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[Federal Register Volume 77, Number 85 (Wednesday, May 2, 2012)]
[Proposed Rules]
[Pages 25930-25932]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-10573]

========================================================================
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. 85 / Wednesday, May 2, 2012 / 
Proposed Rules

[[Page 25930]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0414; Directorate Identifier 2011-NM-210-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A310-203, -221, and -222 airplanes. This proposed 
AD was prompted by the manufacturer re-classifying slat extension 
eccentric bolts as principal structural elements (PSE) with replacement 
due at or before their calculated fatigue lives. This proposed AD would 
require replacing certain slat extension eccentric bolts with new 
bolts. 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 June 18, 2012.

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-2012-0414; 
Directorate Identifier 2011-NM-210-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 2011-0187, dated September 27, 2011 (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 re-classified as 
Principal Structural Elements (PSE). As a result, associated fatigue 
lives will be published in the Airbus A310 Airworthiness Limitations 
Section (ALS) Part 1 and bolts must be replaced at or before their 
calculated fatigue lives.
    The slat extension eccentric bolt Part Number (P/N) 
A5786451220800 installed at slat 2, track 6 of the left hand (LH) 
and right hand (RH) wings is manufactured by SONACA, but some bolts 
with the same P/N, manufactured by FOKKER, may have been installed 
on A310-200 series aeroplanes and are identical in appearance. The 
calculated fatigue life of the FOKKER bolt is lower than that of the 
SONACA equivalent bolt.
    The difference between the FOKKER and SONACA bolt cannot be 
distinguished by a visual inspection. To remedy this, the SONACA 
bolt part number was changed from P/N A5786451220800 to P/N 
A5784307920000.
    Failure to replace the bolts within the new fatigue life limits 
constitutes an unsafe condition.
    For the reasons described above, this [EASA] AD requires the 
replacement of all slat extension eccentric bolts, P/N 
A5786451220800, with slat extension eccentric bolts P/N 
A5784307920000 at the slat 2 tracks 4, 6 and 7 positions, as well as 
at the slat 3 track 8 position, on both LH and RH wings.
    In addition, it is required to replace the slat extension 
eccentric bolt P/N A57843624200 at slat 2 track 5 with a bolt P/N 
A57843624202.

Required actions also include a concurrent inspection of the removed 
bolts for cracking. If cracking is found, certain bolts at slat 2 track 
5 are replaced with new bolts before further flight. If cracking is not 
found, certain bolts at slat 2 track 5 are replaced with new bolts at 
35,900 total flight cycles or 71,800 total flight hours, whichever 
occurs first. 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.

[[Page 25931]]

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A310-57-2043, Revision 
05, dated September 29, 2010; Mandatory Service Bulletin A310-57-2098, 
dated July 22, 2011; and Mandatory Service Bulletin A310-57-2099, dated 
July 22, 2011. 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.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 48 products of U.S. registry. We also estimate that 
it would take about 12 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 $35,365 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 $1,746,480, or $36,385 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-2012-0414; Directorate Identifier 2011-NM-
210-AD.

(a) Comments Due Date

    We must receive comments by June 18, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A310-203, -221, and -222 
airplanes; certificated in any category; all manufacturer serial 
numbers (MSN), except airplanes having MSN 0415, 0419, 0424, 0427, 
0430, 0454, 0468, 0486, and 0487.

(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 principal structural elements (PSE) 
with replacement due at or before their calculated fatigue lives. 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) Bolt Replacement at Slat 2 Track 6 and Visual Inspection

    (1) At the later of the times specified in paragraphs (g)(1)(i) 
and (g)(1)(ii) of this AD: Replace the slat extension eccentric 
bolts having part number (P/N) A5786451220800 at slat 2 track 6 on 
both wings with bolts having P/N A5784307920000, in accordance with 
the Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A310-57-2043, Revision 05, September 29, 2010.
    (i) Before the accumulation of 14,000 total flight cycles or 
19,000 total flight hours, whichever occurs first.
    (ii) Within 6 months after the effective date of this AD.
    (2) Concurrently with the actions specified in paragraph (g)(1) 
of this AD: Do a general visual inspection of the removed slat 
extension eccentric bolts having P/N A5786451220800 to detect 
cracking, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A310-57-2043, Revision 05, 
September 29, 2010.
    (i) If any cracking is found during the inspection required by 
paragraph (g)(2) of this AD: Before further flight, replace the slat 
extension eccentric bolt having P/N A57843624200 at slat 2 track 5, 
on the right or left wing as applicable, with a bolt having P/N 
A57843624202, in accordance with Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A310-57-2099, dated July 22, 2011.
    (ii) If no cracking is found during the inspection required by 
paragraph (g)(2) of this AD: Before the accumulation of 35,900 total 
flight cycles or 71,800 total flight hours, whichever occurs first, 
replace the slat extension eccentric bolt having P/N A57843624200 at 
slat 2 track 5, on the right or left wing as applicable, with a bolt 
having P/N A57843624202, in accordance with Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A310-57-2099, 
dated July 22, 2011.

(h) Bolt Replacement at Slat 2 Track 4 and Track 7, and Slat 3 Track 8

    Within 30 months after the effective date of this AD: Replace 
the slat extension

[[Page 25932]]

eccentric bolts having P/N A5786451220800 at slat 2 track 4 and 
track 7, and slat 3 track 8, on both wings, with bolts having P/N 
A5784307920000, in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A310-57-2098, dated July 22, 
2011.

(i) Parts Installation

    After modification of an airplane as required by this AD, do not 
install any slat extension eccentric bolt having P/N A5786451220800 
on any 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 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.

(k) Related Information

    Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2011-0187, dated September 27, 2011, and the following 
service information, for related information.
    (1) Airbus Mandatory Service Bulletin A310-57-2043, Revision 05, 
dated September 29, 2010.
    (2) Airbus Mandatory Service Bulletin A310-57-2098, dated July 
22, 2011.
    (3) Airbus Mandatory Service Bulletin A310-57-2099, dated July 
22, 2011.

    Issued in Renton, Washington, on April 25, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-10573 Filed 5-1-12; 8:45 am]
BILLING CODE 4910-13-P
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