Document ID: FAA-2018-0298-0007
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus SAS Airplanes
Posted Date: 2018-11-23T05:00Z

[Federal Register Volume 83, Number 226 (Friday, November 23, 2018)]
[Rules and Regulations]
[Pages 59278-59285]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-24486]

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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; Amendment 
39-19488; AD 2018-23-02]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus SAS 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 AD was prompted by reports of 
missing assembly hardware on the trimmable horizontal stabilizer 
actuator (THSA). This AD requires 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

[[Page 59279]]

replacement as applicable; and, for certain airplanes, activation of 
the electrical load sensing device (ELSD) and concurrent modifications. 
We are issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective December 28, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 28, 
2018.

ADDRESSES: For Airbus SAS 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 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 St., Des Moines, WA. For information 
on the availability of this material at the FAA, call 206-231-3195. It 
is also available on the internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2018-0298.

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 Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) 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, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus SAS 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. The NPRM published in the Federal Register on April 16, 
2018 (83 FR 16251). The NPRM was prompted by reports of missing 
assembly hardware on the THSA. The NPRM proposed to 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 ELSD and concurrent 
modifications.
    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.
    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 SAS 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 means 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.
    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.

[[Page 59280]]

Comments

    We gave the public the opportunity to participate in developing 
this final rule. The following presents the comments received on the 
NPRM and the FAA's response to each comment.

Support for the NPRM

    The Air Line Pilots Association, International, stated its support 
for the NPRM. United Airlines stated that it has no objection to the 
NPRM.

Request To Allow Future Revisions of Service Information

    Delta Air Lines (DAL) requested that the proposed AD allow 
operators the opportunity to utilize the latest data and instructions 
available without the need to request an alternative method of 
compliance (AMOC). DAL proposed that after each reference made to 
service information in paragraphs (g), (h), (i), (j), (k), (m)(1), and 
(m)(2) of the proposed AD, the following statement is included:

Or using a method approved by the Manager, International Section, 
Transport Standards Branch, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).

    DAL noted that the service information has been revised multiple 
times or has been revised within a short period of time. DAL observed 
that the statement quoted above is based on language used in paragraph 
(g) of AD 2018-03-12, Amendment 39-19185 (83 FR 5906, February 12, 
2018) (``AD 2018-03-12''), and should be considered as standard wording 
for future ADs, as applicable.
    We disagree with the commenter's request. We infer that the 
commenter is requesting a way for operators to comply with the 
requirements of an AD by using service information revisions that are 
issued after an AD is published without having to request an AMOC. We 
may not refer to any document that does not yet exist. In general 
terms, we are required by Office of the Federal Register (OFR) 
regulations for approval of materials ``incorporated by reference,'' as 
specified in 1 CFR 51.1(f), to either publish the service document 
contents as part of the actual AD language; or submit the service 
document to the OFR for approval as ``referenced'' material, in which 
case we may only refer to such material in the text of an AD. The AD 
may refer to the service document only if the OFR approved it for 
``incorporation by reference.'' See 1 CFR part 51. To allow operators 
to use later revisions of the referenced document (issued after 
publication of the AD), either we must revise the AD to reference 
specific later revisions, or operators must request approval to use 
later revisions as an AMOC with this AD. However, we may consider 
approving global AMOCs to allow operators to use future revisions of 
the service information. We reserve the use of the wording requested by 
the commenter for situations where no service information is available 
or a service document, such as an aircraft maintenance manual, cannot 
be incorporated by reference in an AD. Therefore, we have not changed 
this AD in this regard.

