
[Federal Register Volume 76, Number 122 (Friday, June 24, 2011)]
[Rules and Regulations]
[Pages 36981-36983]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-15677]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0445; Directorate Identifier 2011-NE-14-AD; 
Amendment 39-16727; AD 2011-13-04]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211--Trent 500 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), 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) 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:

    A Trent 500 engine has been found with thermal distress of the 
Intermediate Pressure (IP) Turbine Nozzle Guide Vanes. The resultant 
investigation found the root cause to be carbon blockage of the fuel 
spray nozzles. The source of the carbon has been identified to be 
the RH fuel manifold assembly. Analysis has verified that low fuel 
velocity and thermal input may cause formation of carbon in a 
specific region of the RH fuel manifold. As advanced thermal 
distress of IP Turbine components may potentially result in 
uncontained, high energy debris release, the formation of carbon in 
the RH fuel manifold constitutes a potentially unsafe condition. To 
address and correct this unsafe condition, Rolls Royce have 
developed a cleaning or replacement programme of the RH fuel 
manifold and an optional part replacement.

    We are issuing this AD to prevent the release of uncontained high-
energy debris in the event of IP turbine component failure, which could 
result in damage to the airplane.

DATES: This AD becomes effective July 11, 2011.
    We must receive comments on this AD by July 25, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: U.S. 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.

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: Alan Strom, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; telephone 781-238-7143; 
fax 781-238-7199; e-mail: alan.strom@faa.gov.

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 2011-0050, dated March 21, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    A Trent 500 engine has been found with thermal distress of the 
Intermediate Pressure (IP) Turbine Nozzle Guide Vanes. The resultant 
investigation found the root cause to be carbon blockage of the fuel 
spray nozzles. The source of the carbon has been identified to be 
the RH fuel manifold assembly. Analysis has verified that low fuel 
velocity and thermal input may cause formation of carbon in a 
specific region of the RH fuel manifold. As advanced thermal 
distress of IP Turbine components may potentially result in 
uncontained, high energy debris release, the formation of carbon in 
the RH fuel manifold constitutes a potentially unsafe condition. To 
address and correct this unsafe condition, Rolls Royce have 
developed a cleaning or replacement programme of the RH fuel 
manifold and an optional part replacement.


[[Page 36982]]


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

Relevant Service Information

    Rolls-Royce plc has issued Alert Service Bulletin No. RB.211-73-
AG422, Revision 2, dated January 14, 2011. The actions described in 
this service information are intended to correct the unsafe condition 
identified in the MCAI.

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 MCAI and service 
information referenced above. We are issuing this AD because we 
evaluated all information provided by EASA and determined the unsafe 
condition exists and is likely to exist or develop on other products of 
the same type design.

FAA's Determination of the Effective Date

    Since no domestic operators use this product, notice and 
opportunity for public comment before issuing this AD are unnecessary. 
Therefore, we are adopting this regulation immediately.

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-2011-0445; Directorate 
Identifier 2011-NE-14-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 
with FAA personnel concerning this AD. Using the search function of the 
Web site, anyone can find and read the comments in any of our dockets, 
including, if provided, 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).

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

    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:

2011-13-04 Rolls-Royce plc: Amendment 39-16727; Docket No. FAA-2011-
0445; Directorate Identifier 2011-NE-14-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective July 11, 
2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce plc RB211-Trent 553-61, 
RB211-Trent 553A2-61, RB211-Trent 556-61, RB211-Trent 556A2-61, 
RB211-Trent 556B-61, RB211-Trent 556B2-61, RB211-Trent 560-61, and 
RB211-Trent 560A2-61 turbofan engines, with right-hand (RH) fuel 
manifold assembly, part number FW18706, installed.

