[Federal Register: December 14, 2005 (Volume 70, Number 239)]
[Rules and Regulations]
[Page 73919-73921]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14de05-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23252; Directorate Identifier 2004-NM-146-AD;
Amendment 39-14414; AD 2005-25-21]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-243, -341, -342, and
-343 Airplanes Equipped with Rolls-Royce RB211 TRENT 700 Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Model A330-243, -341, -342, and -343 airplanes equipped
with Rolls-Royce RB211 TRENT 700 engines. This AD requires modifying
the cowl assemblies of the left- and right-hand thrust reversers. This
AD results from a review of certification tests of the thrust reverser,
which revealed that certain structural components within the C-duct
need strengthening to meet high fatigue loads and maintain structural
integrity. 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.
DATES: This AD becomes effective December 29, 2005.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of December 29,
2005.
We must receive comments on this AD by February 13, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for the service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified us that an
unsafe condition may exist on certain Airbus Model A330-243, -341, -
342, and -343 airplanes equipped with Rolls-Royce RB211 TRENT 700
engines. The DGAC advises that a review of certification tests of the
thrust reverser revealed that certain structural components within the
C-duct need strengthening to meet high fatigue loads and maintain
structural integrity. Unexpected high loads were measured on the hinges
integrated into the 12 o'clock beam of the thrust reverser; the 12
o'clock beam forms the upper edge of the C-duct of the thrust reverser
on Rolls-Royce engines. This condition, if not corrected, could result
in fatigue cracking of the hinges integrated into the 12 o'clock beam
of the thrust reversers, separation of a thrust reverser from the
airplane, and consequent reduced controllability of the airplane.
Relevant Service Information
Airbus has issued Service Bulletin A330-78-3010, Revision 03, dated
April 28, 2004. The service bulletin describes procedures for modifying
the cowl assemblies of the left- and right-hand thrust reversers.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The DGAC mandated
the service information and issued French airworthiness directive F-
2001-528 R2, dated June 23, 2004, to ensure the continued airworthiness
of these airplanes in France.
The service bulletin refers to Rolls-Royce Service Bulletin RB.211-
78-C899, Revision 3, dated May 7, 2004, as an additional source of
service information for modifying the cowl assemblies of the left- and
right-hand thrust reversers. The modification includes related
investigative actions, and repair if necessary. The related
investigative actions include certain inspections for discrepancies of
the bores, bushings, plug holes, and cavity webs of the thrust
reversers.
FAA's Determination and Requirements of This AD
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for products of this type design that are certificated for
operation in the United States.
Therefore, 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. This
AD requires accomplishing the actions specified in the Airbus service
information described previously except as discussed under ``Difference
Among the AD, French Airworthiness Directive, and Airbus Service
Information.''
Difference Among the AD, French Airworthiness Directive, and Airbus
Service Information
The French airworthiness directive and the service information
specify a modification that involves replacement of certain thrust
reverser C-ducts with new ducts at or before specific total flight
cycle thresholds. This AD requires you to replace the affected parts
before the accumulation of those thresholds or within 6 months after
the effective date of the AD, whichever is later. A table containing
those flight cycle thresholds is specified in paragraph (f) of this AD.
We have included a 6-month grace period to ensure that any airplane
that is close to or has passed its applicable threshold (if imported
and placed on the U.S. Register) is not grounded as of the effective
date of the AD.
[[Page 73920]]
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
If an affected airplane is imported and placed on the U.S. Register
in the future, the required modification would take about 1 work hour
per airplane, at an average labor rate of $65 per work hour. Based on
these figures, the estimated cost of the modification would be $65 per
airplane.
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2005-
23252; Directorate Identifier 2004-NM-146-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that Web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
http://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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 have 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 the 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); 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. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2005-25-21 Airbus: Amendment 39-14414. Docket No. FAA-2005-23252;
Directorate Identifier 2004-NM-146-AD.
Effective Date
(a) This AD becomes effective December 29, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330-243, -341, -342, and -
343 airplanes, certificated in any category; equipped with Rolls-
Royce RB211 TRENT 700 engines.
Unsafe Condition
(d) This AD results from a review of certification tests of the
thrust reverser, which revealed that certain structural components
within the C-duct need strengthening to meet high fatigue loads and
maintain structural integrity. The FAA is 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.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Modification
(f) At the applicable compliance time specified in Table 1 of
this AD: Modify the cowl assemblies of the left- and right-hand
thrust reversers in accordance with Airbus Service Bulletin A330-78-
3010, Revision 03, dated April 28, 2004.
[[Page 73921]]
Table 1.--Modification (Part Replacement) Thresholds
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Replace part number-- At the later of the times specified--
-------------------------------
(1) 3410L, 3410R, 3411L, (i) Before the (ii) Within 6
3411R, 3412R, 3413R. accumulation of months after
10,000 total flight the effective
cycles since the C- date of this
duct was new. AD.
(2) 3414L, 3416R, 3417R....... (i) For airplanes (iii) Within 6
modified according to months after
Airbus Service the effective
Bulletin A330-78-3010 date of this
with more than 7,200 AD.
total flight cycles
since the C-duct was
new: Before the
accumulation of
10,000 total flight
cycles since the C-
duct was new.
(ii) For airplanes
modified according to
Airbus Service
Bulletin A330-78-3010
with less than or
equal to 7,200 total
flight cycles since
the C-duct was new:
Before the
accumulation of
25,000 total flight
cycles since the C-
duct was new.
(3) 3414L, 3416R, 3417R....... (i) For airplanes (ii) Within 6
modified in months after
production by Airbus the effective
Modification 47316: date of this
Before the AD.
accumulation of
25,000 total flight
cycles since the C-
duct was new.
(4) 3412L, 3414R.............. (i) For airplanes (ii) Within 6
modified in months after
production by Airbus the effective
Modification 46879: date of this
Before the AD.
accumulation of
25,000 total flight
cycles since the C-
duct was new.
(5) 3413L, 3415R.............. (i) Before the (ii) Within 6
accumulation of months after
40,000 total flight the effective
cycles since the C- date of this
duct was new. AD.
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Note 1: Airbus Service Bulletin A330-78-3010, Revision 03, dated
April 28, 2004, refers to Rolls-Royce Service Bulletin RB.211-78-
C899, Revision 3, dated May 7, 2004, as an additional source of
service information for modifying the cowl assemblies of the left-
and right-hand thrust reversers.
Parts Installation
(g) As of the effective date of this AD, no person may install,
on any airplane, a cowl assembly of the left- or right-hand thrust
reverser if the airplane has exceeded the applicable flight cycle
threshold specified in Table 1 of this AD.
Alternative Methods of Compliance (AMOCs)
(h) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
Related Information
(i) French airworthiness directive F-2001-528 R2, dated June 23,
2004, also addresses the subject of this AD.
Material Incorporated by Reference
(j) You must use Airbus Service Bulletin A330-78-3010, Revision
03, dated April 28, 2004, to perform the actions that are required
by this AD, unless the AD specifies otherwise. The Director of the
Federal Register approved the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for a copy of this service information. You may review
copies at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC; on the Internet at http://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the 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 December 2, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-23902 Filed 12-13-05; 8:45 am]
BILLING CODE 4910-13-P