
[Federal Register Volume 80, Number 130 (Wednesday, July 8, 2015)]
[Proposed Rules]
[Pages 38992-38995]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-16583]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2458; Directorate Identifier 2014-NM-122-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 all 
Airbus Model A318, A319, and A321 series airplanes. This proposed AD 
was prompted by reports of in-flight loss of fixed and hinged main 
landing gear (MLG) fairings, and reports of post-modification MLG fixed 
fairing assemblies that have wear and corrosion. This proposed AD would 
require, for certain airplanes, repetitive replacements of the fixed 
fairing upper and lower attachment studs of both the right-hand (RH) 
and left-hand (LH) MLG; and repetitive inspections for corrosion, wear, 
fatigue, cracking, and loose studs of each forward stud assembly of the 
fixed fairing door upper and lower forward attachment of both RH and LH 
MLG; and replacement if necessary. This proposed AD also provides an 
optional terminating modification for the repetitive replacements of 
the fixed fairing upper and lower attachment studs. We are proposing 
this AD to prevent in-flight detachment of an MLG fixed fairing and 
consequent damage to the airplane.

DATES: We must receive comments on this proposed AD by August 24, 2015.

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: 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 proposed AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this 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-2015-
2458; 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 proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-2458; 
Directorate Identifier 2014-NM-122-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 
Airworthiness Directive 2015-0001R1, dated January 15, 2015 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Model A318, A319, 
A320, and Model A321 series airplanes. The MCAI states:

    Several occurrences of in-flight loss of main landing gear (MLG) 
fixed and hinged fairings were reported. The majority of reported 
events occurred following scheduled maintenance activities. One 
result of the investigation was that a discrepancy between the 
drawing and the maintenance manuals was discovered. The maintenance 
documents were corrected to prevent mis-rigging of the MLG fixed and 
hinged fairings, which could induce fatigue cracking.
    Airbus issued Service Bulletin (SB) A320-52-1083, providing 
instructions for a one-time inspection of the MLG fixed fairing 
composite insert and the surrounding area, replacement of the 
adjustment studs at the lower forward position and adjustment to the 
new clearance tolerances. That SB was replaced by Airbus SB A320-52-
1100 (mod 27716) introducing a re-designed location stud, rod end 
and location plate at the forward upper and lower leg fixed-fairing 
positions. Subsequently, reports were received of post-mod 27716/
post-SB A320-52-1100 MLG fixed fairing assemblies with corrosion, 
which could also induce cracking.
    This condition, if not detected and corrected, could lead to 
further cases of in-flight detachment of a MLG fixed fairing, 
possibly resulting in injury to persons on the ground and/or damage 
to the aeroplane.
    To address this potential unsafe condition, EASA issued AD 2014-
0096 [http://ad.easa.europa.eu/blob/easa_ad_2014_0096_superseded.pdf/AD_2014-0096_1] to require [for 
certain airplanes] repetitive detailed inspections (DET) of the MLG 
fixed fairings,

[[Page 38993]]

and, depending on findings, accomplishment of applicable corrective 
actions. That [EASA] AD also prohibited installation of certain MLG 
fixed fairing rod end assemblies and studs as replacement parts on 
aeroplanes incorporating Airbus mod 27716 in production, or modified 
in accordance with Airbus SB A320-52-1100 (any revision) in service.
    Since EASA AD 2014-0096 was issued, Airbus developed an 
alternative inspection programme to meet the AD requirements. In 
addition, a terminating action (mod 155648) was developed, which is 
to be made available for in service aeroplanes through Airbus SB 
A320-52-1165.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0096, which is superseded, and adds an 
optional terminating action for the repetitive inspections. For 
post-mod aeroplanes, i.e. incorporating Airbus mod 155648 in 
production, or modified by Airbus SB A320-52-1165 in service, the 
only remaining requirement is to ensure that pre-mod components are 
no longer installed.
    Prompted by these developments, EASA issued AD 2015-0001, 
retaining the requirements of EASA AD 2014-0096, which was 
superseded, and adding an optional terminating action for the 
repetitive inspections. For post-mod aeroplanes, i.e. incorporating 
Airbus mod 155648 in production, or modified by Airbus SB A320-52-
1165 in service, the only remaining requirement is to ensure that 
pre-mod components are no longer installed.
    Since that [EASA] AD was issued, it was discovered that a 
certain plate support, Part Number (P/N) D5285600620000 as listed in 
Table 3 of the [EASA] AD, remains part of the post SB A320-52-1165 
configuration and is therefore not affected by any prohibition of 
installation--paragraph (11) of the [EASA] AD. In addition, an error 
was detected in Table 1 of the [EASA] AD (missing P/N plate support) 
and paragraph (9) was found to be incorrectly worded.
    For the reasons described above, this [EASA] AD is revised to 
introduce the necessary corrections.

