Document ID: FAA-2017-0476-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2017-05-19T04:00Z

[Federal Register Volume 82, Number 96 (Friday, May 19, 2017)]
[Proposed Rules]
[Pages 22918-22922]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10134]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0476; Directorate Identifier 2016-NM-110-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) 2014-08-
01, for all Airbus Model A318, A319, A320, and A321 series airplanes. 
AD 2014-08-01 currently requires an inspection for part numbers of the 
interconnecting struts and, for affected interconnecting struts, 
identification of the part and serial numbers of the associated target 
and proximity sensors and replacement or re-identification of the flap 
interconnecting strut if necessary. Since we issued AD 2014-08-01, we 
have determined that certain airplanes must be inspected to verify the 
interconnecting strut part number. This proposed AD would add airplanes 
to the applicability. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by July 3, 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 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. 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-
0476; 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, Washington 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-2017-0476; 
Directorate Identifier 2016-NM-110-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.

[[Page 22919]]

Discussion

    On April 7, 2014, we issued AD 2014-08-01, Amendment 39-17825 (79 
FR 23900, April 29, 2014) (``AD 2014-08-01''), for all Airbus Model 
A318, A319, A320, and A321 series airplanes. AD 2014-08-01 superseded 
AD 2014-03-08, Amendment 39-17745 (79 FR 9398, February 19, 2014) (``AD 
2014-03-08''). AD 2014-08-01 was prompted by a report that an 
investigation showed that when a certain combination of target/
proximity sensor serial numbers is installed on a flap interconnecting 
strut, a ``target FAR'' signal cannot be detected when it reaches the 
mechanical end stop of the interconnecting strut. AD 2014-08-01 
requires an inspection to determine the part number of the 
interconnecting struts installed on the wings, identifying the part 
number and the serial number of the associated target and proximity 
sensor if applicable, and replacing or re-identifying the flap 
interconnecting strut if applicable. We issued AD 2014-08-01 to correct 
the definition of a serviceable interconnecting strut.
    Since we issued AD 2014-08-01, we received a report that airplanes 
were delivered with pre-modification 27956 part number installed on the 
flap interconnecting strut(s), but declared to be in post-modification 
configuration in the Aircraft Inspection Report. We have determined 
that certain airplanes must be inspected to verify the interconnecting 
strut part number.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0113, dated June 15, 2016 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for all Airbus Model A318, A319, A320, and A321 series 
airplanes. The MCAI states:

    The flap interconnecting strut is a safety device of the High 
Lift System which acts as an alternative load path from one flap 
surface to another in case of a flap drive system disconnection. In 
such a failure case, the installed proximity sensors provide 
information to the slat flap control computer (SFCC) and the 
operation of the flap drive system is inhibited.
    An engineering investigation showed that, when a certain 
combination of target/sensor serial number (s/n) is installed on a 
flap interconnecting strut, a ``target FAR'' signal cannot be 
detected when reaching the mechanical end stop of the 
interconnecting strut.
    This condition, if not corrected, could cause a flap down drive 
disconnection to remain undetected, due to an already-failed 
interconnecting strut sensor, potentially resulting in asymmetric 
flap panel movement and consequent loss of control of the aeroplane.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A320-27-1206 and SB A320-57-1164, to provide 
identification and replacement instructions for struts that have a 
certain target/sensor s/n combination installed. Aeroplanes on which 
modification (mod) 27956 had been accomplished in production were 
identified as not affected by the unsafe condition. Consequently, 
EASA issued [EASA] AD 2012-0012 [which corresponds to FAA AD 2014-
03-08] to require accomplishment of these inspections and corrective 
actions.
    Since that [EASA] AD was issued, Airbus has informed EASA about 
a batch of aeroplanes that were delivered with pre-mod 27956 Part 
Number (P/N) flap interconnecting strut(s) installed, but declared 
to be in post-mod configuration in the Aircraft Inspection Report. 
Airbus SB A320-57-1202 has been issued to provide instructions to 
verify the interconnecting strut P/N, and to update aircraft 
documentation.
    In addition, to ensure that all pre-mod parts are checked and 
corrected as required, SB A320-27-1206 was revised to include a 
wider range of P/N of affected interconnecting struts.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2012-0012, which is superseded, expands the 
Applicability, changes the compliance time and requires an 
additional inspection for aeroplanes that have already been 
inspected.

