[Federal Register Volume 79, Number 27 (Monday, February 10, 2014)]
[Proposed Rules]
[Pages 7596-7598]
[FR Doc No: 2014-02718]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0004; Directorate Identifier 2013-NM-143-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 A320-111, -211, -212, and -231 airplanes. This
proposed AD was prompted by reports of broken struts of the center wing
box (CWB). This proposed AD would require a detailed inspection of the
CWB struts for cracking, and repair if necessary. We are proposing this
AD to detect and correct cracked or broken struts, which could result
in strut failure and consequent reduced structural integrity of the
airplane.

DATES: We must receive comments on this proposed AD by March 27, 2014.

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, Airworthiness Office--EAS, 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 view this 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 by searching for and locating Docket No. FAA-2014-
0004; or in person at the Docket Management Facility 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: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone:<PHONE_NUMBER>; 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-2014-0004;
Directorate Identifier 2013-NM-143-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 2013-0149, dated July 16, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:

    Two cases of broken Centre Wing Box (CWB) struts have been
reported on A320 aeroplanes. Investigation results indicated that
strut thickness in the crack initiation area was lower than
specified in the production drawings. Only a limited batch of
aeroplanes is affected by this manufacturing defect.
    This condition, if not corrected, could result in strut failure,
reducing the residual life of the remaining struts to below the
initial Design Service Goal, which would deteriorate the structural
integrity of the aeroplane.
    For the reasons described above, this [EASA] AD requires
repetitive Detailed Visual inspections (DVI) of the lower and upper
ends of the CWB struts to detect cracks and, depending on findings,
accomplishment of associated corrective actions [repair].

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-
2014-0004.

Relevant Service Information

    Airbus has Service Bulletin A320-57-1149, Revision 01, dated
February 12, 2013. 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.
    In many FAA transport ADs, when the service information specifies
to contact the manufacturer for further instructions if certain
discrepancies are found, we typically include in the AD a requirement
to accomplish the action using a method approved by either the FAA or
the State of Design Authority (or its delegated agent).
    We have recently been notified that certain laws in other countries
do not allow such delegation of authority, but some countries do
recognize design approval organizations. In addition, we have become
aware that some U.S. operators have used repair instructions that were
previously approved by a State of Design Authority or a Design Approval
Holder (DAH) as a method of compliance with this provision in FAA ADs.
Frequently, in these cases, the previously approved repair instructions
come from the airplane structural repair manual or the DAH repair
approval statements that were not specifically developed to address the
unsafe condition corrected by the AD. Using repair instructions that
were not specifically approved for a particular AD creates the
potential for doing repairs that were not developed to address the
unsafe condition identified by the MCAI AD, the FAA AD, or the
applicable service information, which could result in the unsafe
condition not being fully corrected.
    To prevent the use of repairs that were not specifically developed
to correct the unsafe condition, this proposed AD would require that
the repair approval specifically refer to the FAA AD. This change is
intended to clarify the method of compliance and to provide operators
with better visibility of repairs that are specifically developed and
approved to correct the unsafe condition. In addition, we use the
phrase ``its delegated agent, or the DAH with State of Design Authority
design organization approval, as applicable'' in this proposed AD to
refer to a DAH authorized to approve required repairs for this proposed
AD.

Costs of Compliance

    We estimate that this proposed AD affects 16 airplanes of U.S.
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
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                                                                              Cost per          Cost on U.S.
              Action                      Labor cost         Parts cost        product           operators
----------------------------------------------------------------------------------------------------------------
Inspection........................  12 work-hours x $85                $0          $1,020  $16,320 per
                                     per hour = $1,020                                      inspection cycle.
                                     per inspection cycle.
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    We have received no definitive data that would enable us to provide
cost estimates for the on-condition action specified in this proposed
AD.

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.

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

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness
directive (AD):

Airbus: Docket No. FAA-2014-0004; Directorate Identifier 2013-NM-
143-AD.

(a) Comments Due Date

    We must receive comments by March 27, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A320-211, -212, and -231
airplanes, certificated in any category, all manufacturer serial
numbers up to 0136 inclusive.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of broken struts of the center
wing box (CWB) on certain airplanes. We are issuing this AD to
detect and correct cracked or broken struts, which could result in
struts, which could result in strut failure and consequent reduced
structural integrity of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done.

(g) Repetitive Inspections

    At the applicable time specified in paragraph (g)(1) or (g)(2)
of this AD: Do a detailed inspection of each strut of the CWB for
cracking, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-57-1149, Revision 01, dated February
12, 2013. Repeat the inspection thereafter at intervals not to
exceed 16,800 flight cycles or 33,600 flight hours, whichever occurs
first.
    (1) For airplanes on which the inspection required by paragraph
(g) of this AD has not been done as of the effective date of this
AD: Do the inspection at the later of the times specified in
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
    (i) Before the accumulation of 31,700 total flight cycles or
63,400 total flight hours since first flight, whichever occurs
first.
    (ii) Within 1,250 flight cycles or 2,500 flight hours after the
effective date of this AD, whichever occurs first.
    (2) For airplanes on which the inspection required by paragraph
(g) of this AD has been done as of the effective date of this AD: Do
the inspection within 16,800 flight cycles or 33,600 flight hours
after the most recent inspection, whichever occurs first.

(h) Repair

    If any crack is found during any inspection required by
paragraph (g) of this AD: Before further flight, repair using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; the EASA (or its delegated
agent, or the Design Approval Holder with EASA's design organization
approval). For a repair method to be approved, the repair approval
must specifically refer to this AD.

(i) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph
(g) of this AD, if those actions were performed before the effective
date of this AD using Airbus Service Bulletin A320-57-1149, dated
April 1, 2008.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, 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: Sanjay Ralhan, Aerospace Engineer, International Branch,
ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone:<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, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or the DAH with a State of Design Authority's
design organization approval). You are required to ensure the
product is airworthy before it is returned to service.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0149, dated July 16, 2013,
for related information. This MCAI may be found in the AD docket on
the Internet at http://www.regulations.gov by searching for and
locating it in Docket No. FAA-2014-0004.
    (2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EAS, 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.
    (3) You may view copies of this 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<PHONE_NUMBER>.

    Issued in Renton, Washington, on January 18, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-02718 Filed 2-7-14; 8:45 am]
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