    Required actions also include, for airplanes in Airbus pre-
modification 27716 and pre-Airbus Service Bulletin A320-52-1100 
configuration on which certain components have been installed, 
repetitive replacements of the fixed fairing upper and lower attachment 
studs of both the RH and LH MLG. An optional terminating modification 
also is provided for the repetitive replacements of the fixed fairing 
upper and lower attachment studs. The optional terminating modification 
includes a resonance frequency inspection for debonding of the 
composite insert and delamination of the honeycomb area around the 
insert, and applicable corrective actions if necessary; and 
installation of new studs, rod ends, and location plates at the forward 
upper and lower leg fixed-fairing positions. An additional optional 
terminating modification, for airplanes in pre-modification 27716 and 
pre-Airbus Service Bulletin A320-52-1100 configuration, includes 
installation of a locking device, new studs, rod ends, and location 
plates at the forward upper and lower leg fixed-fairing positions.
    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-2015-
2458.

Related Service Information Under 1 CFR Part 51

     Airbus has issued Service Bulletin A320-52-1100, Revision 
01, dated March 12, 1999. This service information describes procedures 
for modification of the airplane to post-modification 27716 
configuration (by replacing the location stud, rod end, and location 
plate at the forward upper and lower leg fixed-fairing positions of the 
MLG door assemblies). The modification includes a resonance frequency 
inspection for debonding of the composite insert and delamination of 
the honeycomb area around the insert, and applicable corrective 
actions. Corrective actions include repairing the insert. The actions 
in this service information are an optional terminating modification.
     Airbus has also issued Service Bulletin A320-52-1163, 
dated February 4, 2014. This service information describes procedures 
for inspection of the fixed fairing forward attachments of the MLG door 
assemblies, and replacement of the fixed fairing upper and lower 
attachment studs of the RH and LH MLG door assemblies.
     Airbus has issued Service Bulletin A320-52-1165, dated 
November 3, 2014. This service information describes procedures for 
replacing the fairing attachment stud assemblies of the MLG door 
assembly with new assemblies. The actions in this service information 
are an optional terminating modification.
    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 of this 
AD.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 851 airplanes of U.S. 
registry.
    We also estimate that it would take about 18 work-hours per product 
to comply with the basic inspection requirements of this proposed AD. 
The average labor rate is $85 per work-hour. Required parts would cost 
about $4,110 per product. Based on these figures, we estimate the cost 
of this proposed AD on U.S. operators to be $4,799,640, or $5,640 per 
product.
    We estimate that the optional terminating modification would take 
about 18 work-hours and require parts costing $4,110, for a cost of 
$5,640 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 18 work-hours and require parts costing $4,110, for a cost 
of $5,640 per product. We have no way of determining the number of 
aircraft that might need these actions.
    According to the manufacturer, some of the costs of this proposed 
AD might be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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

[[Page 38994]]

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-2015-2458; Directorate Identifier 2014-NM-
122-AD.

(a) Comments Due Date

    We must receive comments by August 24, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by reports of in-flight loss of fixed and 
hinged main landing gear (MLG) fairings, and reports of post-
modification MLG fixed fairing assemblies that have wear and 
corrosion. We are issuing this AD to prevent in-flight detachment of 
an MLG fixed fairing and consequent damage to the airplane.

