[Federal Register Volume 77, Number 166 (Monday, August 27, 2012)]
[Proposed Rules]
[Pages 51717-51720]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-20966]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 77, No. 166 / Monday, August 27, 2012 / 
Proposed Rules  

[[Page 51717]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0858; Directorate Identifier 2011-NM-183-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to certain Airbus Model A300 B4-2C, B4-103, and B4-
203 airplanes; and Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, 
and B4-622R airplanes. The existing AD currently requires performing a 
one-time detailed visual inspection of the forward fitting at frame 
(FR) 40 on both sides of the airplane for cracks, and repair if 
necessary. Since we issued that AD, we have received reports that new 
cracks were found in the FR 40 forward fitting. This proposed AD would 
require repetitive detailed inspections of the forward fitting at FR 40 
without nut removal, and a one-time eddy current or liquid penetrant 
inspection of the forward fitting at FR 40 with nut removal, and repair 
if necessary. We are proposing this AD to detect and correct cracking 
of the FR 40 forward fitting, which could result in a deterioration of 
the structural integrity of the frame.

DATES: We must receive comments on this proposed AD by October 11, 
2012.

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--EAW (Airworthiness Office), 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 review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington. 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 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-2012-0858; 
Directorate Identifier 2011-NM-183-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 March 4, 2010, we issued AD 2010-06-05, Amendment 39-16229 (75 
FR 11435, March 11, 2010). That AD required actions intended to address 
an unsafe condition on the products listed above.
    Since we issued AD 2010-06-05, Amendment 39-16229 (75 FR 11435, 
March 11, 2010), we have received reports that additional cracks have 
been found after the modification had been completed. In addition, new 
inspections have been added to address the unsafe condition. The 
European Aviation Safety Agency (EASA), which is the Technical Agent 
for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2011-0163, dated August 30, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    One A300-600 aeroplane operator reported that, during a routine 
inspection, a crack was found in the right hand frame (FR) 40 
forward fitting between stringer 32 and stringer 33. The subject 
aeroplane had previously been modified in accordance with Airbus SB 
A300-57-6053 (Mod. 10453).
    Therefore and pending completion of the full analysis using a 
refined Finite Element Model, EASA issued AD 2009-0094 [which 
corresponds with FAA AD 2010-06-05, Amendment 39-16229 (75 FR 11435, 
March 11, 2010)] to require a one-time Detailed Visual Inspection 
(DVI) of the post-SB A300-57-6053 A300-600 aeroplanes and post-SB 
A300-53-0297 A300 aeroplanes in order to ensure the structural 
integrity of frame 40.
    During a recent maintenance check, on two aeroplanes (one A300B4 
and one A300-600), cracks were found in the FR 40 forward fitting.
    These new crack findings are considered as unexpected, since 
they were found after:

--Application of modification SB A300-57-6053 or SB A300-53-0297 
which cancels the inspection programme, and
--Accomplishment of EASA AD 2009-0094.

    For the reasons described above, this new [EASA] AD, which 
supersedes EASA AD 2009-0094, requires repetitive DVI of the FR 40 
forward fitting (without nut removal), accomplishment of a one time 
Eddy Current

[[Page 51718]]

(EC) inspection or liquid penetrant inspection of this area (with 
nut removal) and, depending on findings, the accomplishment of 
associated corrective action [repair if any cracking found]. Passing 
the EC or liquid penetrant inspection constitutes terminating action 
for the repetitive DVI.

    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued All Operator Telex A300-53A0391, dated August 9, 
2011 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); and All 
Operator Telex A300-57A6111, dated August 9, 2011 (for Model A300 B4-
601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes). The 
actions described in this service information are intended to correct 
the unsafe condition identified in the MCAI.

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

    Based on the service information, we estimate that this proposed AD 
would affect about 134 products of U.S. registry.
    The actions that are required by AD 2010-06-05, Amendment 39-16229 
(75 FR 11435, March 11, 2010), and retained in this proposed AD take 
about 3 work-hours per product, at an average labor rate of $85 per 
work hour. Based on these figures, the estimated cost of the currently 
required actions is $255 per product.
    We estimate that it would take about 3 work-hours per product to 
comply with the new basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of the proposed AD on U.S. operators to be $34,170, or $255 
per product.

