Document ID: FAA-2017-1100-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2017-12-14T05:00Z

[Federal Register Volume 82, Number 239 (Thursday, December 14, 2017)]
[Proposed Rules]
[Pages 58772-58777]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-26362]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1100; Product Identifier 2017-NM-077-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-
13, which applies to certain Airbus Model A319 series airplanes; Model 
A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2015-
15-13 requires modification of the potable water service panel and 
waste water service panel, including doing applicable related 
investigative and corrective actions. Since we issued AD 2015-15-13, 
further investigations linked to widespread fatigue damage (WFD) 
analysis highlighted that, to meet the WFD requirements, it is 
necessary that the affected modification not be accomplished before 
reaching a certain threshold. This proposed AD would require 
modification of the waste water and potable water service panels with 
new compliance times. This proposed AD would also remove certain 
airplanes from the applicability and add Model A320-216 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 January 29, 
2018.

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 [email protected]; internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For 
information on the availability of this material at the FAA, call 425-
227-1221.

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-
1100; or in person at the Docket

[[Page 58773]]

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 Section, Transport Standards Branch, 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 proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-1100; 
Product Identifier 2017-NM-077-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

    Fatigue damage can occur locally, in small areas or structural 
design details, or globally, in widespread areas. Multiple-site damage 
is widespread damage that occurs in a large structural element such as 
a single rivet line of a lap splice joining two large skin panels. 
Widespread damage can also occur in multiple elements such as adjacent 
frames or stringers. Multiple-site damage and multiple-element damage 
cracks are typically too small initially to be reliably detected with 
normal inspection methods. Without intervention, these cracks will 
grow, and eventually compromise the structural integrity of the 
airplane. This condition is known as WFD. It is associated with general 
degradation of large areas of structure with similar structural details 
and stress levels. As an airplane ages, WFD will likely occur, and will 
certainly occur if the airplane is operated long enough without any 
intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    We issued AD 2015-15-13, Amendment 39-18223 (80 FR 45857, August 3, 
2015) (``AD 2015-15-13''), for certain Airbus Model A319 series 
airplanes; Model A320-211, -212, -214, -231,-232, and -233 airplanes; 
and Model A321 series airplanes. AD 2015-15-13 was prompted by reports 
of cracks that could be initiated at the waste water service panel area 
and the potable water service panel area. AD 2015-15-13 requires 
modification of the potable water service panel and waste water service 
panel, including doing applicable related investigative and corrective 
actions. We issued AD 2015-15-13 to prevent any cracking at the waste 
water service panel area and the potable water service panel area, 
which could affect the structural integrity of the airplane.
    Since we issued AD 2015-15-13, further investigations linked to WFD 
analysis highlighted that, to meet the WFD requirements, it is 
necessary that the affected modification is not accomplished before 
reaching a certain threshold by imposing a ``window of embodiment.''
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0098, dated June 7, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A319 series airplanes; Airbus Model A320-211, -212, -214, -216, -231, -
232, and -233 airplanes; and Airbus Model A321-111, -112, -131, -211, -
212, -213, -231, and -232 airplanes. The MCAI states:

    During the full scale fatigue test on A320-200, it was noticed 
that, due to fatigue, cracks could initiate at the potable water and 
waste water service panel areas.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    Prompted by these findings, Airworthiness Limitation Section 
(ALS) Part 2 tasks were introduced for the affected aeroplanes. 
Since those actions were taken, Airbus developed production mod 
160055 and mod 160056 to embody reinforcements (cold working on 
certain rivet rows) of the potable water and waste water service 
panels, and published associated Airbus Service Bulletin (SB) A320-
53-1272 and Airbus SB A320-53-1267 for in-service embodiment. 
Complementary design office studies highlighted that the 
``Sharklets'' installation on certain aeroplanes has a significant 
impact on the aeroplane structure (particularly, A319 and A320 post-
mod 160001, A320 post-SB A320-57-1193 (mod 160080), and A321 post-
mod 160021), leading to different compliance times, depending on 
aeroplane configuration.
    Consequently, EASA issued AD 2014-0081 [which corresponds to FAA 
AD 2015-15-13] to require reinforcement of the potable water and 
waste water service panels. Accomplishment of these modifications 
cancelled the need for the related ALS Part 2 Tasks.
    Since that AD was issued, further investigations linked to the 
Widespread Fatigue Damage (WFD) analysis highlighted that, to meet 
the WFD requirements, it is necessary that the affected modification 
is not accomplished before reaching a certain threshold, by imposing 
a so-called ``window of embodiment''. Consequently, Airbus revised 
SB A320-53-1272 (now at revision (Rev.) 04) and SB A320-53-1267 (now 
at Rev. 05).
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0081, which is superseded, and 
introduces additional compliance times for those actions.

