Airworthiness Directives; Airbus Model A330-243, -341, -342, and -343 Airplanes Equipped with Rolls-Royce RB211 TRENT 700 Engines, 73919-73921 [05-23902]

Download as PDF Federal Register / Vol. 70, No. 239 / Wednesday, December 14, 2005 / Rules and Regulations Done in Washington, DC, this 12th day of December 2005. Charles D. Lambert, Acting Under Secretary for Marketing and Regulatory Programs. [FR Doc. 05–24057 Filed 12–12–05; 11:30 am] BILLING CODE 3410–34–P 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 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330–243, –341, –342, and –343 airplanes equipped with RollsRoyce 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 Cduct 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 VerDate Aug<31>2005 15:23 Dec 13, 2005 Jkt 208001 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 Generale 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 Cduct 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. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 73919 The service bulletin refers to RollsRoyce 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. E:\FR\FM\14DER1.SGM 14DER1 73920 Federal Register / Vol. 70, No. 239 / Wednesday, December 14, 2005 / Rules and Regulations 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 VerDate Aug<31>2005 15:23 Dec 13, 2005 Jkt 208001 (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. 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 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 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. I 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 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. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 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. 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. E:\FR\FM\14DER1.SGM 14DER1 Federal Register / Vol. 70, No. 239 / Wednesday, December 14, 2005 / Rules and Regulations 73921 TABLE 1.—MODIFICATION (PART REPLACEMENT) THRESHOLDS Replace part number— At the later of the times specified— (1) 3410L, 3410R, 3411L, 3411R, 3412R, 3413R. (2) 3414L, 3416R, 3417R ............... (i) Before the accumulation of 10,000 total flight cycles since the Cduct was new. (i) For airplanes modified according to Airbus Service Bulletin A330– 78–3010 with more than 7,200 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. (i) For airplanes modified in production by Airbus Modification 47316: Before the accumulation of 25,000 total flight cycles since the Cduct was new. (i) For airplanes modified in production by Airbus Modification 46879: Before the accumulation of 25,000 total flight cycles since the Cduct was new. (i) Before the accumulation of 40,000 total flight cycles since the Cduct was new. (3) 3414L, 3416R, 3417R ............... (4) 3412L, 3414R ............................ (5) 3413L, 3415R ............................ 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. 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 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 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. 14 CFR Part 39 Related Information (i) French airworthiness directive F–2001– 528 R2, dated June 23, 2004, also addresses the subject of this AD. Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes 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/ VerDate Aug<31>2005 15:23 Dec 13, 2005 Jkt 208001 [Docket No. FAA–2005–22561; Directorate Identifier 2005–NM–136–AD; Amendment 39–14409; AD 2005–25–16] RIN 2120–AA64 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model ERJ 170 airplanes. This AD requires doing a general visual inspection of the passenger seat track attachments to determine if the attachment rod is installed and to check the torque value of the attachment bolts, and doing any corrective actions if necessary. This AD results from the finding of missing rods, which attach the passenger seat tracks to the airplane structure to absorb loads. We are issuing this AD to detect and correct missing attachment rods, which could result in reducing the ability of the seat to PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 (ii) Within 6 months after the effective date of this AD. (iii) Within 6 months after the effective date of this AD. (ii) Within 6 months after the effective date of this AD. (ii) Within 6 months after the effective date of this AD. (ii) Within 6 months after the effective date of this AD. withstand a hard landing or rejected takeoff and possible injury to passengers. This AD becomes effective January 18, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 18, 2006. DATES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC. Contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil, for service information identified in this AD. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (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 street address stated in the ADDRESSES section. E:\FR\FM\14DER1.SGM 14DER1

Agencies

[Federal Register Volume 70, Number 239 (Wednesday, December 14, 2005)]
[Rules and Regulations]
[Pages 73919-73921]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23902]


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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.

-----------------------------------------------------------------------

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
------------------------------------------------------------------------
 
------------------------------------------------------------------------
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.
------------------------------------------------------------------------


    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