[Federal Register Volume 77, Number 193 (Thursday, October 4, 2012)]
[Proposed Rules]
[Pages 60658-60660]
From the Federal Register Online via the Government Publishing 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 [email protected]; 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 [email protected];
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: [email protected]. 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 [email protected]; 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]
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