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[Federal Register Volume 79, Number 48 (Wednesday, March 12, 2014)]
[Proposed Rules]
[Pages 13944-13948]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-05436]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0138; Directorate Identifier 2013-NM-020-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) 95-24-04, 
that applies to all Airbus Model A300 series airplanes; 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). AD 95-24-04 requires repetitive inspections to detect 
cracks at the aft spar web of the wings, and repair if necessary. Since 
we issued AD 95-24-04, we have determined that the inspection threshold 
and interval must be reduced to allow timely detection of cracks and 
accomplishment of applicable repairs, because of cracking in the rear 
spar web of the wings between certain ribs due to fatigue-related high 
shear stress. This proposed AD would reduce the inspection compliance 
time and interval, and would expand the applicability to airplanes on 
which a certain Airbus modification has been embodied in production and 
to airplanes on which a certain Airbus service bulletin has been 
embodied in service. We are proposing this AD to detect and correct 
fatigue-related cracking, which could result in reduced structural 
integrity of the wing.

DATES: We must receive comments on this proposed AD by April 28, 2014.

ADDRESSES: You may send comments 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 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 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; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the MCAI, 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 proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0138; 
Directorate Identifier 2013-NM-020-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

[[Page 13945]]

substantive verbal contact we receive about this proposed AD.

Discussion

    On November 9, 1995, we issued AD 95-24-04, Amendment 39-9436 (60 
FR 58213, November 27, 1995). AD 95-24-04 required actions intended to 
address an unsafe condition on all Airbus Model A300 series airplanes; 
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).
    Since we issued AD 95-24-04, Amendment 39-9436 (60 FR 58213, 
November 27, 1995), the European Aviation Safety Agency (EASA), which 
is the Technical Agent for the Member States of the European Community, 
has issued EASA Airworthiness Directive 2013-0013R1, dated February 20, 
2013 (referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Wing fatigue tests carried out by Airbus revealed cracks on the 
vertical web of the rear spar between Ribs 1 and 2. Similar cracks 
in the same area were reportedly found by A300 aeroplane operators. 
In all cases, the cracks ran from the tip of the build slot to the 
nearest adjacent bolt hole.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this unsafe condition, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued * * * [an 
AD] to require an eddy current inspection of the aft face of the 
wing rear spar in the area adjacent to the build slot on Left Hand 
(LH) and Right Hand (RH) wings.
    Since that [French] AD was issued, a fleet survey and updated 
fatigue and damage tolerance analysis were performed in order to 
substantiate the second A300-600 Extended Service Goal (ESG2) 
exercise. The results of the survey and analysis showed that the 
inspection threshold and interval must be reduced to allow timely 
detection of cracks and accomplishment of an applicable corrective 
action.
    Prompted by these findings, Airbus issued Airbus Service 
Bulletin (SB) A300-57-6059 Revision 04.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 1997-375-239(B)R3, which is 
superseded, but redefines the thresholds and intervals. This [EASA] 
AD also expands the applicability to aeroplanes on which Airbus 
modification (mod) 12102 has been embodied in production and to 
aeroplanes on which Airbus SB A300-57-6063 (Airbus mod 11130) has 
been embodied in service.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2014-0138.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A300-57-6059, Revision 
04, dated February 22, 2011. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.
    For pre-Airbus Modification 11130 (Airbus Service Bulletin A300-57-
6063) airplanes, the compliance times are dependent on airplane 
configuration and utilization. The initial inspection thresholds 
described in Airbus Mandatory Service Bulletin A300-57-6059, Revision 
04, dated February 22, 2011, range between 18,000 and 23,300 total 
flight cycles, and between 29,100 and 46,600 total flight hours. The 
``grace period'' specified in Airbus Mandatory Service Bulletin A300-
57-6059, Revision 04, dated February 22, 2011, is either 1,000 flight 
cycles, or 1,600 flight hours, or 2,100 flight hours. The repetitive 
inspection interval ranges between 4,800 and 6,100 flight cycles, and 
between 7,700 and 12,300 flight hours.
    For post-Airbus Modification 11130 (Airbus Service Bulletin A300-
57-6063) airplanes or post-Airbus production Modification 12102 
airplanes, the compliance times are dependent on airplane configuration 
and utilization. The initial inspection thresholds described in Airbus 
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February 
22, 2011, range between 29,900 and 38,700 total flight cycles, and 
between 48,400 and 77,500 total flight hours. The ``grace period'' 
specified in Airbus Mandatory Service Bulletin A300-57-6059, Revision 
04, dated February 22, 2011, is either 800 or 1,000 flight cycles, or 
1,200 or 1,700 flight hours. The repetitive inspection interval ranges 
between 5,100 and 6,500 flight cycles, or between 8,200 and 13,100 
flight hours.

