Airworthiness Directives; Rolls-Royce plc RB211 Trent 500 Series Turbofan Engines, 6673-6675 [06-1145]

Download as PDF Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Rules and Regulations the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), 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. TABLE 3.—MATERIAL INCORPORATED BY REFERENCE Service Bulletin Boeing Service Bulletin DC10–57–154. Boeing Service Bulletin MD11–57–076. Date February 2, 2005. February 2, 2005. Dated: Issued in Renton, Washington, on January 30, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–1148 Filed 2–8–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–23279; Directorate Identifier 2005–NE–44–AD; Amendment 39– 14478; AD 2006–03–14] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211 Trent 500 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. cprice-sewell on PROD1PC66 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Rolls Royce plc (RR) RB211 Trent 500 series turbofan engines. This AD requires initial and repetitive borescope inspections of the high pressure-andintermediate pressure (HP–IP) turbine oil vent tubes and bearing chambers for coking and carbon buildup and VerDate Aug<31>2005 12:39 Feb 08, 2006 Jkt 208001 replacing the vent tubes if necessary. This AD results from a report of an RB211 Trent 700 series engine that experienced a disk shaft separation, overspeed of the IP turbine rotor, and multiple blade release of IP turbine blades. Since the design arrangement in the Trent 500 series engines is similar to that of the Trent 700 series engines, the same failure could occur in the Trent 500 series engines. We are issuing this AD to prevent internal oil fires caused by coking and carbon buildup, that could result in uncontained engine failure and damage to the airplane. DATES: Effective February 24, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of February 24, 2006. We must receive any comments on this AD by April 10, 2006. ADDRESSES: Use one of the following addresses to comment 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– 0001. • 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 Rolls-Royce plc, Technical Publications, P.O. Box 31, Derby, DE24 8BJ, UK; telephone: 011–44–1332– 242424; fax: 011–44–1332–249936, for the service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone (781) 238–7175; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is the airworthiness authority for the United Kingdom (UK) recently notified us that an unsafe condition might exist on RR RB211 Trent 500 Series turbofan engines. The CAA advises that a previous service incident in a Trent 700 engine indicates that carbon restriction in the vent tube can cause overpressurization of the HP–IP bearing chamber leading to oil ejection from the PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 6673 rear of the chamber. If this oil spray ignites, the fire can cause an IPT shaft failure, leading to overspeed and uncontained failure of the IPT disc. Since the design arrangement in the Trent 500 engines is similar to that of the Trent 700 engines, the same failure could occur in the Trent 500 series engines. We are issuing this AD to prevent internal oil fires caused by coking and carbon buildup, that could result in uncontained engine failure and damage to the airplane. Relevant Service Information We have reviewed and approved the technical contents of RR Alert Service Bulletin (ASB) RB.211–72–AE836, Revision 1, dated October 5, 2005. That ASB describes procedures for initial and repetitive borescope inspection and assessment of the HP–IP turbine oil vent tubes and bearing chamber. The CAA classified this service bulletin as mandatory and issued AD No. G–2005– 0029, dated October 4, 2005, in order to ensure the airworthiness of these RR Trent 500 series engines in the U.K. Bilateral Airworthiness Agreement These RB211 Trent 500 series turbofan engines are manufactured in the U.K. 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. Under this bilateral airworthiness agreement, the CAA kept the FAA informed of the situation described above. We have examined the findings of the CAA, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. FAA’s Determination and Requirements of This AD Although no airplanes that are registered in the United States use these engines, the possibility exists that the engines could be used on airplanes that are registered in the United States in the future. The unsafe condition described previously is likely to exist or develop on other RR RB211 Trent 500 series turbofan engines of the same type design. This AD requires initial and repetitive borescope inspections of the HP–IP turbine bearing oil vent tubes and bearing chambers for coking and carbon