[Federal Register Volume 76, Number 84 (Monday, May 2, 2011)]
[Rules and Regulations]
[Pages 24351-24353]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-9921]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0383; Directorate Identifier 2010-NM-093-AD;
Amendment 39-16675; AD 2011-09-13]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A340-200 and -300 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
Further to accomplishment of A340 ALI tasks 545104, which
require a rototest inspection as per Non Destructive Testing Manual
(NTM) 54-51-04 of engine pylon pyramid attachment areas at aft end
of lower arms between Rib 1 and Rib 2 (2 fastener locations/pylon),
four findings have been reported and repaired.
* * * * *
The unsafe condition is cracking, which might impact the structural
integrity of the airplane. This AD requires actions that are intended
to address the unsafe condition described in the MCAI.
DATES: This AD becomes effective May 17, 2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of May 17, 2011.
We must receive comments on this AD by June 16, 2011.
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 W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
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 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: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone: 425-
227-1138; fax: 425-227-1149.
SUPPLEMENTARY INFORMATION:
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 2008-0140, dated July 28, 2008 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
Further to accomplishment of A340 ALI tasks 545104, which
require a rototest inspection as per Non Destructive Testing Manual
(NTM) 54-51-04 of engine pylon pyramid attachment areas at aft end
of lower arms between Rib 1 and Rib 2 (2 fastener locations/pylon),
four findings have been reported and repaired.
Further investigations made on performances of High Frequency
Eddy Current (HFEC) inspection techniques in steel led to the
conclusion that existing NTM procedure 54-51-04 by rototest is not
reliable because this method is not adapted to the ferromagnetic
materials and therefore findings reported up to now using this
procedure can be considered as uncertain.
Therefore, a new inspection procedure using Ultra Sonic (US)
testing without fastener removal has been developed.
In order to comply with certification requirements, this
Airworthiness Directive (AD) requires performing the new
[repetitive] US inspection [for cracking] on all A340-200/-300 pre-
modification 49203 (reinforcements of pylon primary structure for
enhanced A340).
[[Page 24352]]
The unsafe condition is cracking, which might impact the structural
integrity of the airplane. The required actions include repairing any
cracks found. You may obtain further information by examining the MCAI
in the AD docket.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A340-54-4010,
including Appendices 1, 2, and 3, dated July 21, 2008. 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 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 issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
There are no products of this type currently registered in the
United States. However, this rule is necessary to ensure that the
described unsafe condition is addressed if any of these products are
placed on the U.S. Register in the future.
Differences Between the AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a note within the AD.
FAA's Determination of the Effective Date
Since there are currently no domestic operators of this product,
notice and opportunity for public comment before issuing this AD are
unnecessary.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2011-0383; Directorate
Identifier 2010-NM-093-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
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 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 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); and
3. 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.
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:
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:
2011-09-13 Airbus: Amendment 39-16675. Docket No. FAA-2011-0383;
Directorate Identifier 2010-NM-093-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 17,
2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A340-211, -212, -213, -311,
-312, and -313 airplanes; certificated in any category; all serial
numbers except those on which Airbus Modification 49203 has been
incorporated in production.
Subject
(d) Air Transport Association (ATA) of America Code 54:
Nacelles/Pylons.
Reason
(e) The mandatory continued airworthiness information (MCAI)
states:
Further to accomplishment of A340 ALI tasks 545104, which
require a rototest inspection as per Non Destructive Testing Manual
(NTM) 54-51-04 of engine pylon pyramid attachment areas at aft end
of lower arms between Rib 1 and Rib 2 (2 fastener locations/pylon),
four findings have been reported and repaired.
* * * * *
The unsafe condition is cracking, which might impact the structural
integrity of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
[[Page 24353]]
Ultrasonic Inspection
(g) At the later of the compliance times specified in paragraphs
(g)(1) and (g)(2) of this AD, except as provided by paragraph (h) of
this AD: Perform an ultrasonic inspection of pylon pyramid
attachment areas at the aft end of the lower arms between Rib 1 and
Rib 2 without fastener removal (2 fastener locations per pylon), in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A340-54-4010, dated July 21, 2008.
(1) Before the accumulation of the applicable total flight
cycles or total flight hours, whichever occurs first, specified in
table 1 of this AD.
(2) Within 90 days after the effective date of this AD.
Table 1--Initial Inspection Compliance Times
------------------------------------------------------------------------
Total Total
Weight variant flight flight
cycles hours
------------------------------------------------------------------------
000 through 004............................... 13,000 60,000
020, 021, 023 through 026, 028 through 030, 11,470 77,400
Pre 49203....................................
027........................................... 11,000 30,000
------------------------------------------------------------------------
(h) For airplanes belonging to weight variant 000 through 004
inspected before the effective date of this AD in accordance with
Airworthiness Limitations Items (ALI) Task 545104-01-01, as
described in Airbus A340 Airworthiness Limitations Items Document
Ref: AI/SE-M4/95A.0051/97, Issue 10, dated February 1, 2007: Perform
the inspection required in paragraph (g) of this AD at the
compliance times specified in paragraphs (h)(1) and (h)(2) of this
AD, whichever occurs later.
(1) Within 90 days after the effective date of this AD.
(2) Within 2,680 flight cycles or 19,200 flight hours, whichever
occurs first, after the most recent rototest inspection done in
accordance with ALI task 545104-01-01, but not to exceed the
accumulation of 15,280 total flight cycles or 76,400 total flight
hours, whichever occurs first.
(i) If no cracking is detected during any inspection required by
paragraph (g) of this AD: Repeat the inspection required in
paragraph (g) of this AD thereafter at intervals not to exceed the
earlier of the applicable flight cycles or flight hours interval
specified in table 2 of this AD.
Table 2--Repetitive Inspection Interval
------------------------------------------------------------------------
Flight Flight
Weight variant cycles hours
------------------------------------------------------------------------
000 through 004............................... 1,900 9,500
020, 021, 023 through 026, 028 through 030, 1,700 8,500
Pre 49203....................................
027........................................... 1,700 8,500
------------------------------------------------------------------------
(j) If any crack is detected during any inspection required by
this AD: Before further flight, repair the cracking using 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).
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(k) 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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone: 425-227-1138; fax: 425-227-1149.
Information may be e-mailed 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) Special Flight Permits: Special flight permits, as described
in Section 21.197 and Section 21.199 of the Federal Aviation
Regulations (14 CFR 21.197 and 21.199), are not allowed if any crack
is detected during any inspection required by this AD.
Related Information
(l) Refer to MCAI EASA Airworthiness Directive 2008-0140, dated
July 28, 2008; and Airbus Mandatory Service Bulletin A340-54-4010,
dated July 21, 2008; for related information.
Material Incorporated by Reference
(m) You must use Airbus Mandatory Service Bulletin A340-54-4010,
including Appendices 1, 2, and 3, dated July 21, 2008, to do the
actions required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96;
fax: +33 5 61 93 45 80; e-mail: [email protected];
Internet: http://www.airbus.com.
(3) You may review copies of the 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.
(4) You may also review copies of the 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/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on April 15, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-9921 Filed 4-29-11; 8:45 am]
BILLING CODE 4910-13-P