[Federal Register Volume 82, Number 143 (Thursday, July 27, 2017)]
[Proposed Rules]
[Pages 34891-34894]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15553]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0708; Directorate Identifier 2017-NM-035-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) AD 2016-
20-11, for certain Airbus Model A300 B4-600, B4-600R, and F4-600R 
series airplanes, and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes); and Airbus Model 
A310 series airplanes. AD 2016-20-11 requires repetitive inspections of 
the external area of the aft cargo door sill beam for cracking, 
repetitive inspections for fatigue cracking of the cargo door sill 
beam, lock fitting, and torsion box plate, and repair if necessary. 
Since we issued AD 2016-20-11, we have determined that reinforcement of 
the aft cargo door sill beam area is necessary to address the unsafe 
condition, which constitutes terminating action for the repetitive 
inspections. This proposed AD would retain the inspections for 
cracking, and repair if necessary; and require reinforcement of the aft 
cargo door sill beam area. We are proposing this AD to address the 
unsafe condition on these products.

DATES: We must receive comments on this proposed AD by September 11, 
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 
SAS, Airworthiness Office--EAW, 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-
0708; 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
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-2017-0708; 
Directorate Identifier 2017-NM-035-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On September 28, 2016, we issued AD 2016-20-11, Amendment 39-18677 
(81 FR 85837, November 29, 2016) (``AD 2016-20-11''), for certain 
Airbus Model A300-600 series airplanes; and Airbus Model A310 series 
airplanes. AD 2016-20-11 was prompted by reports of fatigue cracks on 
the cargo door sill beam, lock fitting, and torsion box plate. AD 2016-
20-11 requires repetitive ultrasonic and detailed inspections of the 
external area of the aft cargo door sill beam for cracking, repetitive 
high frequency eddy current (HFEC) inspections for fatigue cracking of 
the cargo door sill beam, lock fitting, and torsion box plate, and 
repair if necessary. We issued AD 2016-20-11 to detect and correct 
fatigue cracking of the cargo door sill beam, lock fitting, and torsion 
box plate, which could result in the loss of the door locking function 
and subsequently, loss of the cargo door in flight and rapid 
decompression.
    Since we issued AD 2016-20-11, Airbus has developed a reinforcement 
modification of the aft cargo door sill beam area, which constitutes 
terminating action for the repetitive inspections. We have determined 
the reinforcement of the aft cargo door sill beam area is necessary to 
address the unsafe condition.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0048, dated March 15, 2017; corrected April 20, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300-600 series airplanes; and Airbus Model A310 series airplanes. The 
MCAI states:

    In the frame of the widespread fatigue damage (WFD) compliance 
study and after an in-service occurrence, the area of the aft cargo 
door sill beam and adjacent structure was identified as sensitive to 
the fatigue loads.
    This condition, if not detected and corrected, could lead to 
failure of multiple lock fittings, possibly resulting in loss of the 
cargo door in flight and consequent explosive decompression of the 
aeroplane.

[[Page 34892]]

    To address this potential unsafe condition, Airbus issued Alert 
Operators Transmission (AOT) A53W005-14 providing inspection 
instructions and, consequently, EASA issued Emergency AD 2014-0097-E 
[which corresponded to FAA AD 2014-12-06] to require repetitive 
ultrasonic inspections (US) or detailed inspections (DET) of the aft 
cargo door sill beam area [and corrective actions if necessary].
    After that [EASA] AD was issued, further analysis indicated that 
repetitive high frequency eddy current (HFEC) inspections needed to 
be introduced, and Airbus published Service Bulletin (SB) A310-53-
2139 and SB A300-53-6179 to provide instructions. Prompted by this 
determination, EASA issued AD 2015-0150, retaining the requirements 
of EASA Emergency AD 2014-0097-E, which was superseded, and required 
repetitive HFEC inspections of the concerned areas. The first HFEC 
inspection terminated the repetitive US/DET inspections. That [EASA] 
AD also required the inspection results to be reported.
    Since that [EASA] AD was issued, Airbus developed a 
reinforcement modification of the aft cargo door sill beam area, and 
published Airbus SB A310-53-2141 and SB A300-53-6181, which were 
revised lately, to make this available for in-service application.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2015-0150 [which corresponded to FAA AD 
2016-20-11], which is superseded, and requires modification 
[reinforcement] of the aft cargo door sill beam, which constitutes 
terminating action for the repetitive inspections.
    This [EASA] AD is re-published to correct the compliance time 
description in Table 4.

