AD 2017-19-23

[Federal Register Volume 82, Number 186 (Wednesday, September 27, 2017)]
[Rules and Regulations]
[Pages 44903-44907]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-20567]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0498; Product Identifier 2016-NM-175-AD; Amendment 
39-19053; AD 2017-19-23]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2015-15-10, 
which applied to all Airbus Model A318, A319, A320, and A321 series 
airplanes. AD 2015-15-10 required repetitive inspections of the 
trimmable horizontal stabilizer actuator (THSA) for damage, and 
replacement if necessary; and replacement of the THSA after reaching a 
certain life limit. This AD requires repetitive detailed inspections of 
certain THSAs, and related investigative and corrective actions if 
necessary. This AD was prompted by the establishment of an additional 
life limit for the THSA, based on flight cycles. In addition, the THSA 
manufacturer has issued service information which, when accomplished, 
increases the life limit of the THSA. We are issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective November 1, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 1, 
2017.

ADDRESSES: For service information identified in this final rule, 
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 <a href="/cdn-cgi/l/email-protection#bbdad8d8d4ced5cf95dad2c9ccd4c9cfd396dedac8fbdad2c9d9cec895d8d4d6"><span class="__cf_email__" data-cfemail="503133333f253e247e313922273f2224387d353123103139223225237e333f3d">[email&#160;protected]</span></a>; Internet 
<a href="http://www.airbus.com">http://www.airbus.com</a>.
    You may view this referenced service information at the FAA, 
Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 425-
227-1221. It is also available on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2017-
0498.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://

[[Page 44904]]

www.regulations.gov by searching for and locating Docket No. FAA-2017-
0498; 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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, 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, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-
1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2015-15-10, Amendment 39-18219 (80 FR 43928, 
July 24, 2015) (``AD 2015-15-10''). AD 2015-15-10 applied to all Airbus 
Model A318, A319, A320, and A321 series airplanes. The NPRM published 
in the Federal Register on June 2, 2017 (82 FR 25542). The NPRM was 
prompted by the establishment of an additional life limit for the THSA, 
based on flight cycles. The NPRM proposed to require repetitive 
detailed inspections of certain THSAs, and related investigative and 
corrective actions if necessary. We are issuing this AD to detect and 
correct wear of the THSA, which could reduce the remaining life of the 
THSA, possibly resulting in premature failure and consequent reduced 
controllability 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 2016-0184, dated September 13, 2016 (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, -212, -214, -231, -232, and 
-233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes. The MCAI states:

    In the frame of the A320 Extended Service Goal (ESG) project and 
the study on the Trimmable Horizontal Stabilizer Actuator (THSA), a 
sampling programme of in-service units was performed and several 
cases of wear at different THSA levels were reported.
    This condition, if not detected and corrected, would reduce the 
remaining life of the THSA, possibly resulting in premature failure 
and consequent reduced control of the aeroplane.
    Prompted by these findings, Airbus issued Service Bulletin (SB) 
A320-27-1227 to provide THSA inspection instructions. Consequently, 
EASA issued AD 2014-0011 (later revised) [which corresponds to AD 
2015-15-10] to require repetitive inspections of the THSA [and 
related investigative and corrective actions] and to introduce a 
life limit for the THSA, based on flight hours (FH).
    Since EASA AD 2014-0011R1 was issued, an additional life 
limitation has been established, based on flight cycles (FC). 
Furthermore, United Technologies Corporation Aerospace Systems 
(UTAS), the THSA manufacturer, issued an SB which, after 
accomplishment on THSA, increases the life limit of the THSA.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0011R1, which is superseded, and 
introduces an additional FC life limit for the affected THSA. This 
[EASA] AD also provides a revised life limit for the THSA after UTAS 
SB accomplishment on that THSA.

    You may examine the MCAI in the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2017-
0498.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received. Air Line Pilots 
Association, International (ALPA) and United Airlines expressed their 
support for the NPRM.

