AD 2017-20-02

[Federal Register Volume 82, Number 186 (Wednesday, September 27, 2017)]
[Rules and Regulations]
[Pages 44907-44914]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-20559]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0813; Product Identifier 2017-NM-109-AD; Amendment 
39-19059; AD 2017-20-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2017-13-05, 
which applied to all Airbus Model A330-200, A330-300, A340-200, A340-
300, A340-500, and A340-600 series airplanes. AD 2017-13-05 required an 
inspection, corrective actions if necessary, lubrication of the ball-
nut, modification of the trimmable horizontal stabilizer actuator 
(THSA), and additional work for previously modified airplanes. For 
certain airplanes, AD 2017-13-05 required installation of an electronic 
harness, terminating actions, and a ball-screw assembly inspection. 
This AD clarifies the formatting of a figure in the published version 
of AD 2017-13-05. This AD was prompted by reports indicating that 
affected parties misinterpreted the intent of a figure as formatted in 
the published version of AD 2017-13-05, which could result in a 
negative effect on compliance. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective October 12, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 28, 
2017 (82 FR 34251, July 24, 2017).
    We must receive comments on this AD by November 13, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For Airbus 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#88e9ebebe7fde6fca6e9e1faffe7fafce0a5ede9fbc8e9e1faeafdfba6ebe7e5"><span class="__cf_email__" data-cfemail="d4b5b7b7bba1baa0fab5bda6a3bba6a0bcf9b1b5a794b5bda6b6a1a7fab7bbb9">[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-
0813.

Examining the AD Docket

    You may examine 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-
0813; 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 street 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: Vladimir Ulyanov, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-
1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    On June 15, 2017, we issued AD 2017-13-05, Amendment 39-18935 (82 
FR 34251, July 24, 2017) (``AD 2017-13-05''), which applied to all 
Airbus Model A330-200, A330-300, A340-200, A340-300, A340-500, and 
A340-600 series airplanes. AD 2017-13-05 was prompted by the need for a 
modification that automatically detects failure of the ball-screw 
assembly. AD 2017-13-05 required an inspection, corrective actions if 
necessary, lubrication of the ball-nut, modification of the trimmable 
horizontal stabilizer actuator (THSA), and additional work for 
previously modified airplanes. For certain airplanes, AD 2017-13-05 
required installation of an electronic harness, terminating actions, 
and a ball-screw assembly inspection. We issued AD 2017-13-05 to detect 
and correct wear on the THSA, possibly resulting in damage to the ball-
screw and fail-safe nut, which could jam the THSA and result in reduced 
control of the airplane.
    Since we issued AD 2017-13-05, we have received reports indicating 
that affected parties could misinterpret the identity of applicable 
service information to use for the modification, due to the formatting 
of figure 2 to paragraphs (h) and (i) in the published version of AD 
2017-13-05. Since the published figure could result in a negative 
effect on compliance, we have determined that clarification of the 
formatting of the published figure is necessary.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2014-0219, dated September 29, 2014 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus Model A330 and Model A340 
series airplanes. (Model A330-223F and A330-243F airplanes were removed 
from AD 2017-13-05 to correspond with the MCAI.) The EASA AD is 
referenced in AD 2017-13-05. EASA has not revised its AD since the 
issuance of AD 2017-13-05.
    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-
0813.

[[Page 44908]]