Request To Specify Required Paragraphs in Airbus Alert Operators 
Transmission

    DAL requested that paragraph (k) of the proposed AD specify only 
paragraphs 4.2.2 and 4.2.3 of Airbus Alert Operators Transmission (AOT) 
A27N010-17, Revision 01, dated October 17, 2017, including AOT 
Appendix_A27N010-17, because, as a whole, the service information 
contains data that are unrelated to the inspection process. Paragraphs 
4.2.2 and 4.2.3 of the service information provide the inspection 
activities and corrective actions.
    We agree with the commenter that the primary instructions for 
inspection and corrective actions are contained in paragraphs 4.2.2 and 
4.2.3 of Airbus AOT A27N010-17, Revision 01, dated October 17, 2017, 
including AOT Appendix_A27N010-17. We have revised paragraph (k) of 
this AD to require only paragraphs 4.2.2 and 4.2.3 of Airbus AOT 
A27N010-17, Revision 01, dated October 17, 2017, including AOT 
Appendix_A27N010-17. Note that there is relevant information outside of 
those two paragraphs, such as references to part numbers, aircraft 
maintenance manual procedures, and an appendix. Procedures outside of 
paragraphs 4.2.2 and 4.2.3 can be deviated from, using accepted methods 
provided in an operator's maintenance or inspection program, provided 
the required AD actions can be done and the airplane can be put back in 
service in an airworthy condition.

Request To Modify Language Regarding Contacting the Manufacturer

    DAL noted that paragraph (o) of the proposed AD provides exceptions 
to two Airbus service information documents--Airbus Service Bulletin 
A320-27-1164, Revision 13, dated August 8, 2016; and Airbus AOT 
A27N010-17, Revision 01, dated October 17, 2017, including AOT 
Appendix_A27N010-17, with respect to contacting the manufacturer. DAL 
proposed that this paragraph be rewritten to state:

    Any approved method which specifies to contact the manufacturer: 
Before further flight, accomplish the corrective actions in 
accordance with the procedures specified in paragraph (v)(2) of this 
AD.

    We acknowledge the commenter's request to clarify paragraph (o) of 
this AD. When specifying exceptions to required service information, we 
are unable to generalize the required documents by stating ``any 
approved method,'' as requested by the commenter. We must identify the 
specific service information. Therefore, we have not changed this AD in 
this regard.

Request for Clarification of Service Information Instructions

    DAL observed that Airbus Service Bulletin A320-27-1245, Revision 
00, dated March 6, 2017, indicates multiple configurations for certain 
aircraft. As an example, DAL pointed out that aircraft manufacturer 
serial number (MSN) 118 is shown as both configuration 078 and 
configuration 082. DAL stated the service information does not provide 
clear guidance on determining if both or only one set of material/
instructions is applicable. DAL requested that the service bulletin be 
revised to clarify the intent of the multiple configurations and how to 
address them.
    We disagree with the commenter's request to revise the service 
information; however, we agree to clarify. The referenced service 
information is adequate because different aircraft configurations can 
be determined based on the type of placard installed. Airbus Service 
Bulletin A320-27-1245, Revision 00, dated March 6, 2017, provides 
airplane configuration definitions in paragraph 1.A.(5), 
``Configuration Definition,'' of the ``Planning Information'' section. 
According to the configuration definition, configuration 078 has 
placard 33LM PN D11311117A00 installed and configuration 082 has 
placard 33LM PN 002051-09 installed. Once the placard installation is 
determined, an operator can follow the instructions based on each 
respective configuration. We have not changed this AD in this regard.

Request for One Comprehensive AD To Address THSA System

    DAL noted that the Model A319, A320, and A321 THSA system has had a 
continually complicated maintenance and regulatory history. The THSA 
system has been subject to numerous ADs throughout the years that 
address numerous individual shortcomings. The

[[Page 59281]]

proposed AD encompasses several different aspects (inspections and 
alterations), yet there are still other regulatory actions such as the 
replacement of No-Back Brake components or overhaul restrictions, which 
complicate the operators' maintenance activities. DAL requested that 
future regulatory actions related to the system be reviewed with a goal 
of providing a singular, coordinated over-arching regulatory and 
maintenance requirement.
    We agree that there have been several ADs issued on the THSA system 
addressed in this AD, and we acknowledge the commenter's concerns. We 
understand that the EASA and the airplane manufacturer are making an 
effort to combine as many THSA issues as possible into a single 
rulemaking action to simplify the THSA requirements. In response to 
their efforts, we may consider additional rulemaking in the future to 
simplify the THSA requirements. However, at this time, we are issuing 
this final rule AD to address the specified unsafe condition. No change 
has been made to this AD in this regard.