buildup; and replacement of the tubes if necessary. We are issuing this AD to prevent internal oil fires from coking and carbon buildup that could cause uncontained engine failure and damage to the E:\FR\FM\09FER1.SGM 09FER1 6674 Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Rules and Regulations airplane. You must use the service information described previously to perform the actions required by this AD. FAA’s Determination of the Effective Date Since there are currently no domestic operators of this engine model, notice and opportunity for public comment before issuing this AD are unnecessary. A situation exists that allows the immediate adoption of this regulation. cprice-sewell on PROD1PC66 with RULES Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to send us any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. FAA–2005–23279; Directorate Identifier 2005–NE–44–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule 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 the DMS 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 AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS 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, VerDate Aug<31>2005 12:39 Feb 08, 2006 Jkt 208001 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 summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘AD Docket No. FAA–2005– 23279; Directorate Identifier 2005–NE– 44–AD’’ in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I 2006–03–14 Rolls-Royce plc: Amendment 39–14478. Docket No. FAA–2005–23279; Directorate Identifier 2005–NE–44–AD. Effective Date (a) This airworthiness directive (AD) becomes effective February 24, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 553–61, 553A2–61, 556B–61, 556A2–61, 556–61, 556B2–61, 560–61, and 560A2–61 turbofan engines. These engines are installed on, but not limited to, Airbus A340–500 and A340–600 series airplanes. Unsafe Condition (d) This AD results from a report of an RB211 Trent 700 series engine that experienced a disk shaft separation, overspeed of the IP turbine rotor, and multiple blade release of IP turbine blades. We are issuing this AD to prevent internal oil fires caused by coking and carbon buildup, that could result in uncontained engine failure and damage to 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. Initial Inspection (f) Using section 3, Parts A and B of the Accomplishment Instructions of RR Alert Service Bulletin (ASB) RB.211–72–AE836, Revision 1, dated October 5, 2005, perform an initial inspection of the high pressureand-intermediate-pressure (HP–IP) turbine bearing oil vent tubes and bearing chambers as follows: (1) For IP Turbine modules (05 modules) with 9,600 hours time-since-new (TSN) or 1,200 cycles-since-new (CSN) or more on the effective date of this AD, carry out the inspection within 2,400 hours time-in-service (TIS) or 300 cycles-in-service (CIS) from the effective date of this AD, whichever occurs first. (2) For 05 modules that are below 9,600 hours TSN or 1,200 CSN on the effective date of this AD, carry out the inspection prior to 12,000 hours TSN or 1,500 CSN, whichever occurs first,. Repetitive Inspections (g) Repeat the inspection at intervals not to exceed 12,000 hours time-since-previousinspection (TSPI) or 1,500 cycles-sinceprevious-inspection (CSPI), whichever occurs first, if at the previous inspection, any of the following conditions were observed: (1) There was no carbon buildup of a visible thickness. (2) The cleaning tool, HU82105, could pass along the full length of the internal vent tube into the bearing chamber. E:\FR\FM\09FER1.SGM 09FER1 Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Rules and Regulations (3) The 8 mm diameter borescope could pass along the full length of the internal vent tube into the bearing chamber. (h) Repeat the inspection at intervals not to exceed 1,600 hours TSPI or 400 CSPI, whichever occurs first, if, at the previous inspection, the carbon restriction prevented the 8 mm diameter flexible borescope from passing through the internal vent tube, but the 6 mm diameter borescope could pass along the full length of the internal vent tube into the bearing chamber. (i) Remove the engine within 10 CSPI, if the carbon restriction prevented the 6 mm diameter borescope from passing through the full length of the internal vent tubes. DEPARTMENT OF TRANSPORTATION 05 Modules in the Shop SUMMARY: This amendment amends Standard Instrument Approach Procedures (SIAPs) for operations at certain airports. These regulatory actions are needed because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, addition of new obstacles, or changes in air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports. (j) For 05 modules in the shop on the effective date