Changes Made to This AD

    The NPRM specified that a THSA that had been repaired in-shop as 
specified in UTAS Component Maintenance Manual 27-44-51 would be an 
equivalent method of compliance for the initial inspection required by 
paragraph (h) of this AD. We have revised paragraph (m) of this AD to 
specify that a THSA that has been repaired in-shop using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or the EASA; or Airbus's EASA Design Organization Approval 
(DOA), is acceptable for compliance with the initial inspection 
required by paragraph (h) of this AD. We have also added Note 1 to 
paragraph (m) of this AD to reference UTAS Component Maintenance Manual 
27-44-51 as an additional source of guidance for the in-shop repair of 
the THSA.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> 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 AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-27-1227, Revision 03, dated 
April 29, 2016. This service information describes procedures for 
repetitive special detailed inspections for wear of the THSA, and 
related investigative and corrective actions.
    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 1,182 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......................  6 work-hours x $85               $0  $510 per inspection  $602,820 per
                                    per hour = $510                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------


[[Page 44905]]

    We have received no definitive data that would enable us to provide 
cost estimates for the spectrometric analysis of the oil drained from 
the THSA gearbox. We estimate the following costs to do any necessary 
replacements or overhauls that would be required based on the results 
of the inspection. We have no way of determining the number of aircraft 
that might need these replacements or overhauls:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of THSA (retained from AD 2015-15-  11 work-hours x $85 per hour =          $240,000        $240,935
 10).                                            $935.
Overhaul of THSA (new action).................  66 work-hours x $85 per hour =           115,000         120,610
                                                 $5,610.
----------------------------------------------------------------------------------------------------------------

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 to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that 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:

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 removing Airworthiness Directive (AD) 
2015-15-10, Amendment 39-18219 (80 FR 43928, July 24, 2015), and adding 
the following new AD:

2017-19-23 Airbus: Amendment 39-19053; Docket No. FAA-2017-0498; 
Product Identifier 2016-NM-175-AD.

(a) Effective Date

    This AD is effective November 1, 2017.

(b) Affected ADs

    This AD replaces AD 2015-15-10, Amendment 39-18219 (80 FR 43928, 
July 24, 2015) (``AD 2015-15-10'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of wear at different levels in 
the trimmable horizontal stabilizer actuator (THSA). We are issuing 
this AD to detect and correct wear of the THSA, which could reduce 
the remaining life of the THSA, possibly resulting in premature 
failure and consequent reduced controllability of the airplane.

(f) Compliance

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

(g) Serviceable THSA Definition

    For the purposes of this AD, a serviceable THSA is a THSA that 
does not exceed the life limits as identified in table 1 to 
paragraphs (g) and (j) of this AD.

     Table 1 to Paragraphs (g) and (j) of This AD--THSA Life Limits
------------------------------------------------------------------------
    Configuration, based on service         Compliance time (whichever
        bulletin (SB) embodiment                  occurs first)
------------------------------------------------------------------------
THSA on which United Technologies        Before exceeding 67,500 flight
 Corporation Aerospace Systems (UTAS)     hours (FH) since first
 SB 47145-27-19 has not been embodied.    installation on an airplane,
                                          or before exceeding 48,000
                                          flight cycles (FC) since first
                                          installation on an airplane.

[[Page 44906]]

 
THSA on which UTAS SB 47145-27-19 has    Before exceeding 52,500 FH
 been embodied.                           after embodiment of UTAS SB
                                          47145-27-19 on an airplane,
                                          without exceeding 120,000 FH
                                          since first installation on an
                                          airplane; or before exceeding
                                          27,000 FC after embodiment of
                                          UTAS SB 47145-27-19 on an
                                          airplane, without exceeding
                                          75,000 FC since first
                                          installation on an airplane.
------------------------------------------------------------------------

(h) Repetitive Inspection and Related Investigative Actions

    For any airplane on which UTAS Service Bulletin 47145-27-19 has 
not been embodied: Before the THSA exceeds 48,000 flight hours or 
30,000 flight cycles, whichever occurs first since first 
installation on an airplane, do a special detailed inspection of the 
THSA and do all applicable related investigative actions, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-27-1227, Revision 03, dated April 29, 2016. Do all 
applicable related investigative actions at the applicable times 
specified in paragraph 1.E., ``Compliance'' of Airbus Service 
Bulletin A320-27-1227, Revision 03, dated April 29, 2016. Repeat the 
inspections thereafter at intervals not to exceed 24 months.