    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-
0476.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-27-1206, Revision 02, dated 
November 2, 2015. The service information describes an inspection to 
determine the part number of the installed interconnecting struts and 
the part number and serial number of the associated target and 
proximity sensor, and replacement and re-identification of the 
interconnecting struts. 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 1,032 airplanes of U.S. 
registry.
    The actions required by AD 2014-08-01, and retained in this 
proposed AD, take about 8 work-hours per product, at an average labor 
rate of $85 per work-hour. Required parts cost about $0 per product. 
Based on these figures, the estimated cost of the actions that are 
required by AD 2014-08-01 is $680 per product.
    We also estimate that it would take about 15 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $0 per 
product. Based on these figures, we estimate the cost of this proposed 
AD on U.S. operators to be $1,315,800, or $1,275 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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

[[Page 22920]]

responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    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) 
2014-08-01, Amendment 39-17825 (79 FR 23900, April 29, 2014), and 
adding the following new AD:

Airbus: Docket No. FAA-2017-0476; Directorate Identifier 2016-NM-
110-AD.

(a) Comments Due Date

    We must receive comments by July 3, 2017.

(b) Affected ADs

    This AD replaces AD 2014-08-01, Amendment 39-17825 (79 FR 23900, 
April 29, 2014) (``AD 2014-08-01'').

(c) Applicability

    This AD applies to Airbus Model A318-111, -112, -121, and -122 
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes; certificated in any category; all manufacturer 
serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by a report that an investigation showed 
that when a certain combination of a target/proximity sensor serial 
numbers is installed on a flap interconnecting strut, a ``target 
FAR'' signal cannot be detected when reaching the mechanical end 
stop of the interconnecting strut. We are issuing this AD to detect 
and correct a latent failure of the flap down drive disconnection 
due to an already-failed interconnecting strut sensor, which could 
result in asymmetric flap panel movement and consequent loss of 
control of the airplane.

(f) Compliance

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

(g) Retained Inspection to Determine the Part Number of the 
Interconnecting Struts, With Revised Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2014-08-01, with revised service information. Within 8,000 flight 
hours after March 26, 2014 (the effective date of AD 2014-03-08, 
Amendment 39-17745 (79 FR 9398, February 19, 2014) (``AD 2014-03-
08'')), inspect to determine the part number of the interconnecting 
struts installed on both the left-hand (LH) and right-hand (RH) 
wings of the airplane, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1206, Revision 01, 
dated October 10, 2011; or Airbus Service Bulletin A320-27-1206, 
Revision 02, dated November 2, 2015. A review of the airplane 
maintenance records is acceptable for determining the part number of 
the installed interconnecting struts, in lieu of the inspection, if 
the part number of the installed interconnecting struts, and the 
part number and the serial number of the associated target and 
proximity sensor, can be conclusively determined from that review. 
Accomplishment of the requirements of paragraph (i) of this AD 
terminates the requirements of this paragraph.
    (1) Airplanes on which Airbus Modification 27956 has been 
embodied in production, and on which no interconnecting strut has 
been replaced with a strut having a part number specified in figure 
1 to paragraphs (g) and (h) of this AD since the airplane's first 
flight: No further work is required by paragraph (g) of this AD.
    (2) If, during the inspection required by paragraph (g) of this 
AD, any interconnecting strut is installed with a part number 
specified in figure 1 to paragraphs (g) and (h) of this AD: Within 
8,000 flight hours after March 26, 2014 (the effective date of AD 
2014-03-08), determine the part number and the serial number of the 
associated target and proximity sensor.
    (i) For airplanes having conditions specified in paragraphs 
(g)(2)(i)(A), (g)(2)(i)(B), (g)(2)(i)(C), and (g)(2)(i)(D) of this 
AD: Before further flight, replace the interconnecting strut with a 
serviceable unit, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-27-1206, Revision 01, dated October 
10, 2011; or Airbus Service Bulletin A320-27-1206, Revision 02, 
dated November 2, 2015. For the purposes of paragraph (g) of this 
AD, a serviceable interconnecting strut is a unit which has been 
determined to be in compliance with the requirements of paragraph 
(g) of this AD.
    (A) A target part number (P/N) ABS0121-13 or P/N 8-536-01; and
    (B) A target serial number lower than 1600, or a target serial 
number that is unreadable; and
    (C) A proximity sensor having P/N ABS0121-31 or P/N 8-372-04; 
and
    (D) A proximity sensor having a serial number between C59198 and 
C59435, or a serial number (S/N) C500000 or higher.
    (ii) For a target having S/N 1600 or higher and target P/N 
ABS0121-13 or P/N 8-536-01: Within 8,000 flight hours after March 
26, 2014 (the effective date of AD 2014-03-08), re-identify the 
interconnecting strut, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1206, Revision 01, 
dated October 10, 2011; or Airbus Service Bulletin A320-27-1206, 
Revision 02, dated November 2, 2015.