Request To Refer to Revised Service Information

    Airbus noted that two of the service bulletins referred to in the 
NPRM were revised and requested that the revised service bulletins be 
referred to in the final rule. The current revision levels are Airbus 
Service Bulletin A320-27-1164, Revision 14, dated January 16, 2018; and 
Airbus Service Bulletin A320-27-1248, Revision 01, dated April 16, 
2018.
    We agree with the commenter's request. In the NPRM we referred to 
Airbus Service Bulletin A320-27-1164, Revision 13, dated August 8, 
2016; and Service Bulletin A320-27-1248, Revision 00, dated March 6, 
2017. Airbus Service Bulletin A320-27-1164, Revision 14, dated January 
16, 2018, includes clarifications regarding reporting inspection 
results but does not change the proposed reporting requirements of the 
NPRM and otherwise adds no substantive changes compared with the 
previous version. Airbus Service Bulletin A320-27-1248, Revision 01, 
dated April 16, 2018, clarifies the instructions, but adds no 
substantive changes compared with the previous version. We have 
therefore revised the ``Related Service Information under 1 CFR part 
51'' paragraph in this final rule to refer to Airbus Service Bulletin 
A320-27-1164, Revision 14, dated January 16, 2018; and Airbus Service 
Bulletin A320-27-1248, Revision 01, dated April 16, 2018. We have also 
revised paragraphs (g), (h), (i), (j), and (o)(1) of this AD to refer 
to Airbus Service Bulletin A320-27-1164, Revision 14, dated January 16, 
2018. In addition, we revised paragraph (m) of this AD to refer to 
Airbus Service Bulletin A320-27-1248, Revision 01, dated April 16, 
2018.
    Furthermore, we revised paragraph (s), ``Credit for Previous 
Actions,'' of this AD to include Airbus Service Bulletin A320-27-1164, 
Revision 13, dated August 8, 2016; and Service Bulletin A320-27-1248, 
Revision 00, dated March 6, 2017. Specifically, we revised paragraph 
(s)(1) to provide credit for actions done before the effective date of 
this AD using Airbus Service Bulletin A320-27-1164, Revision 10, dated 
March 27, 2014; Revision 11, dated December 15, 2014; Revision 12, 
dated March 23, 2016; or Revision 13, dated August 8, 2016. We also 
added paragraph (s)(3) to this AD to provide credit for actions 
required by paragraph (m)(1) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A320-27-1248, Revision 00, dated March 6, 2017. We 
redesignated subsequent paragraphs of this AD accordingly.

Request To Supersede Affected ADs

    Airbus requested that the FAA consider aligning with EASA's 
decision of superseding affected ADs instead of keeping the obsolete 
ADs active. We infer that Airbus is requesting that we supersede AD 
2007-06-02 and AD 2008-09-16 instead of issuing this stand-alone AD 
that terminates the requirements of AD 2007-06-02 and AD 2008-09-16.
    We acknowledge the commenter's request. Although paragraph (u) of 
this AD states ``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,'' it does not 
supersede those ADs. The purpose of issuing stand-alone AD actions is 
to reduce the complexity involved with superseding certain ADs. After 
certain compliance times in this AD have passed, we may consider 
rescinding AD 2007-06-02 and AD 2008-09-16 since they are terminated by 
certain actions in this AD. In addition, if we converted this AD to a 
supersedure, we would need to issue another notice for public comment, 
which would further delay issuance of this final rule. Therefore, we 
have not changed this AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule with the changes described previously and minor 
editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

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 also issued Service Bulletin A320-27-1164, Revision 14, 
dated January 16, 2018. This service information describes procedures 
for a general visual inspection of the upper THSA attachment for 
correct installation, cracks, damage and metallic particles; a general 
visual inspection of the lower and upper THSA attachments 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.
    In addition, 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 also 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

[[Page 59282]]

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 01, dated 
April 16, 2018. 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 the 
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.

