
[Federal Register: September 9, 2008 (Volume 73, Number 175)]
[Rules and Regulations]               
[Page 52201-52203]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09se08-5]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28059; Directorate Identifier 2007-NE-13-AD; 
Amendment 39-15665; AD 2008-18-08]
RIN 2120-AA64

 
Airworthiness Directives; Rolls-Royce plc (RR) RB211 Trent 500, 
700, and 800 Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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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:

    This action is necessary following the discovery of IP 
Compressor Rotor rear balance land cracking on an in-service Trent 
800 engine. Stress analysis of the damaged rotor has shown a 
possible threat to the rotor integrity, the cracking therefore 
presents a potential unsafe condition.

We are issuing this AD to detect cracking on the intermediate pressure 
(IP) compressor rotor rear balance land. IP compressor rotor rear 
balance land cracking can lead to uncontained failure of the rotor and 
damage to the airplane.

DATES: This AD becomes effective October 14, 2008. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of October 14, 2008.

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

[[Page 52202]]

apply to the specified products. That NPRM was published in the Federal 
Register on October 15, 2007 (72 FR 58267). That NPRM proposed to 
correct an unsafe condition for the specified products. The MCAI states 
that:

    This Airworthiness Directive requires inspections for cracks in 
the rear balance land of the IP Compressor Rotor. The inspections 
comprise an on-wing one-off inspection by borescope for RR Trent 800 
engines which must be completed within a short timescale, and in-
shop inspections to be completed at each opportunity for RR Trent 
500, 700 and 800 engines (the in-shop inspection may be carried out 
in lieu of the on-wing inspection for the Trent 800 engines if it is 
accomplished within the timescale applicable to the on-wing 
inspection). This action is necessary following the discovery of IP 
Compressor Rotor rear balance land cracking on an in-service Trent 
800 engine. Stress analysis of the damaged rotor has shown a 
possible threat to the rotor integrity, the cracking therefore 
presents a potential unsafe condition. The cause of the cracking is 
currently not fully understood but evidence suggests it relates to 
an unusual balance weight condition.

You may obtain further information by examining the EASA AD in the AD 
docket.

Comments

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

Editorial Addition of a New Revision to Alert Service Bulletin RB.211-
72-AF260

    We received Alert Service Bulletin RB.211-72-AF260, Revision 2, 
dated July 4, 2007, after we issued the NPRM. We reviewed Revision 2 
and determined that no changes to the NPRM were necessary. We updated 
the revision number from Revision 1 to Revision 2 in this AD.

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

    We estimate that this AD will affect about 110 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 
3.5 work-hours per engine to perform the proposed actions and that the 
average labor rate is $80 per work-hour. Based on these figures, we 
estimate the total cost of the proposed AD to U.S. operators to be 
$30,800. Our cost estimate is exclusive of possible warranty coverage.

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.
    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:

2008-18-08 Rolls-Royce plc: Amendment 39-15665. Docket No. FAA-2007-
28059; Directorate Identifier 2007-NE-13-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
14, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce plc RB211 Trent 553-61, 
553A2-61, 556-61, 556A2-61, 556B-61, 560-61, 560A2-61, 768-60, 772-
60, 772B-60, 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 
895-17 turbofan engines. These engines are installed on, but not 
limited to, Airbus A330, A340-500, A340-600, and Boeing 777 series 
airplanes.

Reason

    (d) This action is necessary following the discovery of IP 
Compressor Rotor rear balance land cracking on an in-service Trent 
800 engine. Stress analysis of the damaged rotor has shown a 
possible threat to the rotor integrity, the cracking therefore 
presents a potential unsafe condition. The proposed AD would require 
actions that are intended to address the unsafe condition described 
in the MCAI.
    We are issuing this AD to detect cracking on the intermediate 
pressure (IP) compressor rotor rear balance land. IP compressor 
rotor rear balance land cracking can lead to uncontained failure of 
the rotor and damage to the airplane.

Actions and Compliance

    (e) Unless already done, do the following actions:

Inspection--On-Wing

    (1) Applicable to RR Trent 800 engines not previously inspected 
per Rolls-Royce RB211 Propulsion System Alert Non Modification 
Service Bulletin RB.211-72-AF260, Revision 2, dated July 4, 2007; or 
earlier issue: Within 400 flight cycles of the Effective Date of 
this AD inspect the IP Compressor rotor rear

[[Page 52203]]

balance land for cracks in accordance with Rolls-Royce RB211 
Propulsion System Alert Non Modification Service Bulletin RB.211-72-
AF313, dated February 22, 2007 section 3 Accomplishment 
Instructions. Engines on which cracking is found should be rejected 
from service.

Inspection--In-Shop

    (2) Applicable to RR Trent 500, 700 and 800 engines at each shop 
visit in which the engine is sufficiently disassembled to access the 
IP Compressor Module rear face: Inspect the IP Compressor rotor rear 
balance land for cracks in accordance with Rolls-Royce RB211 
Propulsion System Alert Non Modification Service Bulletin RB.211-72-
AF260, Revision 2, dated July 4, 2007; or earlier issue section 3 
Accomplishment Instructions.

Other FAA AD Provisions

    (f) Alternative Methods of Compliance (AMOCs): 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

    (g) Refer to EASA Airworthiness Directive 2007-0052, dated 
February 23, 2007, for related information.
    (h) 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

    (i) You must use the service information specified in Table 1 of 
this AD 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, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; 
telephone: 44 (0) 1332-242424; fax: 44 (0) 1332-249936.
    (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.

                                   Table 1--Material Incorporated by Reference
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    Alert Service Bulletin No.               Page                 Revision                     Date
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RB.211-72-AF260; Total pages--11..  ALL..................  Original.............  October 17, 2006.
RB.211-72-AF260; Total pages--11..  ALL..................  1....................  January 17, 2007.
RB.211-72-AF260; Total pages--11..  ALL..................  2....................  July 4, 2007.
RB.211-72-AF313; Total pages--11..  ALL..................  Original.............  February 22, 2007.
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    Issued in Burlington, Massachusetts, on August 25, 2008.
Mark A. Rumizen,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E8-20212 Filed 9-8-08; 8:45 am]

BILLING CODE 4910-13-P
