Document ID: FAA-2009-1004-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Rolls-Royce plc RB211-Trent 800 Series Turbofan Engines
Posted Date: 2010-03-29T04:00Z

[Federal Register: March 29, 2010 (Volume 75, Number 59)]
[Rules and Regulations]               
[Page 15321-15322]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29mr10-1]                         

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[[Page 15321]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1004; Directorate Identifier 2009-NE-36-AD; 
Amendment 39-16239; AD 2010-06-14]
RIN 2120-AA64

 
Airworthiness Directives; Rolls-Royce plc RB211-Trent 800 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    During 2004, an incident was reported involving uncontained 
multiple intermediate-pressure (IP) turbine blade release on a Trent 
700 engine. The blade release was the result of an overspeed of the 
IP turbine rotor that was initiated by an internal fire in the high-
pressure/intermediate-pressure (HP/IP) bearing chamber. Post-
incident analysis and investigation has established that blockage of 
the HP/IP turbine bearing oil vent tube due to carbon deposits was a 
significant factor in the failure sequence. The Trent 800 has a 
similar type design standard to that of the Trent 700 and has also 
been found in service to be susceptible to carbon deposits in the 
oil vent tube.

We are issuing this AD to prevent internal oil fires due to coking and 
carbon buildup in the HP/IP turbine bearing oil vent tube that could 
cause uncontained engine failure and damage to the airplane.

DATES: This AD becomes effective May 3, 2010. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of May 3, 2010.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on January 5, 2010 (75 
FR 264). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    During 2004, an incident was reported involving uncontained 
multiple IP turbine blade release on a Trent 700 engine. The blade 
release was the result of an overspeed of the IP turbine rotor that 
was initiated by an internal fire in the HP/IP bearing chamber. 
Post-incident analysis and investigation has established that 
blockage of the HP/IP turbine bearing oil vent tube due to carbon 
deposits was a significant factor in the failure sequence. The Trent 
800 has a similar type design standard to that of the Trent 700 and 
has also been found in service to be susceptible to carbon deposits 
in the oil vent tube.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. The commenter supports the 
NPRM.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed.

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect about 138 RB211 Trent 800 series turbofan engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 
one work-hour per engine to comply with this AD. The average labor rate 
is $80 per work-hour. Required parts will cost about $2,000 per engine. 
Based on these figures, we estimate the cost of the AD on U.S. 
operators to be $287,040.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this 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 this AD:

    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.

[[Page 15322]]

    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

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 provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

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 FAA amends Sec.  39.13 by adding the following new AD:

2010-06-14 Rolls-Royce plc: Amendment 39-16239. Docket No. FAA-2009-
1004; Directorate Identifier 2009-NE-36-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 3, 
2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce plc models RB211-Trent 875-
17, Trent 877-17, Trent 884-17, Trent 884B-17, Trent 892-17, Trent 
892B-17, and Trent 895-17 turbofan engines. These engines are 
installed on, but not limited to, Boeing 777 series airplanes.

Reason

    (d) During 2004, an incident was reported involving uncontained 
multiple intermediate-pressure (IP) turbine blade release on a Trent 
700 engine. The blade release was the result of an overspeed of the 
IP turbine rotor that was initiated by an internal fire in the high-
pressure/intermediate-pressure (HP/IP) bearing chamber. Post-
incident analysis and investigation has established that blockage of 
the HP/IP turbine bearing oil vent tube due to carbon deposits was a 
significant factor in the failure sequence. The Trent 800 has a 
similar type design standard to that of the Trent 700 and has also 
been found in service to be susceptible to carbon deposits in the 
oil vent tube.
    This AD results from mandatory continuing airworthiness 
information (MCAI) issued by an aviation authority of another 
country to identify and correct an unsafe condition on an aviation 
product. We are issuing this AD to prevent internal oil fires due to 
coking and carbon buildup in the HP/IP turbine bearing oil vent tube 
that could cause uncontained engine failure and damage to the 
airplane.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) At the next engine shop visit after the effective date of 
this AD and thereafter at each engine shop visit, using the 
Accomplishment Instructions of Rolls-Royce plc Alert Service 
Bulletin No. RB.211-72-AE362, Revision 1, dated April 3, 2009:
    (i) Inspect the HP/IP turbine bearing internal and external oil 
vent tubes and bearing chamber for carbon buildup.
    (ii) Clean and flush the tubes and bearing chamber as required.
    (iii) Reject any oil vent tubes that do not meet inspection 
requirements after cleaning.
    (2) This AD does not require reporting of inspection results, as 
does paragraphs 3.B.(4)(g) and 3.C.(9) of Rolls-Royce plc Alert 
Service Bulletin No. RB.211-72-AE362, Revision 1, dated April 3, 
2009.

FAA AD Differences

    (f) None.

Alternative Methods of Compliance (AMOCs)

    (g) The Manager, Engine Certification Office, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency AD 2009-0071 
(corrected April 14, 2009), for related information.
    (i) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

Material Incorporated by Reference

    (j) You must use Rolls-Royce plc Alert Service Bulletin No. 
RB.211-72-AE362, Revision 1, dated April 3, 2009, to do the actions 
required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Rolls-Royce plc, PO Box 31, Derby, England; telephone: 011-44-1332-
249428; fax: 011-44-1332-249223.
    (3) You may review copies at the FAA, New England Region, 12 New 
England Executive Park, Burlington, MA; 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.

    Issued in Burlington, Massachusetts on March 9, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-5788 Filed 3-26-10; 8:45 am]
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