  Figure 1 to Paragraphs (g) and (h) of This AD--Interconnecting Strut
                              Part Numbers
------------------------------------------------------------------------
                   Interconnecting strut part numbers
-------------------------------------------------------------------------
D5757030500000
D5757030500100
D5757030500200
D5757030500600
D5757030500800
D5757030501000
D5757030501200
D5757032200000
------------------------------------------------------------------------

(h) Retained Parts Installation Prohibition, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2014-08-01, with no changes. As of March 26, 2014 (the effective 
date of AD 2014-03-08), no person may install an interconnecting 
strut with a part number specified in figure 1 to paragraphs (g) and 
(h) of this AD, on any airplane, except for parts identified in 
paragraph (g)(2)(ii) of this AD, provided that the actions in 
paragraph (g)(2)(ii) are done. As of the effective date of this AD, 
comply with the requirements of paragraph (l) of this AD in lieu of 
the requirements of this paragraph.

(i) New Requirements of This AD: Inspection To Determine the Part 
Number of the Interconnecting Struts and the Associated Target and 
Proximity Sensor

    Within 24 months after the effective date of this AD, accomplish 
the actions specified in paragraphs (i)(1) and (i)(2) of this AD, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-27-1206, Revision 02, dated November 2, 2015. 
Accomplishment of the actions specified in this paragraph terminates 
the requirements of paragraph (g) of this AD.
    (1) Inspect to determine the part number of the interconnecting 
struts installed on both the LH and RH wings on the airplane.
    (2) If an interconnecting strut is installed with a part number 
specified in figure 2 to paragraphs (i)(2), (k), and (l) of this AD, 
identify the part number and the serial number of the associated 
target and

[[Page 22921]]

proximity sensor; and for the target and proximity sensor part 
number and serial number combination specified in paragraph (j) of 
this AD, within the compliance times specified in paragraph (j) of 
this AD, do the actions specified in paragraph (j) of this AD for 
that interconnecting strut.

    Figure 2 to Paragraphs (i)(2), (k), and (l) of This AD--Affected
                         Interconnecting Struts
[XXX signifies any alpha-numeric combination. It may be possible to find
                           units with only XX]
 
 
-------------------------------------------------------------------------
D57570305000XXX
D57570305001XXX
D57570305002XXX
D57570305006XXX
D57570305008XXX
D57570305010XXX
D57570305012XXX
D57570322000XXX
------------------------------------------------------------------------

(j) New Requirements of This AD: Replacement or Reidentification

    (1) If the target serial number is lower than 1600 or is 
unreadable, and the proximity sensor part number is P/N ABS0121-31 
or P/N 8-372-04 with a serial number between S/N C59198 and C59435, 
or S/N C500000 or higher: Before further flight, do the actions 
required by paragraph (j)(1)(i) or (j)(1)(ii) of this AD. For the 
purposes of paragraph (j) of this AD, a serviceable interconnecting 
strut is a unit which has been determined to be in compliance with 
the requirements of paragraphs (i) and (j) of this AD.
    (i) Replace the interconnecting strut with a serviceable unit, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-27-1206, Revision 02, dated November 2, 2015.
    (ii) Do a general visual inspection of the flap down drive to 
detect discrepancies, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1206, Revision 02, 
dated November 2, 2015.
    (A) If no discrepancy is found, within 50 flight cycles after 
the inspection, replace the interconnecting strut with a serviceable 
unit, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-27-1206, Revision 02, dated November 2, 2015.
    (B) If any discrepancy is found, before further flight, replace 
the interconnecting strut with a serviceable unit, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-27-1206, Revision 02, dated November 2, 2015.
    (2) If the target serial number is 1600 or higher (with any 
proximity sensor part number and serial number): Within 24 months 
after the effective date of this AD, re-identify the interconnecting 
strut, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-27-1206, Revision 02, dated November 2, 2015.