(f) Compliance

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

(g) Repetitive Replacements

    For airplanes in pre-modification 27716 and pre-Airbus Service 
Bulletin A320-52-1100 configuration, with any of the components 
installed that are identified in paragraphs (g)(1) through (g)(5) of 
this AD: At the applicable compliance time specified in paragraph 
(h) of this AD, replace fixed fairing upper and lower attachment 
studs of both right-hand (RH) and left-hand (LH) MLG, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-52-1163, dated February 4, 2014. Repeat the replacements 
thereafter at intervals not to exceed 6,500 flight cycles.
    (1) Plate--support having part number (P/N) D5284024820000.
    (2) Plate--support having part number (P/N) D5284024820200.
    (3) Stud--adjustment having P/N D5284024420000.
    (4) Rod end assembly (lower) having P/N D5284000500000.
    (5) Rod end assembly (upper) having P/N D5284000600000.

(h) Compliance Times for the Requirements of Paragraph (g) of this AD

    Do the initial replacement required by paragraph (g) of this AD 
at the latest of the times specified in paragraphs (h)(1) through 
(h)(4) of this AD.
    (1) Before the accumulation of 6,500 total flight cycles since 
the airplane's first flight.
    (2) Within 6,500 flight cycles since the last installation of a 
pre-modification 27716 stud on the airplane.
    (3) Within 1,500 flight cycles after the effective date of this 
AD.
    (4) Within 8 months after the effective date of this AD.

(i) Repetitive Inspections

    For airplanes in post-modification 27716 or post-Airbus Service 
Bulletin A320-52-1100 configuration, with any of the components 
installed that are identified in paragraphs (i)(1), (i)(2), and 
(i)(3) of this AD: At the applicable compliance time specified in 
paragraph (j) of this AD, do a detailed inspection of the LH and RH 
stud assemblies of the fixed fairing door upper and lower forward 
attachments of both RH and LH MLG for indications of corrosion, 
wear, fatigue, cracking, and loose studs, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, 
dated February 4, 2014. Repeat the inspection thereafter at 
intervals not to exceed 12 months. Replacement of both RH and LH MLG 
forward stud assemblies on an airplane, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, 
dated February 4, 2014, extends the interval for the next detailed 
inspection to 72 months; and the inspection must be repeated 
thereafter at intervals not to exceed 12 months.
    (1) Stud--adjustment having P/N D5285600720000.
    (2) Rod end assembly (lower) having P/N D5285600400000.
    (3) Rod end assembly (upper) having P/N D5285600500000.

(j) Compliance Times for the Requirements of Paragraph (i) of This AD

    Do the initial inspection required by paragraph (i) of this AD 
at the latest of the times specified in paragraphs (j)(1) through 
(j)(4) of this AD.
    (1) Before the accumulation of 72 months since the airplane's 
first flight.
    (2) Within 72 months since the last installation of a post-
modification 27716 assembly or since accomplishment of the actions 
specified in Airbus Service Bulletin A320-52-1100.
    (3) Within 1,500 flight cycles after the effective date of this 
AD.
    (4) Within 8 months after the effective date of this AD.

(k) Corrective Action

    If any indication of corrosion, wear, fatigue, cracking, or 
loose studs of any forward stud assembly is found during any 
inspection required by paragraph (i) of this AD, except as specified 
in paragraph (l) of this AD: Before further flight, replace the 
upper and lower fixed fairing forward attachment assemblies of the 
RH and LH MLG, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-52-1163, dated February 4, 2014; or 
Airbus Service Bulletin A320-52-1165, dated November 3, 2014.

(l) Corrective Action or Repetitive Inspections for Certain Corrosion 
Findings

    If any corrosion is found during any inspection required by 
paragraph (i) of this AD on any MLG fixed fairing forward attachment 
stud assembly (upper, lower, LH or RH), but the corroded stud is not 
loose: Do the action specified in paragraph (l)(1) or (l)(2) of this 
AD.
    (1) Before further flight, replace the affected assembly, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1163, dated February 4, 2014; or Airbus Service 
Bulletin A320-52-1165, dated November 3, 2014.
    (2) Within 4 months after finding corrosion, and thereafter at 
intervals not to exceed 4 months, do a detailed inspection for 
indications of corrosion, wear, fatigue, cracking, and loose studs 
of the forward stud assembly of the affected (RH or LH) MLG, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1163, dated February 4, 2014.