    This proposed AD would also remove Model A319 series airplanes on 
which modification 28162, 28238, and 28342 have been embodied 
(``Corporate Jet'' modifications) from the applicability because 
production modifications

[[Page 58774]]

mitigated the risk associated with the unsafe condition. This proposed 
AD would also add Model A320-216 airplanes to the applicability because 
those airplanes are affected by the identified unsafe condition.
    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-
1100.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-53-1267, Revision 05, dated 
November 29, 2016, which describes procedures for modifying the waste 
water service panel. Airbus has also issued Service Bulletin A320-53-
1272, Revision 04, dated November 29, 2016, which describes procedures 
for modifying the potable water service panel. Both modifications 
include a check of the diameter of the holes of removed fasteners, a 
related investigative action (rotating probe inspection for cracking on 
the holes of the removed fasteners) and a corrective action (repair). 
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 the same 
type design.

Explanation of Compliance Time

    The compliance time for the replacement specified in this proposed 
AD for addressing WFD was established to ensure that discrepant 
structure is replaced before WFD develops in airplanes. Standard 
inspection techniques cannot be relied on to detect WFD before it 
becomes a hazard to flight. We will not grant any extensions of the 
compliance time to complete any AD-mandated service bulletin related to 
WFD without extensive new data that would substantiate and clearly 
warrant such an extension.

Costs of Compliance

    We estimate that this proposed AD affects 851 airplanes of U.S. 
registry.
    We also estimate that it would take about 27 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 $700 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $2,548,745, or $2,995 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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that this 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:
    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) 
2015-15-13, Amendment 39-18223 (80 FR 45857, August 3, 2015), and 
adding the following new AD:

Airbus: Docket No. FAA-2017-1100; Product Identifier 2017-NM-077-AD.

(a) Comments Due Date

    We must receive comments by January 29, 2018.

(b) Affected ADs

    This AD replaces AD 2015-15-13, Amendment 39-18223 (80 FR 45857, 
August 3, 2015) (``AD 2015-15-13'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
except for those airplanes on which Airbus modification 160055 or 
modification 160056 has been embodied in production, and except for 
Model A319 series airplanes on which modification 28162, 28238, and 
28342 have been embodied (``Corporate Jet'').
    (1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (2) Airbus Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes.
    (3) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating

[[Page 58775]]

that the potable water and waste water service panel areas are 
subject to widespread fatigue damage (WFD). We are issuing this AD 
to prevent cracking of the potable water and waste water service 
panel areas, which could result in reduced structural integrity of 
the airplane.

(f) Compliance

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

(g) Modification of the Potable Water Service Panel

    (1) Within the compliance times specified in Table 1 to 
paragraphs (g)(1) and (i) of this AD, as applicable, modify the 
potable water service panel, including doing a check of the diameter 
of the holes of removed fasteners, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1272, 
Revision 04, dated November 29, 2016, except as required by 
paragraph (g)(2) of this AD. Do all applicable related investigative 
and corrective actions before further flight.

     Table 1 to Paragraphs (g)(1) and (i) of This AD--Compliance Times for the Portable Water Service Panel
                                                  Reinforcement
----------------------------------------------------------------------------------------------------------------
                                                                                      Compliance time maximum
                                                                                    (before the accumulation of
               Affected airplanes *                   Compliance time minimum **     the specified total flight
                                                                                    cycles since the airplane's
                                                                                           first flight)
----------------------------------------------------------------------------------------------------------------
A319, pre-modification 160001 and pre-service       33,100 total flight cycles...  48,500 total flight cycles.
 bulletin A320-57-1193.
A319, post-modification 160001 or post-service      None.........................  46,000 total flight cycles.
 bulletin A320-57-1193.
A320, pre-modification 160001 and pre-service       25,100 total flight cycles...  54,200 total flight cycles.
 bulletin A320-57-1193.
A320, post-modification 160001 or post-service      None.........................  48,300 total flight cycles.
 bulletin A320-57-1193.
A321-100..........................................  25,100 total flight cycles...  60,000 total flight cycles.
A321-200 pre[dash]modification 160021.............  22,100 total flight cycles...  60,000 total flight cycles.
A321-200 post[dash]modification 160021............  None.........................  60,000 total flight cycles.
----------------------------------------------------------------------------------------------------------------
* A321-111, A321-112 and A321[dash]131 airplanes are collectively referred to as ``A321-100.'' Similarly, A321-
  211, A321-212, A321-213, A321-231 and A321-232 airplanes are collectively referred to as ``A321[dash]200''.
** Not before accumulating the specified total flight cycles since the airplane's first flight.

