Document ID: FAA-2006-26052-0008
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Rolls-Royce plc, RB211 Trent 768-60, 772-60, and 772B-60 Turbofan Engines
Posted Date: 2007-11-29T05:00Z

[Federal Register: November 29, 2007 (Volume 72, Number 229)]
[Rules and Regulations]               
[Page 67568-67571]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29no07-5]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26052; Directorate Identifier 2006-NE-30-AD; 
Amendment 39-15275; AD 2007-24-09]
RIN 2120-AA64

 
Airworthiness Directives; Rolls-Royce plc, RB211 Trent 768-60, 
772-60, and 772B-60 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Rolls-Royce plc (RR) RB211 Trent 768-60, 772-60, and 772B-60 
turbofan engines. That AD currently requires initial and repetitive on-
wing or in-shop inspections of the high pressure/intermediate pressure 
(HP/IP) turbine bearing oil feed tube heat shield. This AD requires the 
same actions but introduces a terminating action to the repetitive 
inspections. This AD results from RR introducing a revised HP/IP 
turbine bearing support structure as terminating action to the 
repetitive inspections of the HP/IP turbine bearing oil feed tube heat 
shield. We are issuing this AD to prevent an uncontained failure of the 
HP turbine disc and damage to the airplane.

DATES: Effective December 14, 2007. The Director of the Federal 
Register previously approved the incorporation by reference of certain 
publications listed in the regulations as of December 19, 2006 (71 FR 
66229, November 14, 2006). The Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulations as of December 14, 2007.
    We must receive any comments on this AD by January 28, 2008.

ADDRESSES: Use one of the following addresses to comment on this AD.
     Federal eRulemaking Portal: Go to http://www.regulations.gov
 and follow the instructions for sending your 

comments electronically.
     Mail: U.S. Docket Management Facility, Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.
    Contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United 
Kingdom; telephone 44 (0) 1332 242424; Fax 44 (0)

[[Page 67569]]

1332 249936 for a copy of 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; e-
mail: Christopher.spinney@faa.gov; telephone (781) 238-7175; fax (781) 
238-7199.

SUPPLEMENTARY INFORMATION: On November 3, 2006, the FAA issued AD 2006-
23-11, Amendment 39-14823 (71 FR 66229, November 14, 2006). That AD 
requires initial and repetitive on-wing or in-shop inspections of the 
HP/IP turbine bearing oil feed tube heat shield. That AD was the result 
of a report that a damaged outer heat shield caused fretting of the oil 
feed tubes. That condition, if not corrected, could result in an 
uncontained failure of the HP turbine disc and damage to the airplane.

Actions Since AD 2006-23-11 Was Issued

    Since that AD was issued, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, recently notified us that RR introduced a revised 
HP/IP turbine bearing support structure to terminate the repetitive 
inspections. This AD requires initial and repetitive on-wing or in-shop 
inspections of the HP/IP turbine bearing oil feed tube heat shield, and 
requires revising the HP/IP turbine bearing support structure as 
terminating action to the repetitive inspections in this AD. We are 
issuing this AD to prevent an uncontained failure of the HP turbine 
disc and damage to the airplane.

Relevant Service Information

    We have reviewed and approved the technical contents of RR Service 
Bulletin (SB) No. RB.211-72-F117, Revision 2, dated September 25, 2006, 
RR SB No. RB.211-72-F227, Revision 1, dated October 8, 2007, and RR 
Immediate Operational Request SB No. RB.211-72-F048, Revision 11, dated 
September 9, 2006, that describe procedures for revising the HP/IP 
turbine bearing support structure. EASA classified these SBs as 
mandatory and issued AD 2007-0260 in order to ensure the airworthiness 
of these RR engines in Europe.

Bilateral Airworthiness Agreement

    These engine models are manufactured in the United Kingdom 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, EASA has kept the FAA informed of 
the situation described above. We have examined the findings of EASA, 
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 Trent 768-60, 772-60, and 772B-60 turbofan engines, the 
possibility exists that these 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 Trent 768-
60, 772-60, and 772B-60 turbofan engines of the same type design. We 
are issuing this AD to prevent an uncontained failure of the HP turbine 
disc and damage to the airplane. This AD requires initial and 
repetitive on-wing or in-shop inspections of the HP/IP turbine bearing 
oil feed tube heat shield, and requires revising the HP/IP turbine 
bearing support structure as terminating action to the repetitive 
inspections in this AD. 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. Therefore, 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-2006-26052; 
Directorate Identifier 2006-NE-30-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://www.regulations.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 
FDMS 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).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov
; or in person at the Docket Operations office 

between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is the same as 
the Mail address provided in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

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 this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;

[[Page 67570]]

    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 at the 
address listed under ADDRESSES.

