[Federal Register Volume 77, Number 122 (Monday, June 25, 2012)]
[Proposed Rules]
[Pages 37829-37831]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-15461]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0671; Directorate Identifier 2011-NM-096-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 A330-243, -341, -342 and -343
airplanes. The existing AD currently requires modifying certain cowl
assemblies of the left- and right-hand thrust reversers. Since we
issued that AD, the manufacturer has issued new life limits on certain
thrust reverser C-duct assemblies. This proposed AD would require
removing certain C-duct assemblies of the left- and right-hand thrust
reversers from service at certain designated life limits, and would
also add airplanes to the applicability. We are proposing this AD to
prevent fatigue cracking of the hinges integrated into the 12 o'clock
beam of the thrust reversers, which could result in separation of a
thrust reverser from the airplane, and consequent reduced
controllability of the airplane.
DATES: We must receive comments on this proposed AD by August 9, 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 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; 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: 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:
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-2012-0671;
Directorate Identifier 2011-NM-096-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 December 2, 2005, we issued AD 2005-25-21, Amendment 39-14414
(70 FR 73919, December 14, 2005). That AD required actions intended to
address an unsafe condition on Airbus Model A330-243, -341, -342, and -
343 airplanes equipped with Rolls-Royce RB211 TRENT 700 engines.
Since we issued AD 2005-25-21, Amendment 39-14414 (70 FR 73919,
December 14, 2005), the European Aviation Safety Agency (EASA), which
is the Technical Agent for the Member States of the European Community,
has issued EASA Airworthiness Directive 2011-0018, dated February 3,
2011 (referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI has added Model A330-
243F airplanes to the applicability. The MCAI states:
The life limits of the thrust reversers C-ducts are not
addressed by the definition of the structural life limits of Safe
Life items as defined in the A330 Airworthiness Limitations
Section--ALS Part 1. As a result, these life limits are covered by
an Airworthiness Directive (AD).
These life limits are due to unexpected high fatigue loads
(measured during certification tests) on the hinges integrated into
the 12 o'clock beam, which forms the upper extreme edge of the
thrust reverser C-Duct of Rolls Royce Trent 700 engines.
The aim of the [Direction G[eacute]n[eacute]rale de l'Aviation
Civile] (DGAC) France AD F-2001-528 was to mandate the life limits,
depending of the modifications applied to the C-duct.
Revision 1 of the DGAC France AD F-2001-528 deferred the
accomplishment threshold of the modification to be applied in-
service from 6,000 flight cycles (FC) to 6,500 FC.
Revision 2 of DGAC France AD F-2001-528 [which corresponds to
FAA AD 2005-25-21, Amendment 39-14414 (70 FR 73919, December 14,
2005)] was issued to update again the accomplishment threshold from
6,500 FC to 7,200 FC.
This [EASA] AD retains the requirements of DGAC France AD F-
2001-528 R2, which is superseded, and adds [certain] life limits.
The action required in this proposed AD is removing certain C-duct
assemblies of the left- and right-hand thrust reversers from service at
certain designated life limits. This proposed AD also adds Model A330-
243F airplanes to the applicability and revises the applicability to
include all airplanes of the affected models. The unsafe condition is
fatigue cracking of the hinges integrated into the 12 o'clock beam of
the thrust reversers, which could result in separation of a thrust
reverser from the airplane, and consequent reduced controllability of
the airplane. You may obtain further information by examining the MCAI
in the AD docket.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A330-78-3010, Revision
03, dated April 28, 2004. The actions
[[Page 37830]]
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 17 products of U.S. registry. We estimate that it
would take up to 48 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 $69,360, or $4,080 per product.
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) 2005-25-21, Amendment 39-14414 (70 FR 73919, December 14, 2005),
and adding the following new AD:
Airbus: Docket No. FAA-2012-0671; Directorate Identifier 2011-NM-
096-AD.
(a) Comments Due Date
We must receive comments by August 9, 2012.
(b) Affected ADs
This AD supersedes AD 2005-25-21, Amendment 39-14414 (70 FR
73919, December 14, 2005).
(c) Applicability
This AD applies to all Airbus Model A330-243, -243F, -341, -342
and -343 airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 78, Engine
Exhaust.
(e) Reason
This AD was prompted by new life limits on certain thrust
reverser C-duct assemblies. We are issuing this AD to prevent
fatigue cracking of the hinges integrated into the 12 o'clock beam
of the thrust reversers, which could result in separation of a
thrust reverser from the airplane, and consequent reduced
controllability 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) C-Duct Assembly Removal
At the applicable compliance time specified in table 1 of this
AD: Remove the applicable C-duct assemblies of the left- and right-
hand thrust reversers, 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). Thereafter, for any C-duct assembly
of the left- and right-hand thrust reversers installed after the
effective date of this AD, before the accumulation of the applicable
total flight cycles specified in table 1 of this AD: Remove the C-
duct assembly, in accordance with a method approved by either the
Manager, International Branch, ANM 116, Transport Airplane
Directorate, FAA; or the EASA (or its delegated agent).
Table 1--Part Removal Thresholds
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Part No.-- Compliance times at the later of the
times specified--
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HDTR3410L, HDTR3410R, Before the Within 3 months
HDTR3411L, HDTR3411R, accumulation of after the
HDTR3412R, HDTR3413R. 10,000 total flight effective date
cycles since the of this AD.
first installation of
C-duct on the
airplane.
HDTR3414L, HDTR3416R, Before the Within 3 months
HDTR3417R that have been accumulation of after the
modified in service as 10,000 total flight effective date
specified in Airbus Mandatory cycles since the of this AD.
Service Bulletin first installation of
A330[dash]78[dash]3010, or C-duct on the
Rolls-Royce Service Bulletin airplane.
RB.211-78-C899, at 7,200
total flight cycles or more
since first installation on
an airplane.
[[Page 37831]]
HDTR3414L, HDTR3416R, Before the Within 3 months
HDTR3417R that have been accumulation of after the
modified in production by 25,000 total flight effective date
Airbus Modification 47316; or cycles since the of this AD.
modified in service as first installation of
specified in Airbus Mandatory C-duct on the
Service Bulletin airplane.
A330[dash]78[dash]3010, or
Rolls-Royce Service Bulletin
RB.211-78-C899, before the
accumulation of 7,200 total
flight cycles since first
installation on an airplane.
HDTR3412L, HDTR3416L, Before the Within 3 months
HDTR3417L, HDTR3414R, accumulation of after the
HDTR3419R, HDTR3420R. 25,000 total flight effective date
cycles since the of this AD.
first installation of
C-duct on the
airplane.
HDTR3413L, HDTR3415R, Before the Within 3 months
HDTR3415L, HDTR3418R. accumulation of after the
40,000 total flight effective date
cycles since the C- of this AD.
duct was new.
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(h) 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: 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 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.
(i) Related Information
(1) Refer to MCAI EASA Airworthiness Directive 2011-0018, dated
February 3, 2011; and Airbus Mandatory Service Bulletin A330-78-
3010, Revision 03, dated April 28, 2004; for related information.
(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; 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 June 14, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-15461 Filed 6-22-12; 8:45 am]
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