
[Federal Register Volume 82, Number 105 (Friday, June 2, 2017)]
[Proposed Rules]
[Pages 25542-25545]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10607]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0498; Directorate Identifier 2016-NM-175-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2015-15-
10, for all Airbus Model A318, A319, A320, and A321 series airplanes. 
AD 2015-15-10 currently requires 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. Since we issued AD 2015-15-10, an additional life 
limit for the THSA has been established, based on flight cycles. In 
addition, the THSA manufacturer has issued service information which, 
when accomplished, increases the life limit of the THSA. This proposed 
AD would require repetitive detailed inspections of certain THSAs, and 
related investigative and corrective actions if necessary. We are 
proposing this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by July 17, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For Airbus service information identified in this NPRM, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com.
    For United Technologies Corporation Aerospace Systems (UTAS) 
service information identified in this NPRM, contact Goodrich 
Corporation, Actuation Systems, Stafford Road, Fordhouses, 
Wolverhampton WV10 7EH, England; phone: +44 (0) 1902 624938; fax: +44 
(0) 1902 788100; email: techpubs.wolverhampton@goodrich.com; Internet: 
http://www.goodrich.com/TechPubs.
    You may view this referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 425-
227-1221.

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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0498; 
Directorate Identifier 2016-NM-175-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On July 12, 2015, we issued AD 2015-15-10, Amendment 39-18219 (80 
FR 43928, July 24, 2015) (``AD 2015-15-10''), for all Airbus Model 
A318, A319, A320, and A321 series airplanes. AD 2015-15-10 was prompted 
by reports of wear of the THSA. AD 2015-15-10 requires repetitive 
inspections of the THSA for damage, and replacement if necessary; and 
replacement of the THSA after reaching a certain life limit. We issued 
AD 2015-15-10 to detect and correct wear on the THSA, which would 
reduce the remaining life of the THSA, possibly resulting in premature 
failure and consequent reduced controllability of the airplane.
    Since we issued AD 2015-15-10, an additional life limit for the 
THSA has been established, based on flight cycles. In addition, the 
THSA manufacturer has issued service information which, when 
accomplished, increases the life limit of the THSA.
    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

[[Page 25543]]

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.

    The required action is repetitive special detailed inspections of 
the THSA. The optional terminating action is overhaul of the THSA. The 
related investigative action is a spectrometric analysis of the oil 
drained from the THSA gearbox. The corrective action is replacement of 
a THSA with a serviceable THSA.
    The compliance time for the related investigative and corrective 
actions varies depending on the findings, and ranges from before 
further flight to 4 months or between 1,000 and 1,250 flight hours 
since the first THSA oil drain.
    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.

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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 1,182 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections....................  6 work-hours x $85 per               $0  $510 per            $602,820 per
                                  hour = $510 per                          inspection cycle.   inspection cycle.
                                  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 proposed inspection. We have no way of determining the number of 
aircraft that might need these replacements or overhauls:

                                               On-Condition Costs
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                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
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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 proposed 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.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:

[[Page 25544]]

    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2015-15-10, Amendment 39-18219 (80 FR 43928, July 24, 2015), and adding 
the following new AD:

Airbus: Docket No. FAA-2017-0498; Directorate Identifier 2016-NM-
175-AD.

(a) Comments Due Date

    We must receive comments by July 17, 2017.

(b) Affected ADs

    This AD replaces AD 2015-15-10, Amendment 39-18219 (80 FR 43928, 
July 24, 2105) (``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)
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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[dash]27[dash]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 THSA: No 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 is overhauled as specified in the 
Accomplishment Instructions of 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 as specified in UTAS Component Maintenance Manual 
27-44-51 is acceptable for compliance with the initial inspection 
required by paragraph (h) of this AD.

(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.

[[Page 25545]]

(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 Branch, ANM-116, Transport Airplane Directorate, 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 manager of the International Branch send it to the 
attention of the person identified in paragraph (q)(2) of this AD. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
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 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (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, 
2016, 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 Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149.
    (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 account.airworth-eas@airbus.com; 
Internet http://www.airbus.com. You may view this service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.
    (4) For UTAS service information in this AD, contact Goodrich 
Corporation, Actuation Systems, Stafford Road, Fordhouses, 
Wolverhampton WV10 7EH, England; phone: +44 (0) 1902 624938; fax: 
+44 (0) 1902 788100; email: techpubs.wolverhampton@goodrich.com; 
Internet: http://www.goodrich.com/TechPubs.

    Issued in Renton, Washington, on May 17, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10607 Filed 6-1-17; 8:45 am]
BILLING CODE 4910-13-P


