Document ID: FAA-2011-0387-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Model A330-201, -202, -203, -223, and -243 Airplanes, A330-300, A340-200 and A340-300 Series Airplanes
Posted Date: 2011-05-03T04:00Z

[Federal Register Volume 76, Number 85 (Tuesday, May 3, 2011)]
[Proposed Rules]
[Pages 24832-24836]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-10624]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0387; Directorate Identifier 2010-NM-222-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A330-201, -202, -203, -
223, and -243 Airplanes, A330-300 Series Airplanes, A340-200 Series 
Airplanes, and A340-300 Series 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 the 
products listed above. This proposed AD results from mandatory 
continuing airworthiness information (MCAI) originated by an aviation 
authority of

[[Page 24833]]

another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    Surface defects were visually detected on the rudder of * * * 
[an] in-service aeroplane during scheduled maintenance.
    Investigation has determined that the defects reported on both 
rudders corresponded to areas that had been reworked in production. 
The investigation confirmed that the surface defects were a result 
of de-bonding between the skin and honeycomb core.
* * * * *
    An extended de-bonding, if not detected and corrected, may 
degrade the structural integrity of the rudder. The loss of the 
rudder leads to degradation of the handling qualities and reduces 
the controllability of the aeroplane.
* * * * *
    The proposed AD would require actions that are intended to address 
the unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by June 17, 2011.

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 W12-40, 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--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; e-mail airworthiness.A330-A340@airbus.com; 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; 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-2011-0387; 
Directorate Identifier 2010-NM-222-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 Community, has issued EASA 
Airworthiness Directive 2010-0127, dated June 23, 2010 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Surface defects were visually detected on the rudder of one A319 
and one A321 in-service aeroplane during scheduled maintenance.
    Investigation has determined that the defects reported on both 
rudders corresponded to areas that had been reworked in production. 
The investigation confirmed that the surface defects were a result 
of de-bonding between the skin and honeycomb core.
    Such reworks were also performed on some rudders fitted on A330 
and A340-200/-300 aeroplanes.
    An extended de-bonding, if not detected and corrected, may 
degrade the structural integrity of the rudder. The loss of the 
rudder leads to degradation of the handling qualities and reduces 
the controllability of the aeroplane.
    To address this unsafe condition, EASA issued AD 2010-0021, 
superseding EASA AD 2009-0156, to require inspections of specific 
areas and, depending on findings, the accomplishment of corrective 
actions for those rudders where production reworks have been 
identified.
    In addition, this AD addresses the rudder population that has 
also been reworked in production but is not part of EASA AD 2010-
0021 applicability.

Required actions include vacuum loss and elasticity laminate checker 
inspections for damage including de-bonding between the skin and 
honeycomb core of the rudder on certain areas of the rudder, and repair 
if necessary. You may obtain further information by examining the MCAI 
in the AD docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletins A330-55-3042 and 
A340-55-4038, both dated April 22, 2010. 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.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 55 products of U.S. registry. We also estimate that 
it would take

[[Page 24834]]

about 6 work-hours per product to comply with the 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 $28,050, or $510 per product.
    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this 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); and
    3. 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 adding the following new AD:
Airbus: Docket No. FAA-2011-0387; Directorate Identifier 2010-NM-
222-AD.

Comments Due Date

    (a) We must receive comments by June 17, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A330-201, -202, -203, -223, 
-243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 
airplanes and Model A340-211, -212, -213, -311, -312, and -313 
airplanes; certificated in any category, all manufacturer serial 
numbers, if equipped with rudders having part numbers and serial 
numbers as identified in table 1, table 2, or table 3 of this AD.

 Table 1--Rudder Part Number (P/N) and Affected Rudder Serial Number (S/
                                   N)
------------------------------------------------------------------------
                 Rudder P/N                      Affected rudder  S/N
------------------------------------------------------------------------
F554-70000-000-00..........................  TS-2045
F554-70000-000-00..........................  TS-2046
F554-71000-000-00-0000.....................  TS-3013
F554-71000-000-00-0000.....................  TS-3014
F554-71000-000-00-0000.....................  TS-3020
F554-71000-000-00-0000.....................  TS-3022
F554-71000-000-00-0000.....................  TS-3023
F554-71000-000-00-0000.....................  TS-3027
F554-71000-000-00-0000.....................  TS-3031
F554-71000-000-00-0000.....................  TS-3034
F554-71000-000-00-0000.....................  TS-3036
F554-71000-000-00-0000.....................  TS-3038
F554-71000-000-00-0000.....................  TS-3041
F554-71000-000-00-0000.....................  TS-3046
F554-71000-000-00-0000.....................  TS-3054
F554-70005-000-00-0000.....................  TS-3102
F554-71002-000-00-0002.....................  TS-4018
F554-71002-000-00-0002.....................  TS-4022
F554-71002-000-00-0002.....................  TS-4031
------------------------------------------------------------------------

