[Federal Register Volume 77, Number 85 (Wednesday, May 2, 2012)]
[Proposed Rules]
[Pages 25930-25932]
[FR Doc No: 2012-10573]

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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.

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Federal Register / Vol. 77, No. 85 / Wednesday, May 2, 2012 /
Proposed Rules

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).

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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:<PHONE_NUMBER>.
     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<EMAIL_ADDRESS>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<PHONE_NUMBER>.

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<PHONE_NUMBER>) 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<PHONE_NUMBER>.

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.

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

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<PHONE_NUMBER>; fax<PHONE_NUMBER>.
Information may be emailed to<EMAIL_ADDRESS>
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