(i) Corrective Action

    If, during any inspection required by paragraph (h) of this AD, 
any finding as described in the Accomplishment Instructions of 
Airbus Service Bulletin A320-27-1227, Revision 03, dated April 29, 
2016, is identified: At the applicable time (depending on the 
applicable finding) specified in paragraph 1.E., ``Compliance,'' of 
Airbus Service Bulletin A320-27-1227, Revision 03, dated April 29, 
2016, replace the THSA with a serviceable THSA, as specified in 
paragraph (g) of this AD, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1227, Revision 03, 
dated April 29, 2016.

(j) THSA Replacement

    Within the applicable compliance time specified in table 1 to 
paragraphs (g) and (j) of this AD, replace each THSA with a 
serviceable THSA, as specified in paragraph (g) of this AD, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-27-1227, Revision 03, dated April 29, 2016.

(k) Replacement of a THSA: Not Terminating Action

    Replacement of a THSA on an airplane, as required by paragraph 
(i) or (j) of this AD, does not constitute terminating action for 
the repetitive inspections required by paragraph (h) of this AD for 
that airplane, unless the THSA has been overhauled as specified in 
UTAS Service Bulletin 47145-27-19 (i.e., post-service bulletin).

(l) Optional Terminating Action: Overhaul of THSA

    Accomplishment of a modification of an airplane by installing a 
THSA that has been overhauled as specified in UTAS Service Bulletin 
47145-27-19 constitutes terminating action for the repetitive 
inspections required by paragraph (h) of this AD, provided that, 
following modification, no THSA is reinstalled on the airplane 
unless it has been overhauled as specified in UTAS Service Bulletin 
47145-27-19.

(m) Replacement THSA Equivalency

    As of the effective date of this AD: A THSA that has been 
repaired in-shop is acceptable for compliance with the initial 
inspection required by paragraph (h) of this AD, provided that 
repair was done 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).
    Note 1 to paragraph (m) of this AD: Guidance for THSA repair in-
shop can be found in UTAS Component Maintenance Manual 27-44-51.

(n) Parts Installation Limitation

    As of the effective date of this AD: Do not install on any 
airplane a THSA unless it is a serviceable THSA as specified in 
paragraph (g) of this AD.

(o) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (h) and (i) of this AD, if those actions were performed 
before the effective date of this AD using any of the service 
information specified in paragraphs (o)(1), (o)(2), or (o)(3) of 
this AD.
    (1) Airbus Service Bulletin A320-27-1227, dated July 1, 2013, 
which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A320-27-1227, Revision 01, dated 
October 7, 2013, which was incorporated by reference in AD 2015-15-
10.
    (3) Airbus Service Bulletin A320-27-1227, Revision 02, dated 
February 2, 2015, which is not incorporated by reference in this AD.

(p) 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 (q)(2) of this AD. Information 
may be emailed to: <a href="/cdn-cgi/l/email-protection#c2fbef838c8feff3f3f4ef838f8d81ef908793978791969182a4a3a3eca5adb4"><span class="__cf_email__" data-cfemail="2c15016d6261011d1d1a016d61636f017e697d79697f787f6c4a4d4d024b435a">[email&#160;protected]</span></a>. 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 EASA; or Airbus's 
EASA DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Required for Compliance (RC): 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) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0184, dated September 13, 
3016, for related information. This MCAI may be found in the AD 
docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching 
for and locating Docket No. FAA-2017-0498.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 
425-227-1405; fax 425-227-1149.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (r)(3) and (r)(4) of this AD.

(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.
    (i) Airbus Service Bulletin A320-27-1227, Revision 03, dated 
April 29, 2016.
    (ii) Reserved.
    (3) For Airbus service information identified in this AD, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex,

[[Page 44907]]

France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email 
<a href="/cdn-cgi/l/email-protection#523331313d273c267c333b20253d20263a7f37332112333b203027217c313d3f"><span class="__cf_email__" data-cfemail="6a0b0909051f041e440b03181d05181e02470f0b192a0b0318081f1944090507">[email&#160;protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (5) 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on September 14, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-20567 Filed 9-26-17; 8:45 am]
 BILLING CODE 4910-13-P