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[Federal Register Volume 76, Number 216 (Tuesday, November 8, 2011)]
[Proposed Rules]
[Pages 69168-69171]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-28833]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1225; Directorate Identifier 2010-NM-269-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; Model 
A300 B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R 
Variant F airplanes (collectively called A300-600 series airplanes); 
and Model A310 series airplanes. 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 a routine visual inspection on two A310 in-service 
aeroplanes, cracks were found in the wing MLG [main landing gear] 
rib 5 aft bearing forward lug. Laboratory examination of the cracked 
ribs confirmed that the cracks were the result of pitting corrosion 
in the forward lug hole. Also on both aeroplanes, medium to heavy 
corrosion was found in the forward lugs on the opposite wing after 
removal of the bushes. * * * This situation, if not corrected, could

[[Page 69169]]

affect the structural integrity of the MLG attachment [which could 
result in the collapse of the MLG].
* * * * *
    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 December 23, 
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-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 account.airworth-eas@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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 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-2011-1225; 
Directorate Identifier 2010-NM-269-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 2010-0251, dated November 29, 2010 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    During a routine visual inspection on two A310 in-service 
aeroplanes, cracks were found in the wing MLG rib 5 aft bearing 
forward lug. Laboratory examination of the cracked ribs confirmed 
that the cracks were the result of pitting corrosion in the forward 
lug hole. Also on both aeroplanes, medium to heavy corrosion was 
found in the forward lugs on the opposite wing after removal of the 
bushes. Similarly to A310 aeroplanes, although there have been no 
reports of crack findings on any A300, A300-600 or A300-600ST 
aeroplanes, the differences in MLG rib 5 design compared to A310 
aeroplanes does not allow the exclusion of the possibility of 
cracks. This situation, if not corrected, could affect the 
structural integrity of the MLG attachment [which could result in 
the collapse of the MLG].
    In order to ensure the detection of any crack at an early stage 
in the forward lug of the RH and LH MLG rib 5 aft bearing forward 
lug, Airbus developed inspection programs which were rendered 
mandatory, initially by EASA AD 2006-0372-E [which corresponds with 
FAA AD 2007-03-18, Amendment 39-14929] and now by AD 2010-0250 
applicable to A300B4/C4/F4 and A300-600 aeroplanes and AD 2007-0195 
[which corresponds with FAA AD 2008-17-02, Amendment 39-15640] 
applicable to A310 aeroplanes.
    More recently, it has been determined that the installation of 
new bushes with increased interference fit adequately corrects the 
unsafe condition and ensures the structural integrity of the MLG 
attachment. Installation of these bushes constitutes terminating 
action for the repetitive inspection requirements of the existing 
EASA AD 2010-0250 for A300B4/C4/F4 and A300-600 aeroplanes, and AD 
2007-0195 for A310 aeroplanes.
    For the reasons described above, this new AD requires 
installation of bushes with increased interference fit in the gear 
rib 5 aft bearing forward lug.

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

Relevant Service Information

    Airbus has issued the following service bulletins:
     Airbus Mandatory Service Bulletin A300-57-0249, Revision 
02, dated June 18, 2010 (for Airbus Model A300 B4-2C, B4-103, and B4-
203 airplanes).
     Airbus Service Bulletin A300-57-6106, Revision 02, dated 
June 18, 2010 (for Airbus Model A300-600 series airplanes).
     Airbus Mandatory Service Bulletin A310-57-2090, Revision 
02, dated June 18, 2010 (for Airbus Model A310 series 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.

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

[[Page 69170]]

affect about 215 products of U.S. registry. We also estimate that it 
would take about 38 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 $4,590 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 
costs. 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 $1,681,300, or $7,820 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-2011-1225; Directorate Identifier 2010-NM-
269-AD.

Comments Due Date

    (a) We must receive comments by December 23, 2011.

Affected ADs

    (b) This AD affects AD 2007-03-18, Amendment 39-14929 (72 FR 
5919, February 8, 2007); and AD 2008-17-02, Amendment 39-15640 (73 
FR 47032, dated August 13, 2008).