(k) Additional Provisions of This AD

    (1) Airplanes on which Airbus Modification 27956 has been 
embodied in production, and on which no interconnecting strut with a 
part number identified in figure 2 to paragraphs (i)(2), (k), and 
(l) of this AD is installed since the airplane's first flight, are 
not affected by the requirements of paragraph (i) of this AD, except 
for those manufacturer serial numbers specified in figure 3 to 
paragraph (k)(1) of this AD. Airplanes having manufacturer serial 
numbers specified in figure 3 to paragraph (k)(1) of this AD are 
affected by the requirements of paragraph (i) of this AD.
    (2) For an airplane that has already been inspected before the 
effective date of this AD as specified in the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1206, dated January 
28, 2011; or Revision 1, dated October 10, 2011: Within the 
compliance time specified in paragraph (i) of this AD, accomplish 
the additional work specified in and in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-27-1206, 
Revision 2, dated November 2, 2015, unless it is determined that no 
interconnecting strut with a part number specified in figure 2 to 
paragraphs (i)(2), (k), and (l) of this AD is installed on that 
airplane. A review of airplane maintenance records is acceptable to 
make this determination, provided the part number can be 
conclusively identified from that review.

            Figure 3 to Paragraph (k)(1) of This AD--Additional Affected Manufacturer Serial Numbers
----------------------------------------------------------------------------------------------------------------
 
Airplane model--                                              Affected Manufacturer Serial Numbers--
----------------------------------------------------------------------------------------------------------------
A320 series airplanes...........................            1857            1858            1860            1861
                                                            1864            1865            1867            1868
                                                            1871            1873            1874            1877
                                                            1879            1883            1885            1888
                                                            1889            1891            1892            1894
                                                            1895            1896            1898            1899
                                                            1900            1902            1903            1904
                                                            1906            1907            1909            1910
                                                            1911            1913            1914            1915
                                                            1917            1918            1920            1922
                                                            1924            1927            1929            1931
                                                            1933            1935            1937            1940
                                                            1942            1944            1945            1948
                                                            1949            1951            1954            1957
                                                            1958            1961            1964            1965
                                                            1968            1969            1973            1975
                                                            1979            1981            1983            1987
A319 series airplanes...........................            1819            1820            1824            1826
                                                            1831            1833            1837            1839
                                                            1841            1844            1846            1851
                                                            1853            1855            1863            1866
                                                            1870            1872            1875            1876
                                                            1880            1882            1884            1886
                                                            1890            1893            1897            1901
                                                            1908            1912            1916            1923
                                                            1925            1934            1936            1938
                                                            1943            1947
----------------------------------------------------------------------------------------------------------------

(l) New Requirement of This AD: Parts Installation Limitations

    As of the effective date of this AD, no person may install, on 
any airplane, an interconnecting strut with a part number specified 
in figure 2 to paragraphs (i)(2), (k), and (l) of this AD, unless it 
has been modified in accordance with the requirements of this AD.

(m) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before 
March 26, 2014 (the effective date of AD 2014-03-

[[Page 22922]]

08), using Airbus Service Bulletin A320-27-1206, dated January 28, 
2011, and if additional work has been accomplished using Airbus 
Service Bulletin A320-27-1206, Revision 01, dated October 10, 2011.

(n) 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 International Branch, send it to ATTN: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 
98057-3356; telephone 425-227-1405; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (i) 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.
    (ii) AMOCs approved previously for AD 2014-08-01 are approved as 
AMOCs for the corresponding provisions of paragraphs (g) and (h) of 
this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, 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.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0113, dated June 15, 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-2017-0476.
    (2) 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 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.

    Issued in Renton, Washington, on May 11, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10134 Filed 5-18-17; 8:45 am]
 BILLING CODE 4910-13-P