               Table 2--Rudder P/N and Affected Rudder S/N
------------------------------------------------------------------------
                 Rudder P/N                      Affected Rudder  S/N
------------------------------------------------------------------------
A554-71500-024-00..........................  TS-1014
A554-71500-030-00..........................  TS-1042
F554-70000-000-00..........................  TS-2004
F554-70000-000-00..........................  TS-2005
F554-70000-000-00..........................  TS-2008
F554-70000-000-00..........................  TS-2009
F554-70000-000-00..........................  TS-2010
F554-70000-000-00..........................  TS-2022
F554-70000-000-00..........................  TS-2023
F554-70000-000-00..........................  TS-2028
F554-70000-000-00..........................  TS-2029
F554-70000-000-00..........................  TS-2030
F554-70000-000-00..........................  TS-2032
F554-70000-000-00..........................  TS-2033
F554-70000-000-00..........................  TS-2034
F554-70000-000-00..........................  TS-2041
F554-70000-000-00..........................  TS-2044
F554-70000-000-00..........................  TS-2048
F554-70000-000-00..........................  TS-2049
F554-70000-000-00..........................  TS-2050
F554-70000-000-00..........................  TS-2057
F554-70000-000-00..........................  TS-2067
F554-70000-002-00..........................  TS-2068
F554-70000-002-00..........................  TS-2071
F554-71000-000-00-0000.....................  TS-3001
F554-71000-000-00-0000.....................  TS-3010
F554-71000-000-00-0000.....................  TS-3012
F554-71000-000-00-0000.....................  TS-3017
F554-71000-000-00-0000.....................  TS-3018
F554-71000-000-00-0000.....................  TS-3019
F554-71000-000-00-0000.....................  TS-3021
F554-71000-000-00-0000.....................  TS-3024
F554-71000-000-00-0000.....................  TS-3025
F554-71000-000-00-0000.....................  TS-3026
F554-71000-000-00-0000.....................  TS-3028
F554-71000-000-00-0000.....................  TS-3029
F554-71000-000-00-0000.....................  TS-3030
F554-71000-000-00-0000.....................  TS-3032
F554-71000-000-00-0000.....................  TS-3035
F554-71000-000-00-0000.....................  TS-3037
F554-71000-000-00-0000.....................  TS-3039
F554-71000-000-00-0000.....................  TS-3040
F554-71000-000-00-0000.....................  TS-3042
F554-71000-000-00-0000.....................  TS-3047
F554-71000-000-00-0000.....................  TS-3049
F554-71000-000-00-0000.....................  TS-3055
F554-71000-000-00-0000.....................  TS-3058
F554-71000-000-00-0000.....................  TS-3062
F554-71000-000-00-0000.....................  TS-3063
F554-71000-000-00-0000.....................  TS-3065
F554-71000-000-00-0000.....................  TS-3067
F554-71000-000-00-0000.....................  TS-3069
F554-71000-000-00-0000.....................  TS-3070
F554-71000-000-00-0000.....................  TS-3077
F554-71000-000-00-0000.....................  TS-3078
F554-71000-000-00-0000.....................  TS-3080
F554-71000-000-00-0000.....................  TS-3081
F554-71000-000-00-0000.....................  TS-3086
F554-71000-000-00-0000.....................  TS-3089
F554-71000-000-00-0000.....................  TS-3092
F554-71000-000-00-0000.....................  TS-3093
F554-71000-000-00-0000.....................  TS-3095
F554-71000-000-00-0000.....................  TS-3096
F554-70005-000-00-0000.....................  TS-3098
F554-70005-000-00-0000.....................  TS-3099
F554-70005-000-00-0000.....................  TS-3101
F554-70005-000-00-0000.....................  TS-3103
F554-70005-000-00-0000.....................  TS-3104
F554-70005-000-00-0000.....................  TS-3105
F554-70005-000-00-0000.....................  TS-3108