Applicability

    (c) This AD applies to airplanes, certified in any category, as 
specified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD.
    (1) Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; all 
serial numbers; except airplanes where the main landing gear (MLG) 
rib 5 forward lugs of the left hand (LH) and right hand (RH) wing 
have been repaired by installation of oversized interference fit 
bushes per Airbus Repair Instruction R57240221, or those where the 
LH and RH wing have had Airbus Mandatory Service Bulletin A300-57-
0249 embodied in service.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes; Airbus Model A300 B4-605R and B4-622R airplanes; Airbus 
Model A300 F4-605R and F4-622R airplanes; and Airbus Model A300 C4-
605R Variant F airplanes; all serial numbers; except airplanes where 
the MLG rib 5 forward lugs of the LH and RH wing have been repaired 
by installation of oversized interference fit bushes per Airbus 
Repair Instruction R57240221, or those where the LH and RH wing have 
had Airbus Service Bulletin A300-57-6106 embodied in service.
    (3) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes; all serial numbers; except airplanes where the 
MLG rib 5 forward lugs of the LH and RH wing have been repaired by 
installation of oversized interference fit bushes per Airbus Repair 
Instruction R57249121, or those where the LH and RH wing have had 
Airbus Mandatory Service Bulletin A310-57-2090 embodied in service.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    During a routine visual inspection on two A310 in-service 
aeroplanes, cracks were found in the wing MLG rib 5 aft bearing 
forward lug. Laboratory examination of the cracked ribs confirmed 
that the cracks were the result of pitting corrosion in the forward 
lug hole. Also on both aeroplanes, medium to heavy corrosion was 
found in the forward lugs on the opposite wing after removal of the 
bushes. * * *. This situation, if not corrected, could affect the 
structural integrity of the MLG attachment [which could result in 
the collapse of the MLG].
* * * * *

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.

Inspection and Corrective Actions

    (g) Within 30 months after the effective date of this AD, 
install new bushes with increased interference fit in the gear rib 5 
aft bearing forward lug on the RH and LH wing, in accordance with 
the Accomplishment Instructions of the applicable service bulletins 
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD; 
except as specified in paragraph (h) of this AD.
    (1) Airbus Mandatory Service Bulletin A300-57-0249, Revision 02, 
dated June 18, 2010 (for Model A300 B4-2C, B4-103, and B4-203 
airplanes);
    (2) Airbus Service Bulletin A300-57-6106, Revision 02, dated 
June 18, 2010 (for Model A300-600 series airplanes); and
    (3) Airbus Mandatory Service Bulletin A310-57-2090, Revision 02, 
dated June 18, 2010 (for Airbus Model A310 series airplanes).
    (h) If one wing had rib 5 forward lugs of the MLG repaired by 
installing oversized interference fit bushes in accordance with 
Airbus Repair Instruction R57240221 or Airbus Repair Instruction 
R57249121, as applicable to the airplane model, then installing new 
bushes with increased interference fit in the aft bearing forward 
lug of the gear rib, as specified in paragraph (h) of this AD, is 
required for the opposite wing only.

Terminating Action for Inspections Required by AD 2007-03-18, (72 FR 
5919, February 8, 2007); and AD 2008-17-02, (73 FR 47032, Dated August 
13, 2008)

    (i) Installation of new bushes, as specified in paragraph (h) of 
this AD, is terminating action for the repetitive inspections 
required AD 2007-03-18, Amendment 39-14929 (72 FR 5919, February 8, 
2007); and AD 2008-17-02, Amendment 39-15640 (73 FR 47032, dated 
August 13, 2008).

[[Page 69171]]

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (j) Installations accomplished before the effective date of this 
AD, according to the applicable service bulletins specified 
paragraphs (j)(1), (j)(2), and (j)(3) of this AD, are considered 
acceptable for compliance with the corresponding installations 
specified in this AD.
    (1) Airbus Service Bulletin A300-57-0249, dated May 22, 2007; or 
Airbus Service Bulletin A300-57-0249, Revision 01, dated December 
19, 2007 (for Model A300 B4-2C, B4-103, and B4 203 airplanes);
    (2) Airbus Service Bulletin A300-57-6106, May 22, 2007; or 
Airbus Service Bulletin A300-57-6106, Revision 01, January 28, 2008 
(for Model A300-600 series airplanes); and
    (3) Airbus Service Bulletin A310-57-2090, dated May 22, 2007; or 
Airbus Service Bulletin A310-57-2090, Revision 01, dated December 
19, 2007 (for Model A310 series airplanes).

FAA AD Differences

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

Other FAA AD Provisions

    (k) 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, Washington 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 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

    (l) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2010-0251, dated November 29, 2010; Airbus Mandatory 
Service Bulletin A300-57-0249, Revision 02, dated June 18, 2010; 
Airbus Service Bulletin A300-57-6106, Revision 02, dated June 18, 
2010; and Airbus Mandatory Service Bulletin A310-57-2090, Revision 
02, dated June 18, 2010; for related information.

    Issued in Renton, Washington, on October 28, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-28833 Filed 11-7-11; 8:45 am]
BILLING CODE 4910-13-P
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