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information. The service 
bulletins having the same document number (but different revision 
levels) are distinct because each revision contains unique editorial 
changes.
    The following service information describes procedures for doing 
repetitive inspections for integrity of the primary and secondary load 
paths of the ball-screw assembly of the THSA. These service bulletins 
are distinct because they apply to different airplane models.
    <bullet> Airbus Service Bulletin A330-27-3102, Revision 09, dated 
March 29, 2016.
    <bullet> Airbus Service Bulletin A340-27-4107, Revision 09, dated 
March 29, 2016.
    The following service information describes procedures for 
installing two electrical detection devices, also called CSPs, on the 
lower attachment secondary load path of the THSA, and modifying the 
THSA. These service bulletins are distinct because they apply to 
different airplane models equipped with THSAs having different part 
numbers.
    <bullet> Airbus Service Bulletin A330-27-3137, including Appendix 
01, dated March 20, 2007.
    <bullet> Airbus Service Bulletin A330-27-3137, Revision 01, 
including Appendix 1, dated December 6, 2007.
    <bullet> Airbus Service Bulletin A330-27-3137, Revision 02, dated 
January 18, 2010.
    <bullet> Airbus Service Bulletin A330-27-3143, Revision 01, dated 
July 10, 2012.
    <bullet> Airbus Service Bulletin A340-27-4136, including Appendix 
01, dated March 20, 2007.
    <bullet> Airbus Service Bulletin A340-27-4136, Revision 01, 
including Appendix 1, dated December 6, 2007.
    <bullet> Airbus Service Bulletin A340-27-4136, Revision 02, 
including Appendix 1, dated February 24, 2010.
    <bullet> Airbus Service Bulletin A340-27-4143, dated February 21, 
2012.
    <bullet> Airbus Service Bulletin A340-27-5030, Revision 01, 
including Appendix 1, dated November 20, 2009.
    The following service information describes procedures for 
installing electrical wiring harnesses and brackets to connect the 
secondary nut detection device to the monitoring systems. These service 
bulletins are distinct because they apply to different airplane models.
    <bullet> Airbus Service Bulletin A330-92-3046, Revision 04, dated 
July 16, 2010.
    <bullet> Airbus Service Bulletin A330-92-3046, Revision 05, dated 
November 7, 2011.
    <bullet> Airbus Service Bulletin A330-92-3046, Revision 07, dated 
January 13, 2017.
    <bullet> Airbus Service Bulletin A340-92-4056, Revision 03, dated 
July 16, 2010.
    <bullet> Airbus Service Bulletin A340-92-4056, Revision 04, dated 
December 5, 2013.
    <bullet> Airbus Service Bulletin A340-92-5008, Revision 07, dated 
February 8, 2013.
    The following service information describes system equipment 
maintenance requirements (SEMR) that refer to preventative maintenance 
requirements found necessary to comply with safety objectives. These 
documents are distinct because they apply to different airplane models.
    <bullet> Airbus A330 Airworthiness Limitations Section (ALS) Part 
4--System Equipment Maintenance Requirements (SEMR), Revision 05, dated 
October 19, 2015.
    <bullet> Airbus A340 Airworthiness Limitations Section (ALS) Part 
4--System Equipment Maintenance Requirements (SEMR), Revision 04, dated 
October 19, 2015.
    <bullet> Airbus A340 Airworthiness Limitations Section (ALS) Part 
3--Certification Maintenance Requirements (CMR), Revision 03, dated 
October 19, 2015, describes CMRs that are system-related periodic tasks 
established during type certification.
    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 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

FAA's Justification and Determination of the Effective Date

    We are superseding AD 2017-13-05 to clarify the formatting of a 
figure in the regulatory text of the published AD. No other changes 
have been made to AD 2017-13-05. Therefore, we determined that notice 
and opportunity for prior public comment are unnecessary.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2017-0813; Product 
Identifier 2017-NM-109-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to <a href="http://www.regulations.gov">http://www.regulations.gov</a>, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 33 airplanes of U.S. registry. 
This AD adds no new economic burden to AD 2017-13-05.
    We estimate that it takes about 68 work-hours per product to comply 
with the basic requirements of this AD. The average labor rate is $85 
per work-hour. Required parts would cost about $17,481 per product. 
Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $764,808, or $23,260 per product.

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

[[Page 44909]]

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) 
2017-13-05, Amendment 39-18935 (82 FR 34251, July 24, 2017), and adding 
the following new AD:

2017-20-02 Airbus: Amendment 39-19059; Docket No. FAA-2017-0813; 
Product Identifier 2017-NM-109-AD.

(a) Effective Date

    This AD is effective October 12, 2017.