[[Page 24835]]

 
F554-70005-000-00-0000.....................  TS-3109
F554-70005-000-00-0000.....................  TS-3110
F554-70005-000-00-0000.....................  TS-3111
F554-70005-000-00-0000.....................  TS-3112
F554-70005-000-00-0000.....................  TS-3114
F554-70005-000-00-0000.....................  TS-3116
F554-70005-000-00-0000.....................  TS-3117
F554-70005-000-00-0000.....................  TS-3120
F554-70005-000-00-0000.....................  TS-3131
F554-70005-000-00-0000.....................  TS-3132
F554-70005-000-00-0000.....................  TS-3212
F554-70005-000-00-0002.....................  TS-3323
F554-70005-000-00-0002.....................  TS-3330
F554-71002-000-00-0002.....................  TS-4009
F554-71002-000-00-0002.....................  TS-4010
F554-71002-000-00-0002.....................  TS-4012
F554-71002-000-00-0002.....................  TS-4013
F554-71002-000-00-0002.....................  TS-4014
F554-71002-000-00-0002.....................  TS-4015
F554-71002-000-00-0002.....................  TS-4016
F554-71002-000-00-0002.....................  TS-4017
F554-71002-000-00-0002.....................  TS-4020
F554-71002-000-00-0002.....................  TS-4023
F554-71002-000-00-0002.....................  TS-4025
F554-71002-000-00-0002.....................  TS-4026
F554-71002-000-00-0002.....................  TS-4027
F554-71002-000-00-0002.....................  TS-4029
F554-71002-000-00-0002.....................  TS-4030
F554-71002-000-00-0002.....................  TS-4038
F554-71002-000-00-0002.....................  TS-4047
F554-71002-000-00-0002.....................  TS-4049
F554-71002-000-00-0002.....................  TS-4066
F554-71002-000-00-0003.....................  TS-4083
------------------------------------------------------------------------

               Table 3--Rudder P/N and Affected Rudder S/N
------------------------------------------------------------------------
                 Rudder P/N                      Affected Rudder  S/N
------------------------------------------------------------------------
F554-71000-000-00-0000.....................  TS-3060
F554-71000-000-00-0000.....................  TS-3068
F554-70005-000-00-0000.....................  TS-3128
F554-71002-000-00-0002.....................  TS-4011
------------------------------------------------------------------------

Subject

    (d) Air Transport Association (ATA) of America Code 55: 
Stabilizers.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Surface defects were visually detected on the rudder of * * * 
[an] in-service aeroplane during scheduled maintenance.
    Investigation has determined that the defects reported on both 
rudders corresponded to areas that had been reworked in production. 
The investigation confirmed that the surface defects were a result 
of de-bonding between the skin and honeycomb core.
* * * * *
    An extended de-bonding, if not detected and corrected, may 
degrade the structural integrity of the rudder. The loss of the 
rudder leads to degradation of the handling qualities and reduces 
the controllability of the aeroplane.
* * * * *

Compliance

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

Inspections

    (g) For rudders identified in table 1 and table 2 of this AD, 
within the compliance time in paragraph (g)(1) or (g)(2) of this AD 
as applicable, do a vacuum loss inspection on the rudder non-
ventilated area (Area 1) for damage including de-bonding between the 
skin and honeycomb core of the rudder, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-55-3042 or A340-55-4038, both dated April 22, 2010, as 
applicable.
    (1) For rudders identified in table 1 of this AD: Within 1,800 
flight hours after the effective date of this AD.
    (2) For rudders identified in table 2 of this AD: Within 21 
months after the effective date of this AD.
    (h) For rudders identified in table 1 and table 2 of this AD, 
within 21 months after the effective date of this AD, do an 
elasticity laminate checker inspection on the trailing edge area 
(Area 2) for damage including de-bonding between the skin and 
honeycomb core of the rudder, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or 
A340-55-4038, both dated April 22, 2010, as applicable. Thereafter, 
repeat the inspection two more times at intervals not to exceed 
4,500 flight cycles but not less than 4,000 flight cycles from the 
most recent inspection.
    (i) For rudders identified in table 3 of this AD, within 4,500 
flight cycles but not less than 4,000 flight cycles from the date of 
the sampling inspection identified in table 4 of this AD, or within 
30 days after the effective date of this AD, whichever occurs later, 
do an elasticity laminate checker inspection on the trailing edge 
area for damage including de-bonding between the skin and honeycomb 
core of the rudder, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or 
A340-55-4038, both dated April 22, 2010, as applicable. Repeat the 
inspection once within 4,500 flight cycles after doing the 
inspection but not less than 4,000 flight cycles from the last 
inspection.

