comply 
with a collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 1 
hour per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW, Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.
    (4) Required for Compliance (RC): Except as specified in 
paragraph in (o)(1) 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.

(w) Special Flight Permits

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed.

(x) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0237, dated December 4, 
2017, for related information. This MCAI may be found in the AD 
docket on the internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2018-0298.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone 
and fax: 206-231-3223.
    (3) For Airbus service information identified in this AD, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email [email protected]; 
internet http://www.airbus.com.
    (4) For UTAS service information identified in this AD, contact 
United Technologies Corporation Aerospace Systems (UTAS): Goodrich 
Corporation, Actuation Systems, Stafford Road, Fordhouses, 
Wolverhampton WV10 7EH, England; phone: +44 (0) 1902 624938; fax: 
+44 (0) 1902 788100; email: [email protected]; 
internet: http://www.goodrich.com/TechPubs.
    (5) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th Street, Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.

    Issued in Des Moines, Washington, on March 30, 2018.
Chris Spangenberg,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-07656 Filed 4-13-18; 8:45 am]
 BILLING CODE 4910-13-P