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.

Repair Approvals

    In many FAA transport ADs, when the service information specifies 
to contact the manufacturer for further instructions if certain 
discrepancies are found, we typically include in the AD a requirement 
to accomplish the action using a method approved by either the FAA or 
the State of Design Authority (or its delegated agent).
    We have recently been notified that certain laws in other countries 
do not allow such delegation of authority, but some countries do 
recognize design approval organizations. In addition, we have become 
aware that some U.S. operators have used repair instructions that were 
previously approved by a State of Design Authority or a Design Approval 
Holder (DAH) as a method of compliance with this provision in FAA ADs. 
Frequently, in these cases, the previously approved repair instructions 
come from the airplane structural repair manual or the DAH repair 
approval statements that were not specifically developed to address the 
unsafe condition corrected by the AD. Using repair instructions that 
were not specifically approved for a particular AD creates the 
potential for doing repairs that were not developed to address the 
unsafe condition identified by the MCAI AD, the FAA AD, or the 
applicable service information, which could result in the unsafe 
condition not being fully corrected.
    To prevent the use of repairs that were not specifically developed 
to correct the unsafe condition, certain requirements of this proposed 
AD specify that the repair approval specifically refer to the FAA AD. 
This change is intended to clarify the method of compliance and to 
provide operators with better visibility of repairs that are 
specifically developed and approved to correct the unsafe condition. In 
addition, we use the phrase ``its delegated agent, or the DAH with 
State of Design Authority design organization approval, as applicable'' 
in this proposed AD to refer to a DAH authorized to approve certain 
required repairs for this proposed AD.

Differences Between This AD and the MCAI or Service Information

    Although the MCAI or service information allows further flight 
after cracks are found during compliance with the required action, 
paragraphs (k) and (n) of this proposed AD would require that you 
repair any cracking before further flight.

Costs of Compliance

    We estimate that this proposed AD affects 71 products of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 13946]]

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspection [actions retained from  3 work-hour x $85              $0  $255 per inspection   $18,105 per
 AD 95-24-04, Amendment 39-9436     per hour = $255 per                cycle.                inspection cycle.
 (60 FR 58213, November 27,         inspection cycle.
 1995)].
Inspection [new proposed action].  3 work-hour x $85               0  $255 per inspection   $18,105 per
                                    per hour = $255 per                cycle.                inspection cycle.
                                    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.

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 removing airworthiness directive (AD) 
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), and 
adding the following new AD:

Airbus: Docket No. FAA-2014-0138; Directorate Identifier 2013-NM-
020-AD.

(a) Comments Due Date

    We must receive comments by April 28, 2014.

(b) Affected ADs

    This AD supersedes AD 95-24-04, Amendment 39-9436 (60 FR 58213, 
November 27, 1995).

(c) Applicability

    This AD applies to the Airbus airplanes specified in paragraphs 
(c)(1) through (c)(5) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes
    (3) Airbus Model A300 B4-605R and B4-622R airplanes.
    (4) Airbus Model A300 F4-605R airplanes.
    (5) Airbus Model A300 C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by a determination that the inspection 
compliance time and interval must be reduced to allow timely 
detection of cracks and accomplishment of applicable repairs if 
necessary because of cracking in the rear spar web of the wings 
between certain ribs due to fatigue-related high shear stress. We 
are issuing this AD to detect and correct fatigue-related cracking, 
which could result in reduced structural integrity of the wing.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Inspection of Model A300 B2 Series Airplanes