(m) Corrective Action for Inspections Specified in Paragraph (l)(2) of 
This AD

    If any indication of wear, fatigue, cracking, or loose studs of 
any forward stud assembly is found during any inspection required by

[[Page 38995]]

paragraph (l)(2) of this AD: Before further flight, replace the 
affected (RH or LH) MLG fixed fairing forward attachment assembly, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1163, dated February 4, 2014; or Airbus Service 
Bulletin A320-52-1165, dated November 3, 2014.

(n) Terminating Action

    (1) Replacement of parts on an airplane, as required by 
paragraph (g), (k), or (l)(1) of this AD, does not constitute 
terminating action for the repetitive inspections required by 
paragraph (i) of this AD, except as specified in paragraph (n)(3) of 
this AD.
    (2) The repetitive replacements required by paragraph (g) of 
this AD may be terminated by modification of the airplane to post-
modification 27716 configuration, including a resonance frequency 
inspection for debonding of the composite insert and delamination of 
the honeycomb area around the insert, and all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-52-1100, Revision 01, dated March 12, 
1999, provided all applicable corrective actions are done before 
further flight. Thereafter, refer to paragraph (i) of this AD to 
determine the compliance time for the next detailed inspection 
required by this AD.
    (3) Modification of an airplane, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-52-1165, 
dated November 3, 2014, constitutes terminating action for actions 
required by paragraphs (g) through (m) of this AD for the airplane 
on which the modification is done.

(o) Exception to Certain AD Actions

    An airplane on which Airbus Modification 155648 has been 
embodied in production is not affected by the requirements of 
paragraphs (g) and (i) of this AD, provided that no affected 
component, identified by part number as listed paragraphs (g)(1) 
through (g)(5) and (i)(1) through (i)(3) of this AD, has been 
installed on that airplane since first flight of the airplane.

(p) Parts Installation Prohibition

    (1) For airplanes in pre-Airbus-Modification 27716 and pre-
Airbus-Service-Bulletin A320-52-1100 configuration: No person may 
install a component identified in paragraphs (g)(1) through (g)(5) 
of this AD on any airplane after doing the actions provided in 
paragraph (n)(2) of this AD.
    (2) For airplanes in post-Airbus-Modification 27716 and post 
Airbus Service Bulletin A320-52-1100 configuration: As of the 
effective date of this AD, no person may install a component 
identified in paragraphs (g)(1) through (g)(5) of this AD on any 
airplane.
    (3) For airplanes in pre-Airbus-Modification 155648 and pre-
Airbus-Service-Bulletin A320-52-1165 configuration: No person may 
install a component identified in paragraphs (g)(1) through (g)(5) 
and (i)(1) through (i)(3) of this AD on any airplane after doing the 
actions provided in paragraph (n)(3) of this AD.
    (4) For airplanes in post-Airbus-Modification 155648 and post-
Airbus-Service-Bulletin A320-52-1165 configuration: As of the 
effective date of this AD, no person may install a component 
identified in (g)(1) through (g)(5) and (i)(1) through (i)(3) of 
this AD on any airplane.

(q) Credit for Previous Actions

    This paragraph provides credit for optional actions provided by 
paragraph (n)(2) of this AD, if those actions were performed before 
the effective date of this AD using Airbus Service Bulletin A320-52-
1100, dated December 7, 1998, which is not incorporated by reference 
in this AD.

(r) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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. The 
AMOC approval letter must specifically reference this AD.
    (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 the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(s) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0001R1, dated January 15, 
2015, 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-2015-2458.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.


    Issued in Renton, Washington, on June 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-16583 Filed 7-7-15; 8:45 am]
 BILLING CODE 4910-13-P


