Daily Rules, Proposed Rules, and Notices of the Federal Government
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
You may examine the AD docket on the Internet at
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
We will post all comments we receive, without change, to
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:
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.
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
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.
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.
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.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
1. The authority citation for part 39 continues to read as follows:
49 U.S.C. 106(g), 40113, 44701.
2. The FAA amends § 39.13 by adding the following new AD:
We must receive comments by January 3, 2013.
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.
Air Transport Association (ATA) of America Code 57, Wings.
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.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
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.
(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.
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.
The following provisions also apply to this AD:
(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