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on  U.S.
             Action                   Labor cost          Parts cost       Cost per  product       operators
----------------------------------------------------------------------------------------------------------------
Inspections, check, activation,   Up to 59 work-      Up to $15,353.....  Up to $20,368.....  Up to $24,034,240.
 and modifications.                hours x $85 per
                                   hour = $5,015.
Reporting.......................  1 work-hour x $85   0.................  85................  100,300.
                                   per hour = $85.
----------------------------------------------------------------------------------------------------------------

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

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

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition repairs specified in this 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 AD is 2120-
0056. The paperwork cost associated with this AD 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 AD 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 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 and 
associated appliances to the Director of the System Oversight Division.

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) 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

[[Page 59283]]

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):

2018-23-02 Airbus SAS: Amendment 39-19488; Docket No. FAA-2018-0298; 
Product Identifier 2017-NM-179-AD.

(a) Effective Date

    This AD is effective December 28, 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 SAS 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 14, dated January 
16, 2018. 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 THSA 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 14, dated January 16, 
2018. 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 THSA attachment 
for correct installation of attachment parts.

(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 particles, 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 14, 
dated January 16, 2018; 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 SAS 
using the applicable ``Inspection Reporting Sheet'' of Airbus 
Service Bulletin A320-27-1164, Revision 14, dated January 16, 2018, 
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 paragraphs 4.2.2 and 
4.2.3 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 01, dated April 16, 2018.
    (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 59284]]

[GRAPHIC] [TIFF OMITTED] TR23NO18.289

(o) Exceptions to Service Information

    (1) Where Airbus Service Bulletin A320-27-1164, Revision 14, 
dated January 16, 2018, specifies to contact Airbus SAS 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 SAS 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 SAS 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 the 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 
Airbus Service Bulletin A320-27-1164, Revision 10, dated March 27, 
2014; Revision 11, dated December 15, 2014; Revision 12, dated March 
23, 2016; or Revision 13, dated August 8, 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)(1) of this AD, if those actions were performed before 
the effective date of this AD using Airbus Service Bulletin A320-27-
1248, Revision 00, dated March 6, 2017.
    (4) 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.

[[Page 59285]]

(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, 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, terminate 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 SAS'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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (y)(3) and (y)(5) of this AD.

(y) 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.
    (i) Airbus Alert Operators Transmission (AOT) A27N010-17, 
Revision 01, dated October 17, 2017, including AOT Appendix_A27N010-
17.
    (ii) Airbus Service Bulletin A320-27-1164, Revision 14, dated 
January 16, 2018.
    (iii) Airbus Service Bulletin A320-27-1245, Revision 00, dated 
March 6, 2017.
    (iv) Airbus Service Bulletin A320-27-1246, Revision 01, dated 
November 4, 2016.
    (v) Airbus Service Bulletin A320-27-1247, Revision 00, dated 
March 6, 2017.
    (vi) Airbus Service Bulletin A320-27-1248, Revision 01, dated 
April 16, 2018.
    (vii) United Technologies Corporation Aerospace Systems (UTAS) 
United Technologies Corporation (UTC) Aerospace Systems Repair 
Instructions RF-DSC-1361-17, Version 00, including Appendix A, dated 
May 24, 2017.
    (3) For Airbus SAS service information identified in this 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 [email protected]; 
internet http://www.airbus.com.
    (4) For United Technologies Corporation Aerospace Systems 
service information identified in this AD, contact United 
Technologies Corporation Aerospace Systems: 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 St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (6) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on October 24, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-24486 Filed 11-21-18; 8:45 am]
BILLING CODE 4910-13-P