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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

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

    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]

    2. The FAA amends Sec.  39.13 by removing Airworthiness Directive 
(AD) 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010), and 
adding the following new AD:

Airbus: Docket No. FAA-2012-0858; Directorate Identifier 2011-NM-
183-AD.

(a) Comments Due Date

    We must receive comments by October 11, 2012.

(b) Affected ADs

    This AD supersedes AD 2010-06-05, Amendment 39-16229 (75 FR 
11435, March 11, 2010).

(c) Applicability

    This AD applies to Airbus airplanes, certificated in any 
category, as identified in paragraphs (c)(1) and (c)(2) of this AD. 
For airplanes on which Airbus Service Bulletin A300-53-0297 or A300-
57-6053 (Airbus Modification 10453), as applicable, have been 
incorporated as a corrective action (repair following crack 
finding), no action is required by this AD.
    (1) Model A300 B4-2C, B4-103, and B4-203 airplanes, all serial 
numbers, modified preventively in service (without any preliminary 
crack findings) as specified in Airbus Service Bulletin A300-53-0297 
(Airbus Modification 10453).
    (2) Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-
622R airplanes, all serial numbers, modified preventively in service 
(without any preliminary crack findings) as specified in Airbus 
Service Bulletin A300-57-6053 (Airbus Modification 10453).

(d) Subject

    Air Transport Association (ATA) of America Code 53, 57: 
Fuselage, Wings.

(e) Reason

    This AD was prompted by reports that cracks were found in the 
frame (FR) 40 forward fitting. We are issuing this AD to detect and 
correct cracking of the FR 40 forward fitting, which could result in 
a deterioration of the structural integrity of the frame.

(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 Detailed Inspection

    This paragraph restates the actions required by paragraphs 
(f)(1), (f)(2), and (f)(3) of AD 2010-06-05, Amendment 39-16229 (75 
FR 11435, March 11, 2010).
    (1) At the applicable time specified in table 1 to paragraph 
(g)(1) of this AD: Do a one-time detailed visual inspection of the 
forward fitting at FR 40 on both sides of the airplane, in 
accordance with Airbus Mandatory Service Bulletin A300-57A6108 (for 
Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R 
airplanes) or A300-53A0387 (for Model A300 B4-2C, B4-103, and B4-203 
airplanes), both including

[[Page 51719]]

Appendices 01 and 02, both dated September 12, 2008.