    (2) Where Airbus Service Bulletin A320-53-1272, Revision 04, 
dated November 29, 2016, specifies to contact Airbus for appropriate 
action, and specifies that action as ``RC'' (Required for 
Compliance): Before further flight, accomplish corrective actions in 
accordance with the procedures specified in paragraph (m)(2) of this 
AD.

(h) Modification of the Waste Water Service Panel

    (1) Within the compliance times specified in Table 2 to 
paragraphs (h)(1) and (i) of this AD, as applicable, modify the 
waste water service panel, including doing a check of the diameter 
of the holes of removed fasteners, and do all applicable related 
investigative and corrective actions in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1267, 
Revision 05, dated November 29, 2016, except as required by 
paragraph (h)(2) of this AD. Do all applicable related investigative 
and corrective actions before further flight.

       Table 2 to Paragraphs (h)(1) and (i) of This AD--Compliance Times for the Waste Water Service Panel
                                                  Reinforcement
----------------------------------------------------------------------------------------------------------------
     Affected airplanes *                  Compliance time minimum **                Compliance time maximum
----------------------------------------------------------------------------------------------------------------
A319, pre-modification 160001   28,600 total flight cycles.....................  Before the accumulation of
 and pre-service bulletin A320-                                                   44,400 total flight cycles
 57-1193.                                                                         since the airplane's first
                                                                                  flight.
A319, post-modification 160001  None...........................................  Before the accumulation of
 or post-service bulletin A320-                                                   43,600 total flight cycles
 57-1193.                                                                         since the airplane's first
                                                                                  flight.
A320, pre-modification 160001   35,800 total flight cycles.....................  Before the accumulation of
 and pre-service bulletin A320-                                                   46,000 total flight cycles
 57-1193.                                                                         since the airplane's first
                                                                                  flight; or within 2,300 flight
                                                                                  cycles since the last
                                                                                  accomplishment of
                                                                                  Airworthiness Limitation
                                                                                  Section (ALS) Part 2 Task
                                                                                  534126-01-3 without exceeding
                                                                                  48,000 total flight cycles
                                                                                  since the airplane's first
                                                                                  flight; whichever occurs
                                                                                  later.
A320, post-modification 160001  5,400 total flight cycles......................  Before the accumulation of
 or post-service bulletin A320-                                                   39,200 total flight cycles
 57-1193.                                                                         since the airplane's first
                                                                                  flight.
A321-100......................  36,900 total flight cycles.....................  Before the accumulation of
                                                                                  52,500 total flight cycles
                                                                                  since the airplane's first
                                                                                  flight.
A321-200 pre-modification       35,700 total flight cycles.....................  Before the accumulation of
 160021.                                                                          53,500 total flight cycles
                                                                                  since the airplane's first
                                                                                  flight.
A321-200 post-modification      None...........................................  Before the accumulation of
 160021.                                                                          51,200 total flight cycles
                                                                                  since the airplane's first
                                                                                  flight.
----------------------------------------------------------------------------------------------------------------
* A321-111, A321-112 and A321-131 airplanes are collectively referred to as ``A321-100.'' Similarly, A321-211,
  A321-212, A321-213, A321-231 and A321-232 airplanes are collectively referred to as ``A321-200''.
** Not before accumulating the specified total flight cycles since the airplane's first flight.

    (2) Where Airbus Service Bulletin A320-53-1267, Revision 05, 
dated November 29, 2016, specifies to contact Airbus for appropriate 
action, and specifies that action as ``RC'' (Required for 
Compliance): Before further flight, accomplish corrective actions in 
accordance with the procedures specified in paragraph (m)(2) of this 
AD.

(i) Corrective Action for Airplanes With Certain Modifications

    For airplanes on which the modification, as required by 
paragraph (g) or (h) of this AD,

[[Page 58776]]

as applicable, was accomplished before reaching the applicable 
minimum compliance time as defined in Table 1 to paragraphs (g)(1) 
and (i) of this AD or Table 2 to paragraphs (h)(1) and (i) of this 
AD: Before exceeding 60,000 flight cycles since the airplane's first 
flight, contact the Manager, International Section, Transport 
Standards Branch, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA) for 
approved corrective action instructions and accomplish those 
instructions accordingly.

