[Federal Register Volume 82, Number 141 (Tuesday, July 25, 2017)]
[Proposed Rules]
[Pages 34449-34453]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15485]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0707; Directorate Identifier 2016-NM-014-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 adopt a new airworthiness directive (AD) for 
certain Airbus Model A318 series airplanes; Model A319 series 
airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; 
and Model A321 series airplanes. This proposed AD was prompted by 
reports of fatigue damage in the structure for the door stop fittings 
on certain fuselage frames (FR). This proposed AD would require 
repetitive rototest inspections for cracking of the fastener holes in 
certain door stop fittings, and repair if necessary. We are proposing 
this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by September 8, 
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.

[[Page 34450]]

     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: 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 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 
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-
0707; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

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

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0707; 
Directorate Identifier 2016-NM-014-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0238, dated December 2, 2016, corrected January 4, 2017 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A318 series airplanes; Model A319 series airplanes; Model A320-211, -
212, -214, -231, -232, and -233; and Model A321 series airplanes. The 
MCAI states:

    During an A320 fatigue test campaign, it was determined that 
fatigue damage could appear at the door stop fitting holes of 
fuselage frame (FR) 66 and FR 68 on left hand (LH) and right hand 
(RH) sides.
    This condition, if not detected and corrected, could affect the 
structural integrity of the airframe.
    Two inspections, Airworthiness Limitations Item (ALI) tasks 
534129 and 534130, were introduced in the Airworthiness Limitations 
Section (ALS) Part 2 with the April 2012 revision and with some 
compliance time changes with Revision 3 of ALS Part 2 of October 
2014.
    Since these ALI tasks were implemented, a significant number of 
reports [were] received concerning non-critical damage and early 
crack findings. Prompted by these reports, Airbus published SB A320-
53-1288 and SB A320-53-1290, providing inspection instructions to 
improve damage management and modification instructions.
    Consequently, EASA issued AD 2016-0015, requiring repetitive 
rototest inspections of the affected door stop fitting holes and, 
depending on findings, repair of any cracked area(s).
    Since that [EASA] AD was issued, ALS Part 2 Revision 04 and 
later on Revision 05 were published, introducing updated thresholds 
and/or intervals for some tasks as specified in Airbus SB A320-53-
1288, introducing new configuration of aeroplane with RETRO WING 
having accomplished SB A320-57-1193 (mod 160080), and keeping the 
threshold or interval only in flight cycles (FC).
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2016-0015, which is superseded, but requires 
those actions within the updated thresholds and intervals. In 
addition, a corrected threshold for pre-mod 160021 A321 aeroplanes 
is introduced and the Applicability is reduced to exclude 
configurations that are not affected.
    This [EASA] AD is republished to clarify some requirements in 
Appendix 1 [in this EASA AD].

    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-
0707.

Related Service Information Under 1 CFR Part 51

    We have reviewed the following Airbus service information.
     Airbus Service Bulletin A320-53-1288, Revision 01, 
including Appendixes 01, 02, and 03, dated October 3, 2016, provides 
procedures for rototest inspections for cracking of the fastener holes 
in the airframe structure for the door stop fittings installation in 
FR66 and FR68.
     Airbus Service Bulletin A320-53-1290, Revision 01, dated 
October 3, 2016, provides procedures for cold working the fastener 
holes in the airframe structure for the door stop fittings installation 
in FR66 and FR68.
    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.

Difference Between This Proposed AD and the MCAI

    The MCAI includes an exception to the compliance times for ``post-
mod 160080 aeroplanes for which a `corrected' threshold or interval can 
be defined in accordance with the instructions of Airbus SB A320-57-
1193.'' Airbus Service Bulletin A320-57-1193, Revision 04, dated 
September 30, 2016, and earlier revisions, do not contain corrected 
compliance times for doing the actions specified in this proposed AD. 
Therefore, this proposed AD does not include that exception. Operators 
may request approval of an alternative method of compliance (AMOC) for 
revised compliance times under the provisions of paragraph (q)(1) of 
this proposed AD.

[[Page 34451]]

Explanation of Compliance Time

    In most ADs, we adopt a compliance time allowing a specified amount 
of time after the AD's effective date. In this case, however, EASA has 
already issued regulations that require operators of airplanes in 
certain configurations to do a rototest inspection for cracking of the 
holes in certain door stop fittings to address an identified unsafe 
condition by certain dates. To provide for coordinated implementation 
of EASA's regulations and this proposed AD, we are using the same 
compliance dates in this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 1,084 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections......................  23 work-hours x $85              $0  $1,955 per           $2,119,220 per
                                    per hour = $1,955                    inspection cycle.    inspection cycle.
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of aircraft that might need this 
repair.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair........................................  27 work-hours x $85 per hour =              $610          $2,905
                                                 $2,295.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

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

Airbus: Docket No. FAA-2017-0707; Directorate Identifier 2016-NM-
014-AD.

(a) Comments Due Date

    We must receive comments by September 8, 2017.

(b) Affected ADs

    None.