    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-
0708.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus Service Bulletin A300-53-6181, Revision 
01, dated July 2, 2015; and A310-53-2141, Revision 01, dated July 2, 
2015. This service information describes procedures for reinforcing the 
aft cargo door sill beam. These service bulletins are distinct since 
they apply to different airplane models.
    Airbus has issued Airbus Service Bulletin A300-53-6179, dated 
December 12, 2014; and A310-53-2139, dated December 12, 2014. This 
service information describes procedures for repetitive HFEC 
inspections of the cargo door sill beam, lock fitting, and torsion box 
plate. These service bulletins are distinct since they apply to 
different airplane models.
    Airbus has also issued AOT A53W005-14, Revision 01, dated April 29, 
2014, which describes procedures for doing an ultrasonic inspection or 
detailed inspection of the aft cargo door sill beam external area for 
cracking.
    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.

Costs of Compliance

    We estimate that this AD affects 75 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
----------------------------------------------------------------------------------------------------------------
Inspection (retained actions from  12 work-hours x $85             N/A  $1,020 per           $76,500 per
 AD 2016-20-11).                    per hour = $1,020                    inspection cycle.    inspection cycle.
                                    per inspection
                                    cycle.
Modification (new proposed         40 work-hours x $85         $96,890  $100,290...........  $7,521,750.
 action).                           per hour = $3,400.
Reporting........................  1 work-hour x $85                 0  $85 per inspection   $6,375 per
(retained action from AD 2016-20-   per hour = $85 per                   cycle.               inspection cycle.
 11).                               inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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

[[Page 34893]]

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) 
2016-20-11, Amendment 39-18677 (81 FR 85837, November 29, 2016), and 
adding the following new AD:

Airbus: Docket No. FAA-2017-0708; Directorate Identifier 2017-NM-
035-AD.

(a) Comments Due Date

    We must receive comments by September 11, 2017.

(b) Affected ADs

    This AD replaces AD 2016-20-11, Amendment 39-18677 (81 FR 85837, 
November 29, 2016) (``AD 2016-20-11'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
through (c)(5) of this AD, certificated in any category, all 
manufacturer serial numbers on which Airbus Modification 05438 has 
been embodied in production, except those on which Airbus 
Modification 12046 has been embodied in production.
    (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (2) Airbus Model A300 B4-605R and B4-622R airplanes.
    (3) Airbus Model A300 F4-605R and F4-622R airplanes.
    (4) Airbus Model A300 C4-605R Variant F airplanes.
    (5) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of fatigue cracks on the cargo 
door sill beam, lock fitting, and torsion box plate. We are issuing 
this AD to prevent fatigue cracking of the cargo door sill beam, 
lock fitting, and torsion box plate, which could result in the loss 
of the door locking function and subsequently, loss of the cargo 
door in flight and rapid decompression.

(f) Compliance

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

(g) Retained Inspection, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2016-20-11, with no changes. Within the compliance time identified 
in paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable: Do 
an ultrasonic inspection or detailed inspection of the aft cargo 
door sill beam external area for cracking, in accordance with Airbus 
Alert Operators Transmission (AOT) A53W005-14, dated April 22, 2014; 
or Airbus AOT A53W005-14, Revision 01, dated April 29, 2014. Repeat 
the inspection thereafter at intervals not to exceed 275 flight 
cycles. As of January 3, 2017 (the effective date of AD 2016-20-11), 
use only AOT A53W005-14, Revision 01, dated April 29, 2014, to 
comply with the requirements of this paragraph.
    (1) For airplanes that have accumulated 30,000 flight cycles or 
more since the airplane's first flight as of July 2, 2014 (the 
effective date of AD 2014-12-06, Amendment 39-17867, (79 FR 34403, 
June 17, 2014) (``AD 2014-12-06'')): Within 50 flight cycles after 
July 2, 2014.
    (2) For airplanes that have accumulated 18,000 flight cycles or 
more, but fewer than 30,000 flight cycles since the airplane's first 
flight as of July 2, 2014 (the effective date of AD 2014-12-06): 
Within 275 flight cycles after July 2, 2014.
    (3) For airplanes that have accumulated fewer than 18,000 flight 
cycles since the airplane's first flight as of July 2, 2014 (the 
effective date of AD 2014-12-06): Before exceeding 18,275 flight 
cycles since the airplane's first flight.

(h) Retained Optional Terminating Action, With No Changes

    This paragraph restates the provisions of paragraph (h) of AD 
2016-20-11, with no changes. Accomplishment of a high frequency eddy 
current (HFEC) inspection for cracking, in accordance with Airbus 
AOT A53W005-14, dated April 22, 2014; or AOT A53W005-14, Revision 
01, dated April 29, 2014; terminates the repetitive inspections 
required by paragraph (g) of this AD for that airplane. If any 
cracking is found during the HFEC inspection, before further flight, 
repair 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).

(i) Retained Reporting Requirement, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2016-20-11, with no changes. Submit a report of the findings (both 
positive and negative) of the inspection required by paragraph (g) 
of this AD to ``Airbus Service Bulletin Reporting Online 
Application'' on Airbus World (https://w3.airbus.com/), at the 
applicable time specified in paragraph (i)(1) or (i)(2) of this AD. 
The report must include the inspection results, including no 
findings.
    (1) If the inspection was done on or after January 3, 2017 (the 
effective date of AD 2016-20-11): Submit the report within 30 days 
after the inspection.
    (2) If the inspection was done before January 3, 2017 (the 
effective date of AD 2016-20-11): Submit the report within 30 days 
after January 3, 2017.