    This paragraph restates the requirements of paragraph (a) of AD 
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with 
no changes. For Model A300 B2 series airplanes: Prior to the 
accumulation of 18,000 total flight cycles, or within 1,400 flight 
cycles after December 27, 1995 (the effective date of AD 95-24-04), 
whichever occurs later, perform a high frequency eddy current (HFEC) 
inspection to detect cracks at the aft spar web of the wings, in 
accordance with Airbus Service Bulletin A300-57-0213, dated August 
12, 1994. Repeat the inspection thereafter at intervals not to 
exceed 5,000 flight cycles.

(h) Retained Inspection of Model A300 B4-103, and B4-2C Series 
Airplanes

    This paragraph restates the requirements of paragraph (b) of AD 
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with 
no changes. For Model A300 B4-103, and B4-2C series airplanes: Prior 
to the accumulation of 19,000 total flight cycles, or within 1,400 
flight cycles after December 27, 1995 (the effective date of AD 95-
24-04), whichever occurs later, perform an HFEC inspection to detect 
cracks at the aft spar web of the wings, in accordance with Airbus 
Service Bulletin A300-57-0213, dated August 12, 1994. Repeat the 
inspection thereafter at intervals not to exceed 6,000 flight 
cycles.

(i) Retained Inspection of Model A300 B4-200 Series Airplanes

    This paragraph restates the requirements of paragraph (c) of AD 
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with 
no changes. For Model A300 B4-200 series airplanes: Prior to the 
accumulation of 17,000 total flight cycles, or within 1,400 flight 
cycles after December 27, 1995 (the effective date of AD 95-24-04), 
whichever occurs later, perform an HFEC inspection to detect cracks 
at the aft spar web of the wings,

[[Page 13947]]

in accordance with Airbus Service Bulletin A300-57-0213, dated 
August 12, 1994. Repeat the inspection thereafter at intervals not 
to exceed 5,000 flight cycles.

(j) Retained Inspection of Model A300-600 B4-601, B4-603, B4-620, B4-
622, B4-605R, B4-622R, and F4-605R Series Airplanes

    This paragraph restates the requirements of paragraph (d) of AD 
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with 
no changes. For Model A300-600 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, and F4-605R series airplanes: Prior to the 
accumulation of 21,600 flight cycles, perform an HFEC inspection to 
detect cracks at the aft spar web of the wings, in accordance with 
Airbus Service Bulletin A300-57-6059, dated August 12, 1994. Repeat 
the inspection thereafter at intervals not to exceed 5,700 flight 
cycles. Accomplishment of the initial inspection required by 
paragraph (l) of this AD terminates the requirements of this 
paragraph.

(k) Retained Repairs

    This paragraph restates the requirements of paragraph (e) of AD 
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with 
new actions.
    (1) Before the effective date of this AD, if any crack is 
detected during any inspection required by paragraphs (g) though (j) 
of this AD: Prior to further flight, repair the crack, in accordance 
with Airbus Service Bulletin A300-57-0213, dated August 12, 1994; or 
Airbus Service Bulletin A300-57-6059, dated August 12, 1994; as 
applicable; or in accordance with a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA.
    (2) As of the effective date of this AD, if any crack is 
detected during any inspection required by paragraphs (g) though (j) 
of this AD: Before further flight, repair the crack, in accordance 
with Airbus Service Bulletin A300-57-0213, dated August 12, 1994 
(for Model A300 B2 series airplanes, and Model A300 B4-103 and B4-2C 
series airplanes); or Airbus Mandatory Service Bulletin A300-57-
6059, Revision 04, dated February 22, 2011 (for Model A300-600 B4-
601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R series 
airplanes); except if Airbus Service Bulletin A300-57-0213, dated 
August 12, 1994; or Airbus Mandatory Service Bulletin A300-57-6059, 
Revision 04, dated February 22, 2011; specifies to contact Airbus 
for an approved repair, before further flight, repair the crack 
using a method approved by either the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the European 
Aviation Safety Agency (EASA) (or its delegated agent, or the Design 
Approval Holder with the EASA design organization approval, as 
applicable). For a repair method to be approved, the repair approval 
must specifically refer to this AD.