(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, except airplanes specified in paragraphs (c)(1), 
(c)(2), and (c)(3) of this AD.
    (1) Airplanes on which Airbus Modification (Mod) 157039 has been 
embodied in production.
    (2) Model A319 series airplanes on which Mod 28238, Mod 28162, 
and Mod 28342 have been embodied in production.
    (3) Model A318 series airplanes on which Mod 39195 has been 
embodied in production or Airbus Service Bulletin A320-00-1219 has 
been embodied in service.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of fatigue damage in the 
structure for the door stop fittings on certain fuselage frames 
(FR). We are issuing this AD to detect and correct cracking at the 
door stop fitting holes of fuselage FR66 and FR68. Such cracking 
could result in reduced structural integrity of the airplane due to 
the failure of structural components.

(f) Compliance

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

(g) Repetitive Rototest Inspections

    Within the applicable compliance times specified in table 1 to 
paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and

[[Page 34452]]

(j) of this AD: Do a rototest inspection of all holes below each 
door stop fitting at fuselage FR66 and FR68, both left-hand (LH) and 
right-hand (RH) sides, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1288, Revision 01, 
including Appendixes 01, 02, and 03, dated October 3, 2016. Repeat 
the inspections thereafter at the applicable compliance times 
specified in table 1 to paragraphs (g) and (j) of this AD and table 
2 to paragraphs (g) and (j) of this AD, until the modification 
specified in paragraph (i) of this AD is done. Where the 
``Threshold'' column of table 1 to paragraphs (g) and (j) of this AD 
and table 2 to paragraphs (g) and (j) of this AD, specifies 
compliance times in ``FC'' (flight cycles), those compliance times 
are total flight cycles since the first flight of the airplane.

  Table 1 to Paragraphs (g) and (j) of This AD--Aft Passenger/Crew Door
           Cut-Out Door Stop Fittings Holes at FR66 WEB LH/RH
------------------------------------------------------------------------
                                                        Interval (not to
      Airplanes affected              Threshold           exceed) (FC)
------------------------------------------------------------------------
A318-PAX (A318-passenger).....  Before 33,800 FC.....             5,900.
A319-PAX pre-mod 160001 and     Before 42,700 FC.....             7,500.
 pre-mod 160080.
A319-PAX post-mod 160001 OR     Before 40,300 FC.....             7,200.
 A319-PAX post-mod 160080.
A320 pre-mod 160001 and pre-    Before 48,000 FC.....             9,700.
 mod 160080.
A320 post-mod 160001 OR A320    Before 45,500 FC.....             7,800.
 post-mod 160080.
A321 pre-mod 160021...........  Before 34,500 FC or              17,000.
                                 before November 30,
                                 2017, whichever is
                                 later, without
                                 exceeding the
                                 accumulation of
                                 42,300 FC since
                                 first flight.
A321 post-mod 160021..........  39,400 FC............             8,500.
------------------------------------------------------------------------


  Table 2 to Paragraphs (g) and (j) of This AD--Aft Passenger/Crew Door
           Cut-Out Door Stop Fittings Holes at FR68 WEB LH/RH
------------------------------------------------------------------------
                                                        Interval (not to
      Airplanes affected              Threshold          exceed)  (FC)
------------------------------------------------------------------------
A318-PAX......................  Before 30,800........             5,900.
A319-PAX pre-mod 160001 and     Before 34,400........             7,500.
 pre-mod 160080.
A319-PAX post-mod 160001 OR     Before 33,500........             7,200.
 A319-PAX post-mod 160080.
A320..........................  Before 40,900........             9,700.
A321 pre-mod 160021...........  Before 24,400 FC or              13,600.
                                 before November 30,
                                 2017, whichever is
                                 later, without
                                 exceeding the
                                 accumulation of
                                 39,300 FC since
                                 first flight.
A321 post-mod 160021..........  Before 39,300........             8,500.
------------------------------------------------------------------------

(h) Airworthiness Limitations Item (ALI) Inspections Accomplished 
Before the Effective Date of This AD

    Inspections accomplished as specified in ALI task 534129 or ALI 
task 534130 before the effective date of this AD are acceptable for 
compliance with the inspection required by paragraph (g) of this AD. 
As of the effective date of this AD, repetitive inspections must be 
continued as required by paragraph (g) of this AD.

(i) Optional Modification

    For airplanes on which no cracks were detected during any 
rototest inspection required by paragraph (g) of this AD: Modifying 
the affected area by cold working the fastener holes before further 
flight after no cracks were detected, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1290, 
Revision 01, dated October 3, 2016, terminates the repetitive 
inspections required by paragraph (g) of this AD for the modified 
area only.