                            Table 1 to Paragraph (g)(1) of This AD--Compliance Times
----------------------------------------------------------------------------------------------------------------
        Airplane models/configuration                                   Compliance time
----------------------------------------------------------------------------------------------------------------
A300 B4-2C and B4-103 airplanes on which       Prior to the accumulation of 18,000 total flight cycles, or
 Airbus Service Bulletin A300-53-0297 was       within 3 months after April 15, 2010 (the effective date of AD
 done prior to the accumulation of 9,000        2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)),
 total flight cycles.                           whichever occurs later.
A300 B4-2C and B4-103 airplanes on which       Within 5,500 flight cycles after accomplishment of Airbus Service
 Airbus Service Bulletin A300-53-0297 was       Bulletin A300-53-0297, or within 6 months after April 15, 2010
 done on or after the accumulation of 9,000     (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR
 total flight cycles.                           11435, March 11, 2010)), whichever occurs later; except, for
                                                airplanes that, as of April 15, 2010 (the effective date of AD
                                                2010-06-05), have accumulated 11,000 flight cycles or more since
                                                accomplishment of Airbus Service Bulletin A300-53-0297, within 3
                                                months after April 15, 2010 (the effective date of AD 2010-06-
                                                05).
A300 B4-203 airplanes on which Airbus Service  Prior to the accumulation of 15,000 total flight cycles, or
 Bulletin A300-53-0297 was done prior to the    within 3 months after April 15, 2010 (the effective date of AD
 accumulation of 8,300 total flight cycles.     2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)),
                                                whichever occurs later.
A300 B4-203 airplanes on which Airbus Service  Within 4,100 flight cycles after accomplishment of Airbus Service
 Bulletin A300-53-0297 was done on or after     Bulletin A300-53-0297, or within 6 months after April 15, 2010
 the accumulation of 8,300 total flight         (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR
 cycles.                                        11435, March 11, 2010)), whichever occurs later; except, for
                                                airplanes that, as of April 15, 2010 (the effective date of AD
                                                2010-06-05), have accumulated 8,200 flight cycles or more since
                                                accomplishment of Airbus Service Bulletin A300-53-0297, within 3
                                                months after April 15, 2010 (the effective date of AD 2010-06-
                                                05).
A300 B4-601, B4-603, B4-605R, B4-620, B4-622,  Prior to the accumulation of 11,500 total flight cycles, or
 and B4-622R airplanes on which Airbus          within 3 months after April 15, 2010 (the effective date of AD
 Service Bulletin A300-57-6053 was done prior   2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)),
 to the accumulation of 6,100 total flight      whichever occurs later.
 cycles.
A300 B4-601, B4-603, B4-605R, B4-620, B4-622,  Within 3,300 flight cycles after accomplishment of Airbus Service
 and B4-622R airplanes on which Airbus          Bulletin A300-57-6053, or within 6 months after April 15, 2010
 Service Bulletin A300-57-6053 was done on or   (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR
 after the accumulation of 6,100 total flight   11435, March 11, 2010)), whichever occurs later; except, for
 cycles.                                        airplanes that, as of April 15, 2010 (the effective date of AD
                                                2010-06-05), have accumulated 6,600 flight cycles or more since
                                                accomplishment of Airbus Service Bulletin A300-57-6053, within 3
                                                months after April 15, 2010 (the effective date of AD 2010-06-
                                                05).
----------------------------------------------------------------------------------------------------------------

     (2) Except as required by paragraph (g)(3) of this AD: If any 
crack is found during the inspection required by paragraph (g)(1) of 
this AD, before further flight, do a temporary or definitive repair, 
as applicable, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-53-0268, Revision 06, dated January 7, 
2002 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or A300-
57-6052, Revision 03, dated May 27, 2002, including Airbus Drawings 
15R53810394, Issue A, dated December 21, 1998, and 21R57110247, 
Issue A, dated June 20, 1997 (for Model A300 B4-601, B4-603, B4-
605R, B4-620, B4-622, and B4-622R airplanes).
    (3) If any crack found during the inspection required by 
paragraph (g)(1) of this AD cannot be repaired in accordance with 
Airbus Service Bulletin A300-53-0268, Revision 06, dated January 7, 
2002 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or A300-
57-6052, Revision 03, dated May 27, 2002 including Airbus Drawings 
15R53810394, Issue A, dated December 21, 1998, and 21R57110247, 
Issue A, dated June 20, 1997 (for Model A300 B4-601, B4-603, B4-
605R, B4-620, B4-622, and B4-622R airplanes): Contact Airbus for 
repair instructions and, before further flight, repair the crack 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA, or the European Aviation 
Safety Agency (EASA) (or its delegated agent).

(h) Retained Reporting Requirement

    This paragraph restates the requirements of paragraph (f)(4) of 
AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010). 
Submit an inspection report in accordance with Appendix 01 of Airbus 
Mandatory Service Bulletin A300-53A0387, including Appendices 01 and 
02, dated September 12, 2008 (for Model A300 B4-2C, B4-103, and B4-
203 airplanes); or Airbus Mandatory Service Bulletin A300-57A6108, 
including Appendices 01 and 02, dated September 12, 2008 (for Model 
A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R 
airplanes); to the address identified on the reporting sheet, at the 
applicable time specified in paragraph (h)(1) or (h)(2) of this AD.
    (1) If the inspection was done on or after April 15, 2010 (the 
effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, 
March 11, 2010)): Submit the report within 30 days after the 
inspection.
    (2) If the inspection was done before April 15, 2010 (the 
effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, 
March 11, 2010)): Submit the report within 30 days after April 15, 
2010 (the effective date of AD 2010-06-05).

