Document ID: FAA-2012-1164-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2012-11-19T05:00Z

[Federal Register Volume 77, Number 223 (Monday, November 19, 2012)]
[Proposed Rules]
[Pages 69391-69393]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-27999]

 ========================================================================
 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. 223 / Monday, November 19, 2012 / 
Proposed Rules  

[[Page 69391]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1164; Directorate Identifier 2012-NM-075-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 A310-204, -222, -304, -322, and -324 airplanes. 
This proposed AD was prompted by the manufacturer re-classifying slat 
extension eccentric bolts as principle structural elements (PSE) with 
replacement due at or before newly calculated fatigue life limits. This 
proposed AD would require replacing slat extension eccentric bolts, and 
associated washers with new slat extension eccentric bolts and washers. 
We are proposing this AD to prevent fatigue cracking, which could 
result in the loss of structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by January 3, 2013.

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, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the 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-2012-1164; 
Directorate Identifier 2012-NM-075-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 aviation 
authority for the Member States of the European Community, has issued 
EASA Airworthiness Directive 2012-0042, dated April 10, 2012 (referred 
to after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Slat extension eccentric bolts have been reclassified as 
Principal Structural Elements (PSE). As a result, associated fatigue 
lives will be published in the Airbus A310 Airworthiness Limitation 
Section (ALS) Part 1 and bolts must be replaced at or before their 
calculated fatigue lives.
    Failure to replace the bolts within the new fatigue life limits 
constitutes an unsafe condition.
    For the reasons explained above, this [EASA] AD requires:

--For A310-300 aeroplanes, the replacement of slat extension 
eccentric bolts, Part Number (P/N) A57844015200, with slat extension 
eccentric bolts P/N A57844015204 at the slat 2 tracks 4 and 7 and 
slat 3 track 8 positions on both Left Hand (LH) and Right Hand (RH) 
wings, and
--For A310-300 and A310-200 aeroplanes that incorporate Airbus 
modification 04809, the replacement of slat extension eccentric 
bolts, P/N A57843624200 and associated washers P/N A57844016200, 
with slat extension eccentric bolts P/N A57843624202 and washers P/N 
A57844391200 at the slat 2 track 5 position, on both LH and RH 
wings.

The unsafe condition is fatigue cracking, which could result in the 
loss of structural integrity of the airplane. You may obtain further 
information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A310-57-2100, Revision 
01, dated February 3, 2012. 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

[[Page 69392]]

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 1 product of U.S. registry. We also estimate that it 
would take about 9 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 $25,250 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 $26,015, or $26,015 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 adding the following new AD:

Airbus: Docket No. FAA-2012-1164; Directorate Identifier 2012-NM-
075-AD.

(a) Comments Due Date

    We must receive comments by January 3, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A310-204, -222, -304, -322, and 
-324 airplanes, certificated in any category, having received in 
production Airbus modification 04809 without Airbus modification 
06243 or 13596.

(d) Subject

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

(e) Reason

    This AD was prompted by the manufacturer re-classifying slat 
extension eccentric bolts as principle structural elements (PSE) 
with replacement due at or before newly calculated fatigue life 
limits. We are issuing this AD to prevent fatigue cracking, which 
could result in the loss of structural integrity of the airplane.

(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) Compliance Times

    At the applicable time specified in paragraphs (g)(1), (g)(2), 
and (g)(3) of this AD: Do the replacements specified in paragraphs 
(h)(1) and (h)(2) of this AD, as applicable. For the purposes of 
this AD, to establish the average flight time (AFT), take the 
accumulated flight time (counted from the take-off up to the 
landing) and divide it by the number of accumulated flight cycles. 
This gives the AFT per flight cycle.
    (1) For Model A310-304, -322, and -324 airplanes operated with 
an AFT of less than 4 hours: Before the accumulation of 66,000 total 
flight hours or 40,000 total flight cycles, whichever occurs first.
    (2) For Model A310-304, -322, and -324 airplanes operated with 
an AFT of 4 hours or more: Before the accumulation of 66,000 total 
flight hours or 31,400 total flight cycles, whichever occurs first.
    (3) For Model A310-204 and -222 airplanes with Airbus 
modification 04809: Before the accumulation of 71,800 total flight 
hours or 35,900 total flight cycles, whichever occurs first.

(h) Replacement of Slat Extension Eccentric Bolt and Hardware on Both 
Wings

    (1) For Model A310-304, -322, and -324 airplanes: Replace the 
slat extension eccentric bolts, part number (P/N) A57844015200, at 
the slat 2 tracks 4 and 7 and slat 3 track 8 positions with new slat 
extension bolts, P/N A57844015204, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A310-57-2100, Revision 01, dated February 3, 2012.
    (2) For Model A310-304, -322, and -324 airplanes, and Model 
A310-204 and -222 airplanes that have incorporated Airbus 
modification 04809: Replace the slat extension eccentric bolts, P/N 
A57843624200, at the slat 2 track 5 position with new slat extension 
bolts, P/N A57843624202; and replace the associated washers of 
eccentric bolts, P/N A57844016200, at slat 2 track 5 position with 
washers, P/N A57844391200; in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A310-57-2100, 
Revision 01, dated February 3, 2012.

(i) Parts Installation Prohibition

    After the modification of the airplane with the replacement of 
slat extension eccentric bolts and associated hardware required by 
paragraphs (g) and (h) of this AD, no person may install any slat 
extension eccentric bolt, P/N A57844015200 or P/N A57843624200, with 
associated washer P/N A57844016200, on that airplane.

(j) Other FAA AD Provisions

    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

[[Page 69393]]

appropriate. If sending information directly to the International 
Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-
2125; fax (425) 227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your 
appropriate principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must 
specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer 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.

(k) Related Information

    (1) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2012-0042, dated April 10, 2012; and Airbus Mandatory 
Service Bulletin A310-57-2100, Revision 01, dated February 3, 2012; 
for related information.
    (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 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, WA. For information on 
the availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on November 9, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-27999 Filed 11-16-12; 8:45 am]
BILLING CODE 4910-13-P