of this AD, inspect the vent tube for carbon buildup of a visible thickness and repair the vent tube as necessary prior to further flight. Information regarding the inspection and repair of vent tubes for 05 modules in the shop can be found in section B. of RR ASB RB.211–72–AE836, Revision 1, dated October 5, 2005. Alternative Methods of Compliance (k) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (l) United Kingdom Civil Aviation Authority airworthiness directive G–2005– 0029, dated October 4, 2005, also addresses the subject of this AD. Material Incorporated by Reference cprice-sewell on PROD1PC66 with RULES (m) You must use Rolls-Royce plc Alert Service Bulletin RB.211–72–AE836, Revision 1, dated October 5, 2005, to perform the inspections required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Rolls-Royce plc, Technical Publications, P.O. Box 31, Derby, DE24 8BJ, UK; telephone: 011–44–1332– 242424; fax: 011–44–1332–249936, 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., Nassif Building, Room PL–401, Washington, DC 20590–0001, 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 NARA, call 202–741–6030, or go to: http://www.archives.gov/federal-register/cfr/ ibrlocations.html. Issued in Burlington, Massachusetts, on February 1, 2006. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 06–1145 Filed 2–8–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 12:39 Feb 08, 2006 Jkt 208001 Federal Aviation Administration 14 CFR Part 97 [Docket No. 30479; Amdt. No. 3153] Standard Instrument Approach Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This rule is effective February 9, 2006. The compliance date for each SIAP is specified in the amendatory provisions. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of February 9, 2006. ADDRESSES: Availability of matter incorporated by reference in the amendment is as follows: For Examination— 1. FAA Rules Docket, FAA Headquarters Building, 800 Independence Ave, SW., Washington, DC 20591; 2. The FAA Regional Office of the region in which affected airport is located; or 3. The National Flight Procedures Office, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 or, 4. 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. For Purchase-—Individual SIAP copies may be obtained from: 1. FAA Public Inquiry Center (APA– 200), FAA Headquarters Building, 800 Independence Avenue, SW., Washington, DC 20591; or DATES: PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 6675 2. The FAA Regional Office of the region in which the affected airport is located. By Subscription—Copies of all SIAPs, mailed once every 2 weeks, are for sale by the Superintendent of Documents, U.S. Government Printing Office, Washington, DC 20402. FOR FURTHER INFORMATION CONTACT: Donald P. Pate, Flight Procedure Standards Branch (AFS–420), Flight Technologies and Programs Division, Flight Standards Service, Federal Aviation Administration, Mike Monroney Aeronautical Center, 6500 South MacArthur Blvd. Oklahoma City, OK. 73169 (Mail Address: P.O. Box 25082 Oklahoma City, OK. 73125) telephone: (405) 954–4164. SUPPLEMENTARY INFORMATION: This amendment to Title 14, Code of Federal Regulations, part 97 (14 CFR part 97) amends Standard Instrument Approach Procedures (SIAPs). The complete regulatory description of each SIAP is contained in the appropriate FAA Form 8260, as modified by the the National Flight Data Center (FDC)/Permanent Notice to Airmen (P-NOTAM), which is incorporated by reference in the amendment under 5 U.S.C. 552(a), 1 CFR part 51, and § 97.20 of the Code of Federal Regulations. Materials incorporated by reference are available for examination or purchase as stated above. The large number of SIAPs, their complex nature, and the need for a special format make their verbatim publication in the Federal Register expensive and impractical. Further, airmen do not use the regulatory text of the SIAPs, but refer to their graphic depiction on charts printed by publishers of aeronautical materials. Thus, the advantages of incorporation by reference are realized and publication of the complete description of each SIAP contained in FAA form documents is unnecessary. The provisions of this amendment state the affected CFR sections, with the types and effective dates of the SIAPs. This amendment also identifies the airport, its location, the procedure identification and the amendment number. The Rule This amendment to 14 CFR part 97 is effective upon publication of each separate SIAP as amended in the transmittal. For safety and timeliness of change considerations, this amendment incorporates only specific changes contained for each SIAP as modified by FDC/P–NOTAMs. The SIAPs, as modified by FDC P– NOTAM, and contained in this E:\FR\FM\09FER1.SGM 09FER1