(j) Terminating Action for Airplanes on Which the Potable Water Service 
Panel Modification Is Done

    Modification of an airplane as required by paragraph (g) of this 
AD terminates the requirement for accomplishing the ALS Part 2 task 
for that airplane as specified in Table 3 to paragraph (j) of this 
AD, as applicable.

  Table 3 to Paragraph (j) of This AD--ALS Part 2 Task Terminated After
                Potable Water Service Panel Modification
------------------------------------------------------------------------
                                                            ALS Part 2
                   Affected airplanes                        task No.
------------------------------------------------------------------------
A319, pre-modification 160001 and pre-service bulletin       534125-01-2
 A320-57-1193...........................................
A319, post-modification 160001 or post-service bulletin      534125-01-5
 A320-57-1193...........................................
A320, pre-modification 160001 and pre-service bulletin       534125-01-3
 A320-57-1193...........................................
A320, post-modification 160001 or post-service bulletin      534125-01-6
 A320-57-1193...........................................
A321 pre-modification 160021............................     534125-01-4
A321 post-modification 160021...........................     534125-01-7
------------------------------------------------------------------------

(k) Terminating Action for Airplanes on Which the Waste Water Service 
Panel Modification Is Done

    Modification of an airplane as required by paragraph (h) of this 
AD terminates the requirement for accomplishing the ALS Part 2 task 
for that airplane as specified in Table 4 to paragraph (k) of this 
AD, as applicable.

  Table 4 to Paragraph (k) of This AD--ALS Part 2 Task Terminated After
                 Waste Water Service Panel Modification
------------------------------------------------------------------------
                                                            ALS Part 2
                   Affected airplanes                        task No.
------------------------------------------------------------------------
A319, pre-modification 160001 and pre-service bulletin       534126-01-2
 A320[dash]57-1193......................................
A319, post-modification 160001 or post-service bulletin      534126-01-5
 A320[dash]57-1193......................................
A320, pre-modification 160001 and pre-service bulletin       534126-01-3
 A320[dash]57-1193......................................
A320, post-modification 160001 or post-service bulletin      534126-01-6
 A320[dash]57-1193......................................
A321 pre-modification 160021............................     534126-01-4
A321 post-modification 160021...........................     534126-01-7
------------------------------------------------------------------------

(l) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g) of this AD if those actions were performed before the 
effective date of this AD using the service information in 
paragraphs (l)(1)(i) through (l)(1)(iv) of this AD.
    (i) Airbus Service Bulletin A320-53-1272, Revision 00, dated 
January 10, 2013, which is not incorporated by reference in this AD.
    (ii) Airbus Service Bulletin A320-53-1272, Revision 01, dated 
August 6, 2013, which is not incorporated by reference in this AD.
    (iii) Airbus Service Bulletin A320-53-1272, Revision 02, dated 
May 19, 2014, which was incorporated by reference in AD 2015-15-13.
    (iv) Airbus Service Bulletin A320-53-1272, Revision 03, dated 
November 26, 2015, which is not incorporated by reference in this 
AD.
    (2) This paragraph provides credit for actions required by 
paragraph (h) of this AD if those actions were performed before the 
effective date of this AD using the service information in 
paragraphs (l)(2)(i) through (l)(2)(v) of this AD.
    (i) Airbus Service Bulletin A320-53-1267, Revision 00, dated 
June 24, 2013, which is not incorporated by reference in this AD.
    (ii) Airbus Service Bulletin A320-53-1267, Revision 01, dated 
October 2, 2013, which is not incorporated by reference in this AD.
    (iii) Airbus Service Bulletin A320-53-1267, Revision 02, dated 
May 19, 2014, which was incorporated by reference in AD 2015-15-13.
    (iv) Airbus Service Bulletin A320-53-1267, Revision 03, dated 
November 26, 2015, which is not incorporated by reference in this 
AD.
    (v) Airbus Service Bulletin A320-53-1267, Revision 04, dated 
February 1, 2016, which is not incorporated by reference in this AD.

(m) Other FAA AD Provisions

    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Section, send it to the attention of 
the person identified in paragraph (n)(2) of this AD. Information 
may be emailed to: [email protected]. 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: 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 Section, Transport Standards 
Branch, FAA; or the EASA; or Airbus's EASA DOA. If approved by the 
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraphs (g)(2) and (h)(2) of this AD: 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

[[Page 58777]]

changes to procedures or tests identified as RC require approval of 
an AMOC.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0098, dated June 7, 2017, 
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-2017-1100.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone 
425-227-1405; fax 425-227-1149.
    (3) 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 [email protected]; Internet http://www.airbus.com. 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.

    Issued in Renton, Washington, on November 29, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-26362 Filed 12-13-17; 8:45 am]
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