[Federal Register Volume 82, Number 186 (Wednesday, September 27, 2017)]
[Rules and Regulations]
[Pages 44903-44907]
[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<EMAIL_ADDRESS>Internet
http://www.airbus.com.
    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 http://www.regulations.gov 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://

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<PHONE_NUMBER>; 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 http://www.regulations.gov 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:
     Are consistent with the intent that was proposed in the
NPRM for correcting 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 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.
----------------------------------------------------------------------------------------------------------------

    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.
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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.

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<EMAIL_ADDRESS>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 http://www.regulations.gov 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<PHONE_NUMBER>.
    (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,

France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email
<EMAIL_ADDRESS>Internet http://www.airbus.com.
    (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<PHONE_NUMBER>.
    (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<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    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


[Federal Register: November 18, 2010 (Volume 75, Number 222)]
[Notices]
[Page 70738]
[DOCID:fr18no10-77]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

 [Docket No. ER11-1939-000]

AP Gas & Electric (PA), LLC; Supplemental Notice That Initial
Market-Based Rate Filing Includes Request for Blanket Section 204
Authorization

November 9, 2010.
    This is a supplemental notice in the above-referenced proceeding AP
Gas & Electric (PA), LLC's application for market-based rate authority,
with an accompanying rate tariff, noting that such application includes
a request for blanket authorization, under 18 CFR Part 34, of future
issuances of securities and assumptions of liability.
    Any person desiring to intervene or to protest should file with the
Federal Energy Regulatory Commission, 888 First Street, NE.,
Washington, DC 20426, in accordance with Rules 211 and 214 of the
Commission's Rules of Practice and Procedure (18 CFR 385.211 and
385.214). Anyone filing a motion to intervene or protest must serve a
copy of that document on the Applicant.
    Notice is hereby given that the deadline for filing protests with
regard to the applicant's request for blanket authorization, under 18
CFR Part 34, of future issuances of securities and assumptions of
liability, is November 29, 2010.
    The Commission encourages electronic submission of protests and
interventions in lieu of paper, using the FERC Online links at http://
www.ferc.gov. To facilitate electronic service, persons with Internet
access who will eFile a document and/or be listed as a contact for an
intervenor must create and validate an eRegistration account using the
eRegistration link. Select the eFiling link to log on and submit the
intervention or protests.
    Persons unable to file electronically should submit an original and
14 copies of the intervention or protest to the Federal Energy
Regulatory Commission, 888 First Street, NE., Washington, DC 20426.
    The filings in the above-referenced proceeding are accessible in
the Commission's eLibrary system by clicking on the appropriate link in
the above list. They are also available for review in the Commission's
Public Reference Room in Washington, DC. There is an eSubscription link
on the Web site that enables subscribers to receive e-mail notification
when a document is added to a subscribed docket(s). For assistance with
any FERC Online service, please e-mail<EMAIL_ADDRESS>or
call<PHONE_NUMBER> (toll free). For TTY, call<PHONE_NUMBER>.

Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. 2010-29030 Filed 11-17-10; 8:45 am]
BILLING CODE 6717-01-P