Document ID: FAA-2007-28976-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Rolls-Royce plc (RR) RB211 Trent 768- 60, 772-60, 772B-60, and 772C-60 Turbofan Engines
Posted Date: 2007-10-26T04:00Z

[Federal Register: October 26, 2007 (Volume 72, Number 207)]
[Rules and Regulations]               
[Page 60762-60764]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26oc07-4]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28976; Directorate Identifier 2007-NE-28-AD; 
Amendment 39-15244; AD 2007-22-08]
RIN 2120-AA64

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

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

ACTION: Final rule; request for comments.

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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) provided by the aviation authority for 
the United Kingdom to identify and correct an unsafe condition on an 
aviation product. The MCAI states the following:

    This action is necessary following the discovery of IP 
Compressor Rotor stage 2-3 interstage spacer cracking on an in-
service Trent 700 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 under investigation.

We are issuing this AD to detect cracks in the stage 2-3 interstage 
spacer of the intermediate pressure (IP) Compressor Rotor. Cracking of 
the stage 2-3 interstage spacer could result in an uncontained engine 
failure and damage to the airplane.

DATES: This AD becomes effective November 13, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of RR service bulletins (SBs) RB.211-72-AE753, Revision 1, 
dated May 24, 2005, and RB.211-72-AF197, dated December 20, 2006, 
listed in the AD as of November 13, 2007.

ADDRESSES: You may send comments by any of the following methods:
     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, West Building Ground Floor, Room W12-140, 1200 New 
Jersey, Avenue, SE., 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.

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.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine & Propeller 
Directorate, 16 New England Executive Park, Burlington, MA 01803; e-
mail: christopher.spinney@faa.gov; telephone (781) 238-7175; fax (781) 
238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2007-0136, dated May 14, 2007, to correct an 
unsafe condition for the specified products. The EASA AD states:

    This Airworthiness Directive requires inspections for cracks in 
the stage 2-3 interstage spacer of the IP Compressor Rotor during 
shop visit.
    This action is necessary following the discovery of IP 
Compressor Rotor stage 2-3 interstage spacer cracking on an in-
service Trent 700 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 under investigation.

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

Relevant Service Information

    Rolls-Royce plc has issued Service Bulletins RB.211-72-AE753, 
Revision 1, dated May 24, 2005, and RB.211-72-AF197, dated December 20, 
2006. The actions described in that service information are intended to 
correct the unsafe condition identified in the EASA AD.

FAA's Determination and Requirements of this AD

    This product has been approved by the aviation authority of the 
United Kingdom, and is approved for operation in the United States. 
Pursuant to our bilateral agreement with the United Kingdom, they have 
notified us of the unsafe condition described in the EASA AD and 
service information referenced above. We are issuing this AD because we 
evaluated all the information provided by the EASA and determined the 
unsafe condition exists and is likely to exist or develop on other 
products of the same type design. We are issuing this AD to detect 
cracks in the stage 2-3 interstage spacer of the IP Compressor Rotor. 
Cracking of the stage 2-3 interstage spacer could result in an 
uncontained engine failure and damage to the airplane. This AD requires 
inspecting the stage 2-3 interstage spacer using an eddy current 
inspection process at every shop visit. You must use the service 
information described previously to perform the actions required by 
this AD.

FAA's Determination of the Effective Date

    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 768-60, 772-60, 772B-60, and 772C-60 turbofan 
engines of the same type design. Therefore, we determined that notice 
and opportunity for public comment before issuing this AD are 
unnecessary and that good cause exists for making this amendment 
effective in fewer than 30 days.

[[Page 60763]]

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2007-28976; Directorate 
Identifier 2007-NE-28-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    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 we 
receive about this AD.

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.

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:

2007-22-08 Rolls-Royce plc: Amendment 39-15244; Docket No. FAA-2007-
28976; Directorate Identifier 2007-NE-28-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
13, 2007.

Affected ADs

    (b) None.

Applicability

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

Reason

    (d) This action is necessary following the discovery of IP 
Compressor Rotor stage 2-3 interstage spacer cracking on an in-
service Trent 700 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 under investigation.
    We are issuing this AD to detect cracks in the stage 2-3 
interstage spacer of the IP Compressor Rotor. Cracking of the stage 
2-3 interstage spacer could result in an uncontained engine failure 
and damage to the airplane.

Actions and Compliance

    (e) Inspect the IP compressor drum stage 2-3 interstage spacer 
for cracking at every shop visit as follows:

Inspection In-shop

    (1) If the IP Compressor rotor is not removed from the IP 
Compressor Casing, inspect the IP compressor drum stage 2-3 
interstage spacer by borescope in accordance with Rolls-Royce RB211 
Propulsion System Alert Non Modification Service Bulletin RB211-72-
AE753 revision 1, section 3 Accomplishment Instructions (paragraphs 
F and G are applicable in revision 1).
    (2) If the IP Compressor rotor is removed from the IP Compressor 
Casing inspect the IP compressor drum stage 2-3 interstage spacer by 
Eddy Current Inspection in accordance with Rolls-Royce RB211 
propulsion System Alert Non Modification Service Bulletin RB211-72-
AF197 initial issue, section 3 accomplishment Instructions.
    (3) IP compressor drums on which cracking is identified by the 
above means must be rejected from service.

FAA AD Differences

    (f) None.

Other FAA AD Provisions

    (g) 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

    (h) Refer to EASA Airworthiness Directive 2007-0136, dated May 
14, 2007, for related information.
    (i) Contact Christopher Spinney, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & 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

    (j) 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, UK, 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 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.

[[Page 60764]]

                                  Table 1.--Material Incorporated by Reference
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       Service Bulletin No.                 Page                 Revision                      Date
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RB.211-72-AE753..................  All..................  1....................  May 24, 2005.
RB.211-72-AF197..................  All..................  Original.............  December 20, 2006.
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    Issued in Burlington, Massachusetts, on October 17, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E7-20913 Filed 10-25-07; 8:45 am]

BILLING CODE 4910-13-P