(b) Affected ADs

    This AD replaces AD 2017-13-05, Amendment 39-18935 (82 FR 34251, 
July 24, 2017) (``AD 2017-13-05'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, all 
manufacturer serial numbers.
    (2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541, 
and -642 airplanes, all manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by the need for a modification that 
automatically detects failure of the ball-screw assembly. We are 
issuing this AD to detect and correct wear on the trimmable 
horizontal stabilizer actuator (THSA), possibly resulting in damage 
to the ball-screw and fail-safe nut, which could jam the THSA and 
result in reduced control of the airplane.

(f) Compliance

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

(g) Retained Actions for Electronic Centralized Aircraft Monitor (ECAM) 
Fault Messages, With Revised FAA Contact Information

    This paragraph restates the requirements of paragraph (g) of AD 
2017-13-05, with revised FAA contact information. For airplanes 
other than those identified in figure 1 to paragraphs (g), (h), and 
(q) of this AD: If, during any flight, one of the ``PRIM X PITCH 
FAULT'' or ``STAB CTL FAULT'' messages is displayed on the ECAM 
associated with the ``PITCH TRIM ACTR (1CS)'' maintenance message, 
before further flight after each time the message is displayed on 
the ECAM, do the actions specified in paragraphs (g)(1) and (g)(2) 
of this AD.
    (1) Do the applicable detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path; check 
the checkable shear pins (CSP), if installed; and do all applicable 
corrective actions; as specified in paragraph (g)(1)(i), (g)(1)(ii), 
or (g)(1)(iii) of this AD. Do all applicable corrective actions 
before further flight.
    (i) For Model A330 series airplanes: Do the actions in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-27-3102, Revision 09, dated March 29, 2016, except as 
required by paragraph (n)(1) of this AD.
    (ii) For Model A340-200 and -300 series airplanes: Do the 
actions in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A340-27-4107, Revision 09, dated March 29, 2016, 
except as required by paragraph (n)(1) of this AD.
    (iii) For Model A340-500 and -600 series airplanes: Do the 
actions 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 (g)(1)(iii) of this AD: Guidance for the 
inspection of the ball-screw assembly can be found in Task 274000-
B0002-1-C, Inspection of the ball-screw assembly for integrity of 
the primary and secondary load paths, of the Airbus A340 
Airworthiness Limitations Section (ALS) Part 3--Certification 
Maintenance Requirements (CMR), Revision 03, dated October 19, 2015.
    (2) Lubricate the THSA ball-nut in accordance with the 
applicable service information specified in paragraph (g)(2)(i), 
(g)(2)(ii), or (g)(2)(iii) of this AD.
    (i) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A330 ALS Part 4--System Equipment Maintenance Requirements 
(SEMR), Revision 05, dated October 19, 2015 (for Model A330 series 
airplanes).
    (ii) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A340 ALS Part 4--System Equipment Maintenance Requirements 
(SEMR), Revision 04, dated October 19, 2015 (for Model A340-200 and 
-300 series airplanes).
    (iii) Task 274000-B0003-1-C, Lubrication of THS Actuator ball-
screw nut, of Airbus A340 ALS Part 3--Certification Maintenance 
Requirements (CMR), Revision 03, dated October 19, 2015 (for Model 
A340-500 and -600 series airplanes).
BILLING CODE 4910-13-C

[[Page 44910]]

[GRAPHIC] [TIFF OMITTED] TR27SE17.010


[[Page 44911]]



(h) Retained Installation of CSP and Electrical Harness, With No 
Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2017-13-05, with no changes. For all airplanes, except Group 2 
airplanes specified in figure 1 to paragraphs (g), (h), and (q) of 
this AD, and except for airplanes identified in paragraphs (i), (j), 
and (n)(2) of this AD: Within 12 months after August 28, 2017 (the 
effective date of AD 2017-13-05), modify the airplane by installing 
a CSP on the THSA and an additional electrical harness, in 
accordance with the Accomplishment Instructions of the Airbus 
service information specified in figure 2 to paragraphs (h) and (i) 
of this AD, as applicable to the part number of the THSA installed 
on the airplane, except as provided by paragraph (n)(2) of this AD.
BILLING CODE 4910-13-C
[GRAPHIC] [TIFF OMITTED] TR27SE17.011

