[Federal Register Volume 78, Number 132 (Wednesday, July 10, 2013)]
[Rules and Regulations]
[Pages 41280-41282]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-15153]
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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;
Amendment 39-17491; AD 2013-13-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting 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 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 series airplane. This AD requires 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 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.
DATES: This AD becomes effective August 14, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 14,
2013.
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That
[[Page 41281]]
NPRM was published in the Federal Register on October 4, 2012 (77 FR
60658). 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 Mandatory Continuing Airworthiness
Information, or ``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 necessary. You may obtain further
information by examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
Request To Revise HFEC Inspection Requirement
Airbus requested that the one-time HFEC inspection in paragraph (g)
of the NPRM (77 FR 60658, October 4, 2012) be revised in anticipation
of further rulemaking by the EASA, which would mandate the
airworthiness limitation inspection task and would correspond with the
one-time HFEC inspection.
We disagree with Airbus's request. We have determined that
publishing this final rule without any further delay is in the interest
of safety of the flying public. However, we will consider additional AD
rulemaking, if appropriate, in the future. We have not revised this
final rule in this regard.
Request for Approval of Repair
Airbus requested consideration that each Airbus Repair Approval
Sheet (RAS) be approved under ``AIRBUS DOA EASA.21J.031,'' provided
that this is done after cracking is reported. Airbus stated that this
would be an approved method for repair as required by paragraph (g) of
the NPRM (77 FR 60658, October 4, 2012).
We agree. Airbus is an EASA-delegated agent; therefore, a RAS
approved under Airbus Design Organization Approval (DOA) EASA.21J.031
would be a method of compliance for a repair required by this AD. We
have not changed the final rule in this regard.
Request To Update Address for the Manufacturer
Airbus requested that the address for the manufacturer be updated.
Airbus stated that in paragraph (k)(2) of the NPRM (77 FR 60658,
October 4, 2012), ``EAS'' should be replaced with ``EIAS.''
We agree with Airbus's request to update the manufacturer's
address. Paragraphs (k)(2) and (l)(3) of this final rule have been
updated accordingly.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD with the change described previously--and minor editorial
changes. We have determined that these changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 60658, October 4, 2012) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 60658, October 4, 2012).
Costs of Compliance
We estimate that this AD will affect 105 products of U.S. registry.
We also estimate that it will take about 20 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD to the 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 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 AD will not have federalism implications
under Executive Order 13132. This AD will 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 that this AD:
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 AD and placed it in the AD docket.
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 the NPRM (77 FR 60658, October 4,
2012), 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
[[Page 41282]]
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 AD:
2013-13-03 Airbus: Amendment 39-17491. Docket No. FAA-2012-1039;
Directorate Identifier 2011-NM-275-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective August 14,
2013.
(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 series 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 further 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, 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, 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: 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, for related information. The MCAI may be viewed on
the Internet at http://ad.easa.europa.eu/blob/easa_ad_2011_0231.pdf.
(2) Service information identified in this AD that is not
incorporated by reference in this AD may be obtained at the
addresses specified in paragraphs (l)(3) and (l)(4) of this AD.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Service Bulletin A320-53-1245, Revision 01, including
Appendix 1, dated May 17, 2011.
(ii) Reserved.
(3) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 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.
(4) You may review copies of the 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on June 14, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-15153 Filed 7-9-13; 8:45 am]
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