                    Table 4--Rudder P/N and Affected Rudder S/N and Sampling Inspection Date
----------------------------------------------------------------------------------------------------------------
                Rudder P/N                      Affected rudder S/N            Date of sampling  inspection
----------------------------------------------------------------------------------------------------------------
F554-71000-000-00-0000...................  TS-3060.....................  March 12, 2009.
F554-71000-000-00-0000...................  TS-3068.....................  April 27, 2009.
F554-70005-000-00-0000...................  TS-3128.....................  July 13, 2009.
F554-71002-000-00-0002...................  TS-4011.....................  February 12, 2009.
----------------------------------------------------------------------------------------------------------------

Corrective Actions

    (j) If damage is found during any inspection required by 
paragraph (g), (h), (i), or (k)(1) of this AD, before further 
flight, repair the damage 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).

Restoration

    (k) If no damage is found during any inspection required by 
paragraph (g) of this AD, before further flight, restore the vacuum 
loss holes by doing a temporary restoration with self-adhesive disks 
or tapes, a temporary restoration with resin, or a permanent 
restoration with resin, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or 
A340-55-4038, both dated April 22, 2010, as applicable. Do the 
applicable actions specified in paragraph (k)(1) or (k)(2) of this 
AD.
    (1) For airplanes on which a temporary restoration with self-
adhesive disks or tapes is done, within 900 flight hours after doing 
the restoration, do a detailed inspection for loose or missing self-
adhesive disks or tapes and repeat the inspection thereafter at 
intervals not to exceed 900 flight hours until the permanent 
restoration is done, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or 
A340-55-4038, both dated April 22, 2010, as applicable. If any loose 
or missing self-adhesive disks or tapes are found during any 
inspection required by this AD, before further flight, close the 
holes, in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A330-55-3042 or A340-55-4038, both dated 
April 22, 2010, as applicable. Do the permanent restoration within 
21 months after doing the temporary restoration, in accordance with 
the Accomplishment Instructions of Airbus

[[Page 24836]]

Mandatory Service Bulletin A330-55-3042 or A340-55-4038, both dated 
April 22, 2010, as applicable.
    (2) For airplanes on which a temporary restoration with resin is 
done: Within 21 months after doing the temporary restoration, do the 
permanent restoration, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or 
A340-55-4038, both dated April 22, 2010, as applicable.

Reporting Requirements

    (l) Submit a report of the findings (positive and negative) of 
the first inspection required by paragraphs (g), (h), and (i) of 
this AD to Airbus, at the applicable time specified in paragraph 
(l)(1) or (l)(2) of this AD. The report must include the inspection 
results, a description of any discrepancies found, the airplane 
serial number, and the number of landings and flight hours on the 
airplane.
    (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.

Parts Installation

    (m) As of the effective date of this AD, no person may install 
any affected rudder listed in table 1, table, 2, or table 3 of this 
AD, on any airplane, unless the rudder is inspected as specified in 
paragraphs (g), (h), and (i) of this AD, as applicable, and all 
applicable corrective actions specified in paragraph (j) of this AD 
and applicable restoration specified in paragraph (k) of this AD are 
done.

FAA AD Differences

    Note 1:  This AD differs from the MCAI and/or service 
information as follows: No differences.

Other FAA AD Provisions

    (n) 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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Information may be e-mailed 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 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.

Related Information

    (o) Refer to MCAI EASA Airworthiness Directive 2010-0127, dated 
June 23, 2010; Airbus Mandatory Service Bulletin A330-55-3042, dated 
April 22, 2010; and Airbus Mandatory Service Bulletin A340-55-4038, 
dated April 22, 2010; for related information.

    Issued in Renton, Washington, on April 20, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-10624 Filed 5-2-11; 8:45 am]
BILLING CODE 4910-13-P