(l) New Repetitive Inspections

    For airplanes identified in paragraphs (c)(2) through (c)(5) of 
this AD: At the later of the compliance times specified in paragraph 
(l)(1) and (l)(2) of this AD, perform an HFEC inspection to detect 
cracks of the aft face of the wing rear spar web in the area 
adjacent to the build slot, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A300-57-6059, 
Revision 04, dated February 22, 2011. Repeat the inspection 
thereafter at the applicable compliance time specified in Airbus 
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February 
22, 2011, except as specified in paragraph (m) of this AD. 
Accomplishment of the initial inspection required by this paragraph 
terminates the requirements of paragraph (j) of this AD.
    (1) At the earlier of the applicable compliance times specified 
in the ``Threshold Inspection'' column in table 1 through table 4 of 
paragraph 1.E., ``Compliance,'' of Airbus Mandatory Service Bulletin 
A300-57-6059, Revision 04, dated February 22, 2011. Where Airbus 
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February 
22, 2011, specifies ``(FH)'' and ``(FC)'' in the ``Threshold 
Inspection'' columns, this AD specifies ``total flight hours'' and 
``total flight cycles.''
    (2) At the earlier of the applicable compliance times specified 
in the ``Grace Period'' column in table 1 through table 4 of 
paragraph 1.E., ``Compliance,'' of Airbus Mandatory Service Bulletin 
A300-57-6059, Revision 04, dated February 22, 2011. Where Airbus 
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February 
22, 2011, specifies ``(FH)'' and ``(FC)'' in the ``Grace Period'' 
columns, this AD specifies ``flight hours'' and ``flight cycles.'' 
Where Airbus Mandatory Service Bulletin A300-57-6059, Revision 04, 
dated February 22, 2011, specifies a grace period, this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.

(m) Compliance Time Exceptions

    The repetitive inspection required by paragraph (l) of this AD 
is to be accomplished at the earlier of the applicable compliance 
time specified in column ``Repeat Interval'' of table 1 through 
table 4 of Airbus Mandatory Service Bulletin A300-57-6059, Revision 
04, dated February 22, 2011. Where Airbus Mandatory Service Bulletin 
A300-57-6059, Revision 04, dated February 22, 2011, specifies 
``(FC)'' and ``(FH)'' in the ``Repeat Interval'' columns, this AD 
specifies ``flight hours'' and ``flight cycles.''

(n) New Repair

    If any crack is detected during any inspection required by 
paragraph (l) of this AD: Before further flight, repair the crack, 
in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February 
22, 2011. Where Airbus Mandatory Service Bulletin A300-57-6059, 
Revision 04, dated February 22, 2011, specifies to contact Airbus 
for an approved repair: Before further flight, repair the crack 
using a method approved by either the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the European 
Aviation Safety Agency (EASA) (or its delegated agent, or the Design 
Approval Holder with the EASA design organization approval, as 
applicable). For a repair method to be approved, the repair approval 
must specifically refer to this AD. Repair of any cracking as 
required by this paragraph does not terminate the repetitive 
inspections required by paragraph (l) of this AD.

(o) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraphs (j) and (k) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A300-57-6059, dated August 12, 1994.
    (2) This paragraph provides credit for the actions required by 
paragraphs (j), (k), (l), and (n) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A300-57-6059, Revision 03, dated October 25, 1999, which is 
not incorporated by reference in this AD.

(p) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International 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 Branch, send it 
to ATTN: 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. 
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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or the Design Approval Holder with a State of 
Design Authority's design organization approval, as applicable). You 
are required to ensure the product is airworthy before it is 
returned to service.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Airworthiness Directive 2013-0013R1, dated February 20, 2013, 
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 it in Docket No. FAA-2014-0138.
    (2) 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 account.airworth-eas@airbus.com; 
Internet http://www.airbus.com. You may view this referenced service

[[Page 13948]]

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 February 28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-05436 Filed 3-11-14; 8:45 am]
BILLING CODE 4910-13-P
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