(j) Retained Definition of Airplane Groups, With No Changes

    This paragraph restates the definitions specified in paragraph 
(j) of AD 2016-20-11, with no changes. Paragraphs (k)(1), (k)(2), 
and (k)(3) of this AD refer to airplane groups, as identified in 
paragraphs (j)(1), (j)(2), and (j)(3) of this AD.
    (1) Airplanes on which an HFEC inspection was accomplished as 
specified in Airbus AOT A53W005-14.
    (2) Airplanes on which no HFEC inspection was accomplished as 
specified in Airbus AOT A53W005-14, that have accumulated more than 
18,000 total flight cycles as of January 3, 2017 (the effective date 
of AD 2016-20-11).
    (3) Airplanes on which no HFEC inspection was accomplished as 
specified in Airbus AOT A53W005-14, that have accumulated 18,000 
total flight cycles or fewer as of January 3, 2017 (the effective 
date of AD 2016-20-11).

(k) Retained Repetitive HFEC Inspections, With No Changes

    This paragraph restates the requirements of paragraph (k) of AD 
2016-20-11, with no changes. At the applicable time specified in 
paragraph (k)(1), (k)(2), or (k)(3) of this AD: Do an HFEC 
inspection for fatigue cracking of the cargo door sill beam, lock 
fitting, and torsion box plate, in accordance with Airbus Service 
Bulletin A300-53-6179, dated December 12, 2014; or Airbus Service 
Bulletin A310-53-2139, dated December 12, 2014; as applicable. 
Repeat the HFEC inspection thereafter at intervals not to exceed 
4,600 flight cycles.
    (1) For airplanes identified in paragraph (j)(1) of this AD: 
Inspect within 4,600 flight cycles after the most recent HFEC 
inspection specified in Airbus AOT A53W005-14.
    (2) For airplanes identified in paragraph (j)(2) of this AD: 
Inspect within 2,000 flight cycles after January 3, 2017 (the 
effective date of AD 2016-20-11).
    (3) For airplanes identified in paragraph (j)(3) of this AD: 
Inspect before exceeding 13,000 total flight cycles since the 
airplane's

[[Page 34894]]

first flight, or within 2,000 flight cycles after January 3, 2017 
(the effective date of AD 2016-20-11), whichever occurs later.

(l) Retained Corrective Action, With No Changes

    This paragraph restates the requirements of paragraph (l) of AD 
2016-20-11, with no changes. If any crack is found during any 
inspection required by paragraph (g) or (k) of this AD: Before 
further flight, repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the EASA; or Airbus's EASA DOA.

(m) Retained Terminating Action for Repetitive Inspections in Paragraph 
(g) of This AD, With No Changes

    This paragraph restates the terminating action of paragraph 
(m)(1) of AD 2016-20-11, with no changes. For any airplane 
identified in paragraphs (j)(2) and (j)(3) of this AD, 
accomplishment of the initial inspection required by paragraph (k) 
of this AD terminates the repetitive inspections required by 
paragraph (g) of this AD.

(n) New Cargo Door Reinforcement

    At the latest of the applicable times specified in paragraphs 
(n)(1), (n)(2), and (n)(3) of this AD: Reinforce the aft cargo door 
sill beam area, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A310-53-2141, Revision 01, dated July 2, 
2015; or Airbus Service Bulletin A300-53-6181, Revision 01, dated 
July 2, 2015; as applicable.
    (1) Before exceeding 19,600 flight cycles since first flight of 
the airplane.
    (2) Within 2,300 flight cycles after the last HFEC or detailed 
inspection required by this AD that was accomplished before the 
effective date of this AD.
    (3) Within 12 months after the effective date of this AD.

(o) New Terminating Action

    Modification of an airplane as required by paragraph (n) of this 
AD constitutes terminating action for the repetitive inspections 
required by paragraphs (g) and (k) of this AD for that airplane.

(p) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(n) of this AD, if those actions were performed before the effective 
date of this AD using Airbus Service Bulletin A300-53-6181, dated 
June 26, 2015; or Airbus Service Bulletin A310-53-2141, dated June 
26, 2015; as applicable.

(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 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].
    (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 2016-20-11 are approved as 
AMOCs for the corresponding provisions 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 EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.
    (4) Required for Compliance (RC): Except as required by 
paragraph (l) 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 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 2017-0048, dated March 15, 2017; 
corrected April 20, 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-2017-0708.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. You may view this 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, WA.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 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. For information on the availability 
of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on July 14, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-15553 Filed 7-26-17; 8:45 am]
 BILLING CODE 4910-13-P