(i) Retained ``Additional Work'' on Previously Modified Airplanes, With 
No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2017-13-05, with no changes. For airplanes that have already been 
modified (installation of CSP on the THSA and electrical harness) 
before August 28, 2017 (the effective date of AD 2017-13-05), in 
accordance with the Accomplishment Instructions of any previous 
revision of an Airbus service bulletin specified in figure 2 to 
paragraphs (h) and (i) of this AD, as applicable: Within 12 months 
after August 28, 2017, do the ``Additional Work'' specified in, and 
in accordance with, the Accomplishment Instructions of the 
applicable Airbus service information specified in figure 2 to 
paragraphs (h) and (i) of this AD.

(j) Retained Installation of Electrical Harness on Airplanes Equipped 
with a CSP, With No Changes

    This paragraph restates the requirements of paragraph (j) of AD 
2017-13-05, with no changes. For airplanes having one of the THSAs 
installed with a part number listed in figure 3 to paragraph (j) of 
this AD, and that have been modified by installing a CSP on the THSA 
as required by paragraph (h) of this AD: Within 12 months after 
August 28, 2017 (the effective date of AD 2017-13-05), inspect to 
determine if the electrical harness identified in the applicable 
Airbus service information specified in figure 3 to paragraph (j) of 
this AD is installed on the airplane, and, if not installed, modify 
the airplane by installing an electrical harness, in accordance with 
the Accomplishment Instructions of the Airbus service information 
specified in figure 3 to paragraph (j) of this AD, as applicable to 
the part number of the THSA installed on the airplane. Airplanes 
having one of the THSAs installed with a part number listed in 
figure 3 to paragraph (j) of this AD already have the CSP installed 
on the THSA, and only the electrical harness must be installed on 
the airplane.

[[Page 44912]]

[GRAPHIC] [TIFF OMITTED] TR27SE17.012

(k) Retained Provisions for Terminating Action for Repetitive 
Inspections of Airbus Model A330-200 and -300 Series Airplanes, With No 
Changes

    This paragraph restates the provisions of paragraph (k) of AD 
2017-13-05, with no changes. Accomplishment of a modification before 
August 28, 2017 (the effective date of AD 2017-13-05), using the 
Accomplishment Instructions of Airbus Service Bulletin A330-27-3137, 
including Appendix 01, dated March 20, 2007; or Revision 01, 
including Appendix 1, dated December 6, 2007; and Airbus Service 
Bulletin A330-92-3046, Revision 04, dated July 16, 2010; or Revision 
05, dated November 7, 2011; or Revision 06, dated November 15, 2013; 
terminates the repetitive inspections specified in paragraphs (k)(1) 
through (k)(4) of this AD. Modification of an airplane as specified 
by this paragraph does not constitute terminating action for the 
actions specified in paragraph (g)(2) of this AD or the additional 
work specified in paragraph (i) of this AD.
    (1) Task 274400-00001-1-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
check the gap at the secondary nut trunnion, of Airbus A330 ALS Part 
4--System Equipment Maintenance Requirements (SEMR), Revision 05, 
dated October 19, 2015.
    (2) Task 274400-00001-2-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
check the CSPs, of Airbus A330 ALS Part 4--System Equipment 
Maintenance Requirements (SEMR), Revision 05, dated October 19, 
2015.
    (3) Task 274400-00001-3-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
check the CSPs, of Airbus A330 ALS Part 4--System Equipment 
Maintenance Requirements (SEMR), Revision 05, dated October 19, 
2015.
    (4) Task 274400-00001-4-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
check the CSPs, of Airbus A330 ALS Part 4--System Equipment 
Maintenance Requirements (SEMR), Revision 05, dated October 19, 
2015.