Agencies

[Federal Register Volume 71, Number 27 (Thursday, February 9, 2006)]
[Rules and Regulations]
[Pages 6673-6675]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-1145]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23279; Directorate Identifier 2005-NE-44-AD; 
Amendment 39-14478; AD 2006-03-14]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Trent 500 Series 
Turbofan 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 
Rolls Royce plc (RR) RB211 Trent 500 series turbofan engines. This AD 
requires initial and repetitive borescope inspections of the high 
pressure-and-intermediate pressure (HP-IP) turbine oil vent tubes and 
bearing chambers for coking and carbon buildup and replacing the vent 
tubes if necessary. This AD results from a report of an RB211 Trent 700 
series engine that experienced a disk shaft separation, overspeed of 
the IP turbine rotor, and multiple blade release of IP turbine blades. 
Since the design arrangement in the Trent 500 series engines is similar 
to that of the Trent 700 series engines, the same failure could occur 
in the Trent 500 series engines. We are issuing this AD to prevent 
internal oil fires caused by coking and carbon buildup, that could 
result in uncontained engine failure and damage to the airplane.

DATES: Effective February 24, 2006. The Director of the Federal 
Register approved the incorporation by reference of certain 
publications listed in the regulations as of February 24, 2006.
    We must receive any comments on this AD by April 10, 2006.

ADDRESSES: Use one of the following addresses to comment 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 20590-0001.
     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 Rolls-Royce plc, Technical Publications, P.O. Box 31, 
Derby, DE24 8BJ, UK; telephone: 011-44-1332-242424; fax: 011-44-1332-
249936, for the service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (781) 238-7175; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is 
the airworthiness authority for the United Kingdom (UK) recently 
notified us that an unsafe condition might exist on RR RB211 Trent 500 
Series turbofan engines. The CAA advises that a previous service 
incident in a Trent 700 engine indicates that carbon restriction in the 
vent tube can cause over-pressurization of the HP-IP bearing chamber 
leading to oil ejection from the rear of the chamber. If this oil spray 
ignites, the fire can cause an IPT shaft failure, leading to overspeed 
and uncontained failure of the IPT disc. Since the design arrangement 
in the Trent 500 engines is similar to that of the Trent 700 engines, 
the same failure could occur in the Trent 500 series engines. We are 
issuing this AD to prevent internal oil fires caused by coking and 
carbon buildup, that could result in uncontained engine failure and 
damage to the airplane.

Relevant Service Information

    We have reviewed and approved the technical contents of RR Alert 
Service Bulletin (ASB) RB.211-72-AE836, Revision 1, dated October 5, 
2005. That ASB describes procedures for initial and repetitive 
borescope inspection and assessment of the HP-IP turbine oil vent tubes 
and bearing chamber. The CAA classified this service bulletin as 
mandatory and issued AD No. G-2005-0029, dated October 4, 2005, in 
order to ensure the airworthiness of these RR Trent 500 series engines 
in the U.K.

Bilateral Airworthiness Agreement

    These RB211 Trent 500 series turbofan engines are manufactured in 
the U.K. 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. Under this bilateral airworthiness agreement, the CAA kept 
the FAA informed of the situation described above. We have examined the 
findings of the CAA, reviewed all available information, and determined 
that AD action is necessary for products of this type design that are 
certificated for operation in the United States.

FAA's Determination and Requirements of This AD

    Although no airplanes that are registered in the United States use 
these engines, the possibility exists that the engines could be used on 
airplanes that are registered in the United States in the future. The 
unsafe condition described previously is likely to exist or develop on 
other RR RB211 Trent 500 series turbofan engines of the same type 
design. This AD requires initial and repetitive borescope inspections 
of the HP-IP turbine bearing oil vent tubes and bearing chambers for 
coking and carbon buildup; and replacement of the tubes if necessary.
    We are issuing this AD to prevent internal oil fires from coking 
and carbon buildup that could cause uncontained engine failure and 
damage to the

[[Page 6674]]

airplane. You must use the service information described previously to 
perform the actions required by this AD.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this engine 
model, notice and opportunity for public comment before issuing this AD 
are unnecessary. A situation exists that allows the immediate adoption 
of this regulation.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2005-23279; 
Directorate Identifier 2005-NE-44-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule 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 the DMS 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 AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is located on the plaza level of the Department of 
Transportation Nassif Building at the street address stated in 
ADDRESSES. Comments will be available in the AD docket shortly after 
the DMS 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 summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. FAA-2005-23279; Directorate Identifier 2005-NE-44-AD'' 
in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Under the authority delegated to me by the Administrator, the Federal 
Aviation Administration amends part 39 of the Federal Aviation 
Regulations (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 airworthiness 
directive:

2006-03-14 Rolls-Royce plc: Amendment 39-14478. Docket No. FAA-2005-
23279; Directorate Identifier 2005-NE-44-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
24, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 553-61, 
553A2-61, 556B-61, 556A2-61, 556-61, 556B2-61, 560-61, and 560A2-61 
turbofan engines. These engines are installed on, but not limited 
to, Airbus A340-500 and A340-600 series airplanes.

