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[Federal Register Volume 77, Number 193 (Thursday, October 4, 2012)]
[Proposed Rules]
[Pages 60658-60660]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-24472]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1039; Directorate Identifier 2011-NM-275-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 A319-112, -113, and -132 airplanes; Model A320-
211, -212, -214, -231, and -232 airplanes; and Model A321-111 and -131 
airplanes. This proposed AD was prompted by a report of two fatigue 
cracks on the left-hand and right-hand sides of the continuity fittings 
at the front windshield lower framing on a Model A319 airplane. This 
proposed AD would require a high frequency eddy current (HFEC) 
inspection for any cracking on the left-hand and right-hand sides of 
the windshield central lower node continuity fittings, and repair if 
necessary. We are proposing this AD to detect and correct cracking of 
the windshield central lower node continuity fittings, which could 
reduce the structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by November 19, 
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, 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 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1405; 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-2012-1039; 
Directorate Identifier 2011-NM-275-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 2011-0231, dated December 9, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    One operator reported finding two fatigue cracks on continuity 
fittings at left-hand (LH) and right-hand (RH) sides at the front 
windshield lower framing on an A319 aeroplane on which Airbus 
modification (mod.) 22058 had been embodied in production. Airbus 
mod. 22058 (which is included in Airbus mod. 21999) was introduced 
to improve the fatigue strength of the windshield front framing by 
increasing the thickness of framing flanges adjacent to the 
concerned fittings.
    Further analyses have demonstrated that the damage tolerance and 
fatigue requirements of JAR 25.571 (b) are not met on aeroplanes in 
post-mod. 22058 configuration.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the affected aeroplanes.

Required actions include an HFEC inspection for any cracking on the 
left-hand and right-hand sides of the windshield central lower node 
continuity fittings, and repair if

[[Page 60659]]

necessary. You may obtain further information by examining the MCAI in 
the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletin A320-53-1245, Revision 01, 
including Appendix 1, dated May 17, 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 105 products of U.S. registry. We also estimate that 
it would take about 20 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $178,500, or $1,700 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions 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.
    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-2012-1039; Directorate Identifier 2011-NM-
275-AD.

(a) Comments Due Date

    We must receive comments by November 19, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A319-112, -113, and -132 
airplanes; Model A320-211, -212, -214, -231, and -232 airplanes; and 
Model A321-111 and -131 airplanes; certificated in any category; 
manufacturer serial numbers 0259, 0260, 0264, 0266 through 0270 
inclusive, 0275, 0276, 0278, 0287, 0296, 0300, 0303, 0312, 0320, 
0321, 0323, 0325, 0328, 0332, 0334, 0335, 0337, 0346, 0352, 0353, 
0356, 0365, 0369, 0375, 0377, 0382, 0383, 0396, 0398, 0401, 0412, 
0413, 0416, 0419, 0421, 0431, 0432, 0438, 0440, 0441, 0445, 0453, 
0458, 0459, 0466, 0468, 0473, 0474, 0482, 0484, 0491, 0493, 0497, 
0498, 0501, 0502, 0505, 0507, 0509, 0518, 0520, 0521, 0529, 0531, 
0534, 0537, 0538, 0544, 0549, 0554, 0555, 0560, 0563, 0577, 0578, 
0585, 0598, 0600, 0608, 0612, 0618, 0621, 0625, 0637, 0660, 0685, 
0976, 1010, 1092, 1096, 1103, 1139, 1143, 1158, 1251, 1356, and 
1511.

(d) Subject

    Air Transport Association (ATA) of America Code 53, fuselage.

(e) Reason

    This AD was prompted by a report of two fatigue cracks on the 
left-hand and right-hand sides of the continuity fittings at the 
front windshield lower framing on a Model A319 airplane. We are 
issuing this AD to detect and correct cracking of the windshield 
central lower node continuity fittings, which could reduce the 
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) Inspection and Corrective Action

    Before the accumulation of 34,000 total flight cycles since the 
airplane's first flight, or within 4,500 flight cycles after the 
effective date of this AD, whichever occurs later: Perform a high 
frequency eddy current (HFEC) inspection for any cracking on the 
left-hand and right-hand sides of the windshield central lower node 
continuity fittings, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1245, Revision 01, 
including Appendix 1, dated May 17, 2011. If any cracking is found, 
before next flight, repair using a method approved by the Manager, 
International Branch, ANM-116, FAA, or the European Aviation Safety 
Agency (EASA) (or its delegated agent).

(h) Reporting Requirement

    Submit a report of the findings (both positive and negative) of 
the inspection required by paragraph (g) of this AD to Airbus, 
Customer Service Directorate, Attn: SDC32 Technical Data and 
Documentation Services, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; fax +33 5 61 93 28 06; email sb.reporting@airbus.com; 
at the applicable time specified in paragraph (h)(1) or (h)(2) of 
this AD.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(i) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD,

[[Page 60660]]

if those actions were performed before the effective date of this AD 
using Airbus Service Bulletin A320-53-1245, including Appendix 1, 
dated March 2, 2011, which is not incorporated by reference in this 
AD.

(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, 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, Washington 98057-3356; telephone (425) 
227-1405; 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.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(k) Related Information

    (1) Refer to MCAI EASA Airworthiness Directive 2011-0231, dated 
December 9, 2011; and Airbus Service Bulletin A320-53-1245, Revision 
01, including Appendix 1, dated May 17, 2011; for related 
information.
    (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 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.

    Issued in Renton, Washington, on September 27, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-24472 Filed 10-3-12; 8:45 am]
BILLING CODE 4910-13-P
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