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 removing Amendment 39-14823 (71 FR 
66229, November 14, 2006), and by adding a new airworthiness directive, 
Amendment 39-15275, to read as follows:

2007-24-09 Rolls-Royce plc: Amendment 39-15275. Docket No. FAA-2006-
26052; Directorate Identifier 2006-NE-30-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
14, 2007.

Affected ADs

    (b) This AD supersedes AD 2006-23-11, Amendment 39-14823.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 768-60, 
772-60, and 772B-60 turbofan engines. These engines are installed 
on, but not limited to, Airbus A330 series airplanes.

Unsafe Condition

    (d) This AD results from RR introducing a revised high pressure/
low pressure (HP/IP) turbine bearing support structure as 
terminating action to the repetitive inspections of the HP/IP 
turbine bearing oil feed tube heat shield. We are issuing this AD to 
prevent an uncontained failure of the HP turbine disc 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) Initially inspect the HP/IP turbine oil feed tube outer heat 
shield for cracks. Use either 3.A.(1) through 3.A.(3) on-wing 
procedures or 3.B.(1)(a) through 3.B.(1)(e) in-shop procedures of RR 
Alert Service Bulletin (ASB) No. RB.211-72-AF045, Revision 2, dated 
July 27, 2006, at one of the following compliance times:
    (1) At the next shop visit of the 05 Module regardless of the 
reason for the visit; or
    (2) Before one of the following intervals whichever occurs 
latest:
    (i) 10,000 hours or 2,500 cycles since new, whichever occurs 
first, or
    (ii) 2,500 cycles since overhaul of the 05 Module.

Repetitive Inspection

    (g) Re-inspect the HP/IP turbine oil feed tube outer heat shield 
for cracks as specified in the applicable criteria of paragraphs 
C.(1)(b)(i) through C(1)(b)(vi) or C(2)(b)(i) through C(2)(b)(ii) of 
RR ASB No. RB.211-72-AF045, Revision 2, dated July 27, 2006. Use 
either 3.A.(1) through 3.A.(3) on-wing procedures or 3.B.(1)(a) 
through 3.B.(1)(e) in-shop procedures of RR ASB RB.211-72-AF045, 
Revision 2, dated July 27, 2006.

Remove HP/IP Turbine Oil Feed Tube Outer Heat Shields From Service

    (h) Remove from service HP/IP turbine oil feed tube outer heat 
shields according to the applicable criteria in paragraphs 
C(1)(b)(vii) through C(1)(b)(vii) or C(2)(b)(iii) of RR ASB No. 
RB.211-72-AF045, Revision 2, dated July 27, 2006.

Terminating Action

    (i) At the next 05 Module overhaul after the effective date of 
this AD, or before May 31, 2010, whichever occurs first, as 
terminating action to the repetitive inspections in this AD, 
introduce the revised HP/IP turbine bearing support structure.
    (j) Use one of the following to introduce the revised HP/IP 
turbine bearing support structure:
    (1) RR Service Bulletin (SB) No. RB.211-72-F117, Revision 2, 
dated September 25, 2006; or
    (2) RR SB No. RB.211-72-F227, Revision 1, dated October 8, 2007; 
or
    (3) RR Immediate Operational Request SB No. RB.211-72-F048, 
Revision 11, dated September 9, 2006.

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) European Aviation Safety Agency AD 2007-0260, dated October 
2, 2007, also addresses the subject of this AD.
    (m) Contact Christopher Spinney, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
Christopher.spinney@faa.gov; telephone (781) 238-7175; fax (781) 

238-7199, for more information about this AD.

Material Incorporated by Reference

    (n) You must use the Rolls-Royce service information in Table 1 
of this AD to perform the inspections and terminating action 
required by this AD. The Director of the Federal Register previously 
approved the incorporation by reference of Rolls-Royce plc Alert 
Service Bulletin No. RB.211-72-AF045, Revision 2, dated July 27, 
2006, as of December 19, 2006 (71 FR 66229, November 14, 2006).The 
Director of the Federal Register approved the incorporation by 
reference of the other service bulletins listed in Table 1 of this 
AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact 
Rolls-Royce plc P.O. Box 31, Derby, DE24 8BJ, United Kingdom; 
telephone 44 (0) 1332 242424; Fax 44 (0) 1332 249936 for a copy of 
this service information. You may review copies at the FAA, New 
England Region, 12 New England Executive Park, Burlington, MA 01803; 
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/ibr-locations.html
.

                                  Table 1.--Material Incorporated by Reference
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       Service Bulletin No.                  Page             Revision                     Date
----------------------------------------------------------------------------------------------------------------
RB.211-72-AF045...................  All...................            2  July 27, 2006.
RB.211-72-F048....................  All...................           11  September 9, 2006.
RB.211-72-F117....................  All...................            2  September 25, 2006.
RB.211-72-F227....................  All...................            1  October 8, 2007.
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[[Page 67571]]

    Issued in Burlington, Massachusetts, on November 20, 2007.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-23020 Filed 11-28-07; 8:45 am]

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