Airworthiness Directives; Airbus Airplanes
Federal Register, Volume 77 Issue 223 (Monday, November 19, 2012)
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
Page 69391
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
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
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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:
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Is not a ``significant regulatory action'' under Executive Order 12866;
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Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
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Will not affect intrastate aviation in Alaska; and
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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
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The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 Amended
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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
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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