(l) Retained Provisions for Terminating Action for Repetitive 
Inspections of Airbus Model A340-200 and -300 Series Airplanes, With No 
Changes

    This paragraph restates the provisions of paragraph (l) of AD 
2017-13-05, with no changes. Accomplishment of a modification in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A340-27-4143, dated February 21, 2012; and Airbus Service 
Bulletin A340-92-4056, Revision 03, dated July 16, 2010; terminates 
the actions required by paragraph (g)(1) of this AD for modified 
Airbus Model A340-200 and -300 series airplanes only. Modification 
of an airplane as specified in this paragraph does not constitute 
terminating action for the actions specified in paragraph (g)(2) of 
this AD, or the additional work specified in paragraph (i) of this 
AD.

(m) Retained Provisions for Terminating Action for Repetitive 
Inspections of Airbus Model A340-200 and -300 Series Airplanes, With No 
Changes

    This paragraph restates the provisions of paragraph (m) of AD 
2017-13-05, with no changes. Accomplishment of a modification before 
August 28, 2017 (the effective date of AD 2017-13-05), using the 
Accomplishment Instructions of Airbus Service Bulletin A340-27-4136, 
including Appendix 01, dated March 20, 2007; or Revision 01, 
including Appendix 1, dated December 6, 2007; and Airbus Service 
Bulletin A340-92-4056, Revision 03, dated July 16, 2010; terminates 
the repetitive inspections specified in paragraphs (m)(1) through 
(m)(4) of this AD. Modification of an airplane as specified in this 
paragraph does not constitute terminating action for the actions 
specified in paragraph (g)(2) of this AD, or the additional work 
specified in paragraph (i) of this AD.
    (1) Task 274400-00001-1-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
gap check at the secondary nut trunnion, of Airbus A340 ALS Part 4--
System Equipment Maintenance Requirements (SEMR), Revision 04, dated 
October 19, 2015.
    (2) Task 274400-00001-2-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
CSP check, of Airbus A340 ALS Part 4--System Equipment Maintenance 
Requirements (SEMR), Revision 04, dated October 19, 2015.
    (3) Task 274400-00001-3-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
CSP check, of Airbus A340 ALS Part 4--System Equipment Maintenance 
Requirements (SEMR), Revision 04, dated October 19, 2015.
    (4) Task 274400-00001-4-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
CSP check, of A340 ALS Part 4--System Equipment Maintenance 
Requirements (SEMR), Revision 04, dated October 19, 2015.

(n) Retained Exceptions to the Actions in Certain Service Information 
and Paragraph (h) of This AD, With No Changes

    This paragraph restates the exceptions of paragraph (n) of AD 
2017-13-05, with no changes.
    (1) Where Airbus Service Bulletin A330-27-3102, Revision 09, 
dated March 29, 2016 (for Model A330 series airplanes); or Airbus 
Service Bulletin A340-27-4107, Revision 09, dated March 29, 2016 
(for Model A340 series airplanes); specifies to contact Airbus for a 
damage assessment: Before further flight, accomplish the required 
actions in accordance with the procedures specified in paragraph 
(s)(2) of this AD.
    (2) For airplanes that already had the electrical harness 
installed during production using Airbus Modifications 52269 and 
56056 for Airbus Model A330-200 and -300 series airplanes and Airbus 
Model A340-200 and -300 series airplanes, and using Airbus 
Modifications 52191 and 56058 for Model A340-500 and -600 series 
airplanes: Only the CSP must be installed on the THSA in

[[Page 44913]]

accordance with applicable Airbus service bulletins and within the 
compliance time specified in paragraph (h) of this AD.

(o) Retained Provisions for Terminating Action for Repetitive 
Inspections for Airplanes on Which Actions Required by Paragraph (h), 
(i), or (j) of This AD Are Done, With No Changes

    This paragraph restates the provisions of paragraph (o) of AD 
2017-13-05, with no changes. Modification of an airplane as required 
by paragraph (h), (i), or (j) of this AD, as applicable, constitutes 
terminating action for that airplane for the applicable actions 
identified in paragraphs (o)(1) through (o)(4) of this AD.
    (1) For all airplanes: The actions required by paragraph (g) of 
this AD.
    (2) For Model A340-500 and -600 series airplanes: Task 274000-
B0002-1-C, Inspection of the ball-screw assembly for integrity of 
the primary and secondary load paths, of Airbus A340 ALS Part 3--
Certification Maintenance Requirements (CMR), Revision 03, dated 
October 19, 2015.
    (3) For Model A330-200 and -300 series airplanes: The ALS tasks 
identified in paragraphs (k)(1) through (k)(4) of this AD.
    (4) For Model A340-200 and -300 series airplanes: The ALS tasks 
identified in paragraphs (m)(1) through (m)(4) of this AD.

