[Federal Register Volume 77, Number 193 (Thursday, October 4, 2012)]
[Proposed Rules]
[Pages 60655-60658]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-24404]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1038; Directorate Identifier 2011-NM-166-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 supersede an existing airworthiness directive
(AD) that applies to certain Airbus Model A319 and A320 airplanes. The
existing AD currently requires repetitive detailed inspections to
detect cracks in the keel beam side panels, and repair if
[[Page 60656]]
necessary. Since we issued that AD, we have received reports of access
difficulties. Additionally, we have determined that the detailed
inspection is not sufficient to mitigate the unsafe condition. This
proposed AD would require repetitive eddy current inspections for
cracking in the keel beam side panels, and corrective actions if
necessary. We are proposing this AD to detect and correct fatigue
cracks on the side panels of the keel beams, which could result in
reduced 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, 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; 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, WA 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-2012-1038;
Directorate Identifier 2011-NM-166-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
On June 16, 2004, we issued AD 2004-13-06, Amendment 39-13688 (69
FR 38818, June 29, 2004). That AD required actions intended to address
an unsafe condition on the products listed above.
Since we issued AD 2004-13-06, Amendment 39-13688 (69 FR 38818,
June 29, 2004), we have determined that the detailed inspection
required by AD 2004-13-06 is not sufficient to mitigate the unsafe
condition. The European Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Community, has
issued EASA Airworthiness Directive 2011-0134, dated July 15, 2011
(referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
During certification structural fatigue tests, several cases of
structural damage (cracks) have been found on keel beam side panels.
Cracks were observed on both sides of the keel beam around the
rivets below the center wing box between frame (FR) 40 and FR 42,
and in part of the area of the upper elliptical cut out forward of
FR 41.
This type of damage, if not detected and repaired, would
adversely affect the structural integrity of the aeroplane.
To address this unsafe condition, DGAC [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 2003-
146 [which corresponds to FAA AD 2004-13-06, Amendment 39-13688 (69
FR 38818, June 29, 2004)] to require repetitive detailed inspections
of those two areas and corrective actions, depending on findings.
Prompted by reported access difficulties and to allow extension
of the interval between two consecutive inspections, Airbus
validated an Eddy current Non-Destructive Test (NDT) inspection to
replace the detailed inspection.
For the reasons described above, this [EASA] AD, which
supersedes DGAC France AD 2003-146, requires repetitive Eddy-current
NDT inspections for cracks in the affected areas of the keel beam
side panel below the center wing box and corrective actions
[repair], depending on findings.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A320-53-1060, Revision
02, dated November 30, 2010. 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.
Differences Between This AD and the MCAI or Service Information
Although the MCAI and Airbus Mandatory Service Bulletin A320-53-
1060, Revision 02, dated November 30, 2010, allow further flight after
cracks are found during compliance with the proposed actions, this
proposed AD would require repair before further flight if cracks are
detected in the keel beam side panels. We have determined that, because
of the safety implications and consequences associated with that
cracking, any cracking in the keel beam side panels must be repaired
before further flight.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 351 products of U.S. registry.
We estimate that it would take about 29 work-hours per product to
comply with the new 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 $865,215, or $2,465
per product.
[[Page 60657]]
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD. We have no way of determining the number of products that may need
these actions.
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 removing airworthiness directive
(AD) 2004-13-06, Amendment 39-13688 (69 FR 38818, June 29, 2004), and
adding the following new AD:
Airbus: Docket No. FAA-2012-1038; Directorate Identifier 2011-NM-
166-AD.
(a) Comments Due Date
We must receive comments by November 19, 2012.
(b) Affected ADs
This AD supersedes AD 2004-13-06, Amendment 39-13688 (69 FR
38818, June 29, 2004).
(c) Applicability
This AD applies to Airbus Model A319-111, -112, -113, -114, -
115, -131, -132, and -133 airplanes; and Model A320-111, -211, -212,
-214, -231, -232, and -233 airplanes; certificated in any category;
all manufacturer serial numbers, except those having embodied Airbus
modification 30355 in production.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks on the side panels of
the keel beams. We are issuing this AD to detect and correct fatigue
cracks on the side panels of the keel beams, which could result in
reduced 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) Repetitive Eddy Current Inspection
At the applicable compliance time in paragraph (k)(1) or (k)(2)
of this AD: Do an eddy current non-destructive test (NDT) inspection
to detect cracks in the keel beam side panels at Area A and Area B,
in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320-53-1060, Revision 02, dated November
30, 2010. Repeat the inspection thereafter at intervals not to
exceed 12,000 flight cycles or 26,700 flight hours, whichever occurs
first. Area A is part of the area of the upper elliptical cut-out
stringer (STGR) 42 on the left-hand (LH) and right-hand (RH) side
forward of Frame (FR) 41, and Area B is the area around the rivets
on both sides of the keel beam side panel below the center wing box
at STGR 42 on the LH and RH side between FR 40 and FR 42.
(1) For airplanes that have been inspected as specified in
Airworthiness Limitations Item (ALI) Task 533142-01-1, which was
specified in the Airbus A319/A320/A321 ALI document up to Revision
05 inclusive; or as specified in Airbus A319/A320/A321 Maintenance
Review Board (MRB) Report up to Revision 08 inclusive; or as
specified in the instructions of Airbus Service Bulletin A320-53-
1060, dated June 19, 2002, or Revision 01, dated April 2, 2004: At
the later of the times specified in paragraphs (g)(1)(i) and
(g)(1)(ii) of this AD.
(i) Within 4,300 flight cycles or 9,600 flight hours after the
last inspection, whichever occurs first.
(ii) Within 30 days after the effective date of this AD.
(2) For airplanes other than those identified in paragraph
(g)(1) of this AD: At the later of the times specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD.
(i) Prior to the accumulation of 24,200 total flight cycles, or
48,400 total flight hours, whichever occurs first.
(ii) Within 30 days after the effective date of this AD.
(h) Corrective Action for Cracking
(1) If any crack is found in Area A during any inspection
required by paragraph (g) of this AD: Before further flight, repair
the affected area, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A320-53-1060,
Revision 02, dated November 30, 2010. Accomplishing a repair
terminates the repetitive inspections of Area A required by
paragraph (g) of this AD for that side of the keel beam.
(2) If any crack is found in Area B during any inspection
required by this AD: Before further flight, repair the affected area
in accordance with a method approved by either the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the European Aviation Safety Agency (EASA) (or its delegated
agent).
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, 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; 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
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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.
(j) Special Flight Permits
Special flight permits may be issued in accordance with sections
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199) to operate the airplane to a location where the airplane
can be repaired (if the operator elects to do so), provided the
conditions in paragraph (n)(1), (n)(2), or (n)(3) of this AD are
met. Areas A and B are defined in Airbus Mandatory Service Bulletin
A320-53-1060, Revision 02, dated November 30, 2010.
(1) No multiple cracks in Area A.
(2) If there is a single crack in Area A, the length must be
less than 20.0 millimeters (0.79 inch).
(3) No cracking in Area B.
(k) Related Information
(1) Refer to MCAI EASA Airworthiness Directive 2011-0134, dated
July 15, 2011; and Airbus Mandatory Service Bulletin A320-53-1060,
Revision 02, dated November 30, 2010; 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, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on September 26, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-24404 Filed 10-3-12; 8:45 am]
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