(i) New Requirement: Repetitive Detailed Visual Inspections

    Within 300 flight cycles after the effective date of this AD: 
Perform a detailed inspection for cracks of the forward fitting at 
FR 40 without nut removal on both sides of the airplane, in 
accordance with Airbus All Operator Telex A300-53A0391, dated August 
9, 2011 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or 
Airbus All Operator Telex A300-57A6111, dated August 9, 2011 (for 
Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R 
airplanes). Thereafter, repeat the inspection at intervals not to 
exceed 300 flight cycles.

(j) New Requirement: Eddy Current Inspection or Liquid Penetrant 
Inspection

    Within 36 months after the effective date of this AD: Perform an 
eddy current inspection or a liquid penetrant inspection for cracks 
of the forward fitting at FR 40 with nut removal on both sides of 
the airplane, in accordance with Airbus All Operator Telex A300-
53A0391, dated August 9, 2011 (for Model A300 B4-2C, B4-103, and B4-
203 airplanes); or Airbus All Operator Telex A300-57A6111, dated 
August 9, 2011 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-
622, and B4-622R airplanes).

(k) New Requirement: Corrective Action

    If, during any inspection required by paragraph (i) or (j) of 
this AD, any crack is detected: Before further flight, repair the 
crack in accordance with a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA (or its delegated agent).

[[Page 51720]]

(l) New Requirement: Reporting Requirement

    Submit a one-time report of the findings (both positive and 
negative) of the inspections required by paragraphs (i) and (j) of 
this AD to Airbus, Sebastien Faure, SEES1, SAS--EAW (Airworthiness 
Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; 
telephone +33 5 61 93 31 68; fax +33 5 61 93 36 14; email 
[email protected], at the applicable time specified in 
paragraph (l)(1) or (l)(2) of this AD.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(m) New Requirement: Terminating Action

    Accomplishment of the one-time eddy current inspection or a 
liquid penetrant inspection required by paragraph (j) of this AD, 
including doing all applicable repairs, constitutes terminating 
action for the inspections required by paragraph (i) of this AD.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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; phone: (425) 227-2125; 
fax: (425) 227-1149; email: [email protected]. 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. The 
AMOC approval letter must specifically reference this AD. AMOCs 
approved previously in accordance with AD 2010-06-05, Amendment 39-
16229 (75 FR 11435, March 11, 2010), are approved as AMOCs for the 
corresponding provisions of this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (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.

(o) Related Information

    (1) Refer to MCAI EASA Airworthiness Directive 2011-0163, dated 
August 30, 2011, and the service information in paragraphs (o)(1)(i) 
through (o)(1)(vi) of this AD, for related information.
    (i) Airbus All Operator Telex A300-53A0391, dated August 9, 
2011.
    (ii) Airbus All Operator Telex A300-57A6111, dated August 9, 
2011.
    (iii) Airbus Mandatory Service Bulletin A300-57A6108, including 
Appendices 01 and 02, dated September 12, 2008.
    (iv) Airbus Mandatory Service Bulletin A300-53A0387, including 
Appendices 01 and 02, dated September 12, 2008.
    (v) Airbus Service Bulletin A300-53-0268, Revision 06, dated 
January 7, 2002.
    (vi) Airbus Service Bulletin A300-57-6052, Revision 03, dated 
May 27, 2002, including Airbus Drawings 15R53810394, Issue A, dated 
December 21, 1998, and 21R57110247, Issue A, dated June 20, 1997.
    (2) For service information identified in this AD, contact 
Airbus SAS--EAW (Airworthiness Office), 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 review copies of the 
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.

    Issued in Renton, Washington, on August 17, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-20966 Filed 8-24-12; 8:45 am]
BILLING CODE 4910-13-P