(p) Retained Ball-screw Assembly Inspection for Certain Airplanes, With 
Revised FAA Contact Information

    This paragraph restates the requirements of paragraph (p) of AD 
2017-13-05, with revised FAA contact information. For Model A340-500 
and -600 airplanes that are in post-Airbus Service Bulletin A340-92-
5008, at Revision 06 or earlier, configuration: Before exceeding the 
threshold or interval, as applicable, of Task 274000-B0002-1-C, 
Inspection of the ball-screw assembly for integrity of the primary 
and secondary load paths, of Airbus A340 ALS Part 3--Certification 
Maintenance Requirements (CMR), Revision 03, dated October 19, 2015, 
or within 3 months after August 28, 2017 (the effective date of AD 
2017-13-05), whichever occurs later, accomplish Task 274000-B0002-1-
C, Inspection of the ball-screw assembly for integrity of the 
primary and secondary load paths, of Airbus A340 ALS Part 3--
Certification Maintenance Requirements (CMR), Revision 03, dated 
October 19, 2015; and do all applicable corrective actions. Do all 
applicable corrective actions before further flight using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or EASA; or Airbus's EASA DOA. Repeat Task 274000-
B0002-1-C, Inspection of the ball-screw assembly for integrity of 
the primary and secondary load paths, thereafter at the applicable 
intervals specified in Airbus A340 ALS Part 3--Certification 
Maintenance Requirements (CMR), Revision 03, dated October 19, 2015.

(q) Retained Parts Installation Prohibitions, With No Changes

    This paragraph restates the requirements of paragraph (1) of AD 
2017-13-05, with no changes.
    (1) For all airplanes except Group 2 airplanes as identified in 
figure 1 to paragraphs (g), (h), and (q) of this AD: After 
modification of the airplane as required by paragraph (h), (i), or 
(j) of this AD, as applicable, no person may install any THSA having 
part number (P/N) 47172-300, P/N 47147-500, P/N 47175-200, or P/N 
47175-300.
    (2) For Group 2 airplanes, as identified in figure 1 to 
paragraphs (g), (h), and (q) of this AD: As of August 28, 2017 (the 
effective date of AD 2017-13-05), no person may install on any Group 
2 airplane any THSA having P/N 47172-300, P/N 47147-500, P/N 47175-
200, or P/N 47175-300.

(r) Retained Credit for Previous Actions, With No Changes

    This paragraph restates the provisions of paragraph (r) of AD 
2017-13-05, with no changes.
    (1) This paragraph provides credit for actions required by 
paragraph (g)(2) of this AD, if those actions were performed before 
August 28, 2017 (the effective date of AD 2017-13-05), using the 
applicable service information specified in paragraphs (r)(1)(i) 
through (r)(1)(iv) of this AD.
    (i) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A330 ALS Part 4--Ageing Systems Maintenance, Revision 03, 
dated September 9, 2011 (for Model A330 series airplanes).
    (ii) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A330 ALS Part 4--Ageing Systems Maintenance, Revision 04, 
dated August 27, 2013 (for Model A330 series airplanes).
    (iii) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, 
of Airbus A340 ALS Part 4--Ageing Systems Maintenance, Revision 02, 
dated October 12, 2011 (for Model A340-200 and -300 series 
airplanes).
    (iv) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A340 ALS Part 4--Ageing Systems Maintenance, Revision 03, 
dated November 15, 2012 (for Model A340-200 and -300 series 
airplanes).
    (2) This paragraph provides credit for the electrical harness 
installation required by paragraph (h) of this AD and the inspection 
and electrical harness installation required by paragraph (j) of 
this AD, if those actions were performed before August 28, 2017 (the 
effective date of AD 2017-13-05), using Airbus Service Bulletin 
A330-92-3046, Revision 06, dated November 15, 2013.