Unsafe Condition

    (d) This AD results from a report of an RB211 Trent 700 series 
engine that experienced a disk shaft separation, overspeed of the IP 
turbine rotor, and multiple blade release of IP turbine blades. We 
are issuing this AD to prevent internal oil fires caused by coking 
and carbon buildup, that could result in uncontained engine failure 
and damage to 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.

Initial Inspection

    (f) Using section 3, Parts A and B of the Accomplishment 
Instructions of RR Alert Service Bulletin (ASB) RB.211-72-AE836, 
Revision 1, dated October 5, 2005, perform an initial inspection of 
the high pressure-and-intermediate-pressure (HP-IP) turbine bearing 
oil vent tubes and bearing chambers as follows:
    (1) For IP Turbine modules (05 modules) with 9,600 hours time-
since-new (TSN) or 1,200 cycles-since-new (CSN) or more on the 
effective date of this AD, carry out the inspection within 2,400 
hours time-in-service (TIS) or 300 cycles-in-service (CIS) from the 
effective date of this AD, whichever occurs first.
    (2) For 05 modules that are below 9,600 hours TSN or 1,200 CSN 
on the effective date of this AD, carry out the inspection prior to 
12,000 hours TSN or 1,500 CSN, whichever occurs first,.

Repetitive Inspections

    (g) Repeat the inspection at intervals not to exceed 12,000 
hours time-since-previous-inspection (TSPI) or 1,500 cycles-since-
previous-inspection (CSPI), whichever occurs first, if at the 
previous inspection, any of the following conditions were observed:
    (1) There was no carbon buildup of a visible thickness.
    (2) The cleaning tool, HU82105, could pass along the full length 
of the internal vent tube into the bearing chamber.

[[Page 6675]]

    (3) The 8 mm diameter borescope could pass along the full length 
of the internal vent tube into the bearing chamber.
    (h) Repeat the inspection at intervals not to exceed 1,600 hours 
TSPI or 400 CSPI, whichever occurs first, if, at the previous 
inspection, the carbon restriction prevented the 8 mm diameter 
flexible borescope from passing through the internal vent tube, but 
the 6 mm diameter borescope could pass along the full length of the 
internal vent tube into the bearing chamber.
    (i) Remove the engine within 10 CSPI, if the carbon restriction 
prevented the 6 mm diameter borescope from passing through the full 
length of the internal vent tubes.

05 Modules in the Shop

    (j) For 05 modules in the shop on the effective date of this AD, 
inspect the vent tube for carbon buildup of a visible thickness and 
repair the vent tube as necessary prior to further flight. 
Information regarding the inspection and repair of vent tubes for 05 
modules in the shop can be found in section B. of RR ASB RB.211-72-
AE836, Revision 1, dated October 5, 2005.

Alternative Methods of Compliance

    (k) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (l) United Kingdom Civil Aviation Authority airworthiness 
directive G-2005-0029, dated October 4, 2005, also addresses the 
subject of this AD.

Material Incorporated by Reference

    (m) You must use Rolls-Royce plc Alert Service Bulletin RB.211-
72-AE836, Revision 1, dated October 5, 2005, to perform the 
inspections required by this AD. The Director of the Federal 
Register approved the incorporation by reference of this service 
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Rolls-Royce plc, Technical Publications, P.O. Box 31, Derby, 
DE24 8BJ, UK; telephone: 011-44-1332-242424; fax: 011-44-1332-
249936, 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., Nassif Building, Room PL-
401, Washington, DC 20590-0001, 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 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-
register/cfr/ibrlocations.html.

    Issued in Burlington, Massachusetts, on February 1, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 06-1145 Filed 2-8-06; 8:45 am]
BILLING CODE 4910-13-P