
[Federal Register Volume 76, Number 193 (Wednesday, October 5, 2011)]
[Proposed Rules]
[Pages 61645-61647]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-25570]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0997; Directorate Identifier 2011-NM-043-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-200 Series Airplanes; 
Model A330-300 Series Airplanes; Model A340-200 Series Airplanes; and 
Model 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 another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

    During fatigue testing of the MLG [main landing gear], three 
failures of the retraction bracket occurred before the calculated 
life limitation. Further analysis has confirmed that those failures 
were due to fatigue initiated by fretting between the bush and lug 
bore.
    The failure of the retraction bracket, if not detected, could 
lead to a MLG extension with no damping resulting in MLG structural 
damage.
* * * * *
    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 November 21, 
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 W12-140, 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--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-2011-0997; 
Directorate Identifier 2011-NM-043-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 2010-0205, dated October 8, 2010 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    During fatigue testing of the MLG [main landing gear], three 
failures of the retraction bracket occurred before the calculated 
life limitation. Further analysis has confirmed that those failures 
were due to fatigue initiated by fretting between the bush and lug 
bore.
    The failure of the retraction bracket, if not detected, could 
lead to a MLG extension with no damping resulting in MLG structural 
damage.
    Airbus carried out an investigation, demonstrating that the life 
limit of retraction brackets must be reduced to 19,800 Landings 
(LDG), which is below the life limit stated in the following A330 
and A340 Airbus ALS Part 4 revisions:

--Airbus A330 ALS Part 4 revision 02 approved by EASA on 16 December 
2009.
--Airbus A340 ALS Part 4 revision 01 approved by EASA on 15 December 
2009.

    In order to maintain the structural integrity of the aeroplane, 
this [EASA] AD requires the replacement of these MLG retraction 
brackets before the accumulation of 19,800 total LDG.

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

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.

[[Page 61646]]

    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 29 products of U.S. registry. We also estimate that 
it would take about 25 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Required parts would cost about $200,000 per product. Where 
the service information lists required parts costs that are covered 
under warranty, we have assumed that there will be no charge for these 
parts. As we do not control warranty coverage for affected parties, 
some parties may incur costs higher than estimated here. Based on these 
figures, we estimate the cost of the proposed AD on U.S. operators to 
be $5,861,625, or $202,125 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); 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-2011-0997; Directorate Identifier 2011-NM-
043-AD.

Comments Due Date

    (a) We must receive comments by November 21, 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; except airplanes on which Airbus modification 54500 has 
been embodied in production; and except airplanes on which Airbus 
Service Bulletin A330-32-3212 or Airbus Service Bulletin A340-32-
4256 has been embodied in service; as applicable to airplane model.

Subject

    (d) Air Transport Association (ATA) of America Code 32: Landing 
Gear.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    During fatigue testing of the MLG [main landing gear], three 
failures of the retraction bracket occurred before the calculated 
life limitation. Further analysis has confirmed that those failures 
were due to fatigue initiated by fretting between the bush and lug 
bore.
    The failure of the retraction bracket, if not detected, could 
lead to a MLG extension with no damping resulting in MLG structural 
damage.
* * * * *

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.

Actions

    (g) Before the accumulation of 19,800 total landings on the 
retraction brackets of the main landing gear or within 900 flight 
hours after the effective date of this AD, whichever occurs later: 
Replace the affected retraction bracket of the MLG specified in 
table 1 of this AD with a serviceable part, in accordance with a 
method approved by the Manager, International Branch, ANM-116, FAA, 
or European Aviation Safety Agency (EASA) (or its delegated agent). 
Thereafter, before the accumulation of 19,800 total landings on any 
retraction bracket of the MLG identified in table 1 of this AD, 
replace the retraction bracket with a serviceable part, in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, FAA, or EASA (or its delegated agent).

                 Table 1--Retraction Bracket of the MLG
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                        Nomenclature                           Part Nos.
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Retraction Bracket of the MLG...............................   201478303
                                                               201478304
                                                               201478305
                                                               201478306
                                                               201478307
                                                               201478308
                                                               201428380
                                                               201428381
                                                               201428382
                                                               201428383
                                                               201428384
                                                               201428385
                                                               201428378
                                                               201428379
                                                               201428351
                                                               201428352
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    Note 1:  Additional guidance for the replacement can be found in 
Task 32-11-11-400-804-A, Removal of the MLG Retraction Bracket 
Assembly, and Task 32-11-11-000-804-A, Installation of the MLG 
Retraction Bracket Assembly, of subsection 32-11-11 of Chapter 32 of 
the Airbus A330 Aircraft Maintenance Manual, Revision 36, dated 
January 1, 2011.


    Note 2: ``Total landings'' are the accumulated landings since 
the initial entry of the MLG retraction bracket into service on any 
airplane.


    Note 3: The initial entry into service for the transferable 
systems components/items is defined as the date at which the 
component/item accomplishes the first flight for which it will 
undertake its intended function.


[[Page 61647]]



FAA AD Differences

    Note 4:  This AD differs from the MCAI and/or service 
information as follows: No differences.

Other FAA AD Provisions

    (h) 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: 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.

Related Information

    (i) Refer to MCAI Airworthiness Directive EASA 2010-0205, dated 
October 8, 2010, for related information.

    Issued in Renton, Washington, on September 22, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-25570 Filed 10-4-11; 8:45 am]
BILLING CODE 4910-13-P