(j) Post-Modification Repetitive Inspections

    For airplanes on which the modification specified in paragraph 
(i) of this AD has been done: At the compliance time specified in 
paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable, 
accomplish a rototest inspection of all holes at the door stop 
fitting locations at fuselage FR66 and FR68, both LH and RH sides, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 
03, dated October 3, 2016. Repeat the inspection thereafter at 
intervals not to exceed the applicable compliance times in table 1 
to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) 
and (j) of this AD.
    (1) For airplanes with less than 1,800 flight cycles accumulated 
since first flight of the airplane at the time of accomplishing the 
modification specified in paragraph (i) of this AD: At the 
applicable initial compliance time specified in table 1 to 
paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and 
(j) of this AD.
    (2) For airplanes with 1,800 flight cycles or more and less than 
13,800 flight cycles accumulated since first flight of the airplane 
at the time of accomplishing the modification specified in paragraph 
(i) of this AD: Before the accumulation of 48,000 flight cycles 
since first flight of the airplane.
    (3) For airplanes with 13,800 flight cycles or more accumulated 
since first flight of the airplane at the time of accomplishing the 
modification specified in paragraph (i) of this AD: Before the 
accumulation of 60,000 flight cycles since first flight of the 
airplane.

(k) Repair

    If, during any inspection required by paragraph (g) or (j) of 
this AD, any crack is detected, before further flight, repair using 
a method approved by the Manager, International Branch, ANM-116, 
FAA, Transport Airplane Directorate; or the European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). 
Repair of an airplane as required by this paragraph does not 
constitute terminating action for the repetitive inspections 
required by paragraph (g) or (j) of this AD for that airplane, 
unless specified otherwise in instructions approved using a method 
approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate; or the EASA; or Airbus's EASA DOA.

(l) Post-Repair Actions for Certain Airplanes

    For an airplane that has been inspected as specified in ALI task 
534129 or task 534130 and repaired before the effective date of this 
AD as specified in the applicable structural repair manual or as 
specified in an Airbus repair design approval sheet (RDAS): Comply

[[Page 34453]]

with the requirements of paragraphs (l)(1) and (l)(2) of this AD.
    (1) For all fastener holes where no damage or cracks were 
detected (i.e., those not repaired), accomplish the actions required 
by paragraph (g) of this AD, unless the terminating action specified 
in paragraph (m) of this AD has been done.
    (2) For all repaired fastener holes: Within 30 days after the 
effective date of this AD, or within a compliance time approved by 
the Manager, International Branch, ANM-116, FAA, Transport Airplane 
Directorate; or the EASA; or Airbus's EASA DOA, whichever occurs 
later, contact the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate; or the EASA; or Airbus's EASA DOA; 
for inspection instructions and applicable corrective actions, and 
do the inspections and applicable corrective actions accordingly.

(m) Terminating Action for Certain Airplanes

    For airplanes that have been inspected, as specified in ALI task 
534129 or task 534130, and repaired before the effective date of 
this AD, as specified in the applicable structural repair manual, or 
as specified in an Airbus RDAS: Modification of the four fastener 
holes at door stop locations where no damage or crack was detected 
(i.e., door stop locations not repaired) by cold working holes 
before further flight after no cracks were detected, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-53-1290, Revision 01, dated October 3, 2016, constitutes 
terminating action for the repetitive inspections of those four 
fastener holes at those door stop locations as required by paragraph 
(g) or (l)(1) of this AD for that airplane.

(n) Actions for Airplanes With Certain Repairs

    For an airplane that has been repaired before the effective date 
of this AD in the areas described in this AD using an Airbus RDAS 
unrelated to ALI task 534129 or task 534130: Before exceeding the 
compliance times specified in paragraph (g) of this AD, contact the 
Manager, International Branch, ANM-116, FAA, Transport Airplane 
Directorate; or the EASA; or Airbus's EASA DOA; for corrective 
action instructions and accomplish those instructions accordingly. 
Accomplishment of corrective action(s) on an airplane, as required 
by this paragraph, does not constitute terminating action for the 
repetitive inspections as required by paragraph (g) or (j) of this 
AD for that airplane, as applicable, unless specified otherwise in 
the instructions.

(o) Terminating Action for ALI Tasks

    (1) Accomplishment of inspections on an airplane, as required by 
paragraph (g), (j), or (l) of this AD, as applicable, constitutes 
terminating action for the inspection requirements of ALI task 
534129 or task 534130, as applicable, for that airplane.
    (2) Modification of the four fastener holes at a door stop 
location of an airplane as specified in paragraph (i) or (m) of this 
AD, as applicable, and subsequent initial inspection required by 
paragraph (j) of this AD, constitutes terminating action for the 
inspection requirements of ALI task 534129 or task 534130, as 
applicable, for those holes for that airplane. Subsequent repetitive 
inspections are required by paragraph (j) of this AD.

(p) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g) and (j) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-53-1288, including Appendixes 01 and 02, dated October 10, 
2014.
    (2) This paragraph provides credit for actions required by 
paragraphs (i) and (m) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-53-1290, dated October 10, 2014.

(q) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Branch, send it to the 
attention of the person identified in paragraph (r)(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: 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 EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(r) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0238, dated December 2, 
2016, corrected January 4, 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-
2017-0707.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149.
    (3) For 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 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 July 13, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-15485 Filed 7-24-17; 8:45 am]
 BILLING CODE 4910-13-P