(s) 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 manager of the International Section, send it to the 
attention of the person identified in paragraph (t)(2) of this AD. 
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#b58c98f4fbf89884848398f4f8faf698e7f0e4e0f0e6e1e6f5d3d4d49bd2dac3"><span class="__cf_email__" data-cfemail="d6effb97989bfbe7e7e0fb979b9995fb849387839385828596b0b7b7f8b1b9a0">[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 EASA; or Airbus's EASA 
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.

(t) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0219, dated September 29, 
2014, for related information. You may examine the MCAI on the 
Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating 
Docket No. FAA-2017-0813.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
telephone 425-227-1138; 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 (u)(4) and (u)(5) of this AD.

(u) 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.
    (3) The following service information was approved for IBR on 
August 28, 2017 (82 FR 34251, July 24, 2017).
    (i) Airbus A330 Airworthiness Limitations Section (ALS) Part 4--
System Equipment Maintenance Requirements (SEMR), Revision 05, dated 
October 19, 2015.
    (ii) Airbus A340 Airworthiness Limitations Section (ALS) Part 
3--Certification Maintenance Requirements (CMR), Revision 03, dated 
October 19, 2015.
    (iii) Airbus A340 Airworthiness Limitations Section (ALS) Part 
4--System Equipment Maintenance Requirements (SEMR), Revision 04, 
dated October 19, 2015.
    (iv) Airbus Service Bulletin A330-27-3102, Revision 09, dated 
March 29, 2016.
    (v) Airbus Service Bulletin A330-27-3137, including Appendix 01, 
dated March 20, 2007.
    (vi) Airbus Service Bulletin A330-27-3137, Revision 01, 
including Appendix 1, dated December 6, 2007.
    (vii) Airbus Service Bulletin A330-27-3137, Revision 02, dated 
January 18, 2010.
    (viii) Airbus Service Bulletin A330-27-3143, Revision 01, dated 
July 10, 2012.
    (ix) Airbus Service Bulletin A330-92-3046, Revision 04, dated 
July 16, 2010.
    (x) Airbus Service Bulletin A330-92-3046, Revision 05, dated 
November 7, 2011.
    (xi) Airbus Service Bulletin A330-92-3046, Revision 07, dated 
January 13, 2017.

[[Page 44914]]

    (xii) Airbus Service Bulletin A340-27-4107, Revision 09, dated 
March 29, 2016.
    (xiii) Airbus Service Bulletin A340-27-4136, including Appendix 
01, dated March 20, 2007.
    (xiv) Airbus Service Bulletin A340-27-4136, Revision 01, 
including Appendix 1, dated December 6, 2007.
    (xv) Airbus Service Bulletin A340-27-4136, Revision 02, 
including Appendix 1, dated February 24, 2010.
    (xvi) Airbus Service Bulletin A340-27-4143, dated February 21, 
2012.
    (xvii) Airbus Service Bulletin A340-27-5030, Revision 01, 
including Appendix 1, dated November 20, 2009.
    (xviii) Airbus Service Bulletin A340-92-4056, Revision 03, dated 
July 16, 2010.
    (xix) Airbus Service Bulletin A340-92-4056, Revision 04, dated 
December 5, 2013.
    (xx) Airbus Service Bulletin A340-92-5008, Revision 07, dated 
February 8, 2013.
    (4) For 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: <a href="/cdn-cgi/l/email-protection#ff9e9c9c908a918bd19e968d88908d8b97d29a9e8cbf9e968d9d8a8cd19c9092"><span class="__cf_email__" data-cfemail="056466666a706b712b646c77726a77716d2860647645646c776770762b666a68">[email&#160;protected]</span></a>; Internet: 
<a href="http://www.airbus.com">http://www.airbus.com</a>.
    (5) 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.
    (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 <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. 2017-20559 Filed 9-26-17; 8:45 am]
BILLING CODE 4910-13-P