Reason

    (d) 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:

    A Trent 500 engine has been found with thermal distress of the 
Intermediate Pressure (IP) Turbine Nozzle Guide Vanes. The resultant 
investigation found the root cause to be carbon blockage of the fuel 
spray nozzles. The source of the carbon has been identified to be 
the RH fuel manifold assembly. Analysis has verified that low fuel 
velocity and thermal input may cause formation of carbon in a 
specific region of the RH fuel manifold.
    As advanced thermal distress of IP Turbine components may 
potentially result in uncontained, high energy debris release, the 
formation of carbon in the RH fuel manifold constitutes a 
potentially unsafe condition. To address and correct this unsafe 
condition, Rolls Royce have developed a cleaning or replacement 
programme of the RH fuel manifold and an optional part replacement.

    We are issuing this AD to prevent the release of uncontained 
high-energy debris in the event of IP turbine component failure, 
which could result in damage to the airplane.

Actions and Compliance

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

Initial Cleaning and Inspection, or Replacement

    (1) For engines that on the effective date of this AD, have not 
been repaired using Engine Management Program, Issue 7, dated May 7, 
2010 or later version; and

[[Page 36983]]

    (2) That have not incorporated Rolls-Royce Repeater Technical 
Variance TV97291, dated July 2009, or later version; and
    (3) That have not had the RH fuel manifold assembly cleaned 
using Overhaul Process Manual TSD594-J, Task 70-00-00-100-121, as 
instructed in Component Maintenance Manual, Tubes, Hoses, and Ducts, 
dated October 2009, or later version; and
    (4) That have not had the RH manifold assembly replaced with a 
new RH manifold assembly; and
    (5) That have not incorporated Rolls-Royce plc Alert Service 
Bulletin No. RB.211-73-AG327, Revision 1, dated May 4, 2010, or 
later version, then:
    (i) Initially clean and inspect the RH fuel manifold assembly or 
replace the RH fuel manifold assembly with a serviceable RH fuel 
manifold assembly.
    (ii) Guidance on cleaning, inspecting, or replacing of the RH 
manifold assembly, can be found in Rolls-Royce plc Alert Service 
Bulletin No. RB.211-73-AG422, Revision 2, dated January 14, 2011.
    (iii) Perform the cleaning, inspection, or replacement at the 
following times:
    (A) For engines with 3,200 cycles-since-new (CSN) or more, clean 
and inspect within 200 cycles after the effective date of this AD.
    (B) For engines with between 3,000 CSN and 3,199 CSN, clean and 
inspect no later than 3,400 CSN.
    (C) For engines with between 2,600 CSN and 2,999 CSN, clean and 
inspect within 400 cycles after the effective date of this AD.
    (D) For engines with between 2,400 CSN and 2,599 CSN, clean and 
inspect no later than 3,000 CSN.
    (E) For engines with between 1,300 CSN and 2,399 CSN, clean and 
inspect within 600 cycles after the effective date of this AD.
    (F) For engines with fewer than 1,300 CSN, clean and inspect no 
later than 1,900 CSN.
    (6) For engines that on the effective date of this AD, have been 
repaired using Engine Management Program, Issue 7, dated May 7, 2010 
or later version; or
    (7) That have incorporated Rolls-Royce Repeater Technical 
Variance TV97291, dated July 2009, or later version; or
    (8) That have had the RH fuel manifold assembly cleaned using 
Overhaul Process Manual TSD594-J, Task 70-00-00-100-121, as 
instructed in Component Maintenance Manual, Tubes, Hoses, and Ducts, 
dated October 2009, or later version; or
    (9) That have had the RH manifold assembly replaced with a new 
RH manifold assembly; or
    (10) That have incorporated Rolls-Royce plc Alert Service 
Bulletin No. RB.211-73-AG327, Revision 1, dated May 4, 2010, or 
later version, then:
    (i) Initially clean and inspect the RH fuel manifold assembly or 
replace the RH fuel manifold assembly with a serviceable RH fuel 
manifold assembly, within 1,300 cycles since the engine most 
recently met any of the requirements of paragraphs (e)(6) through 
(e)(10) of this AD.
    (ii) Guidance on cleaning, inspecting, or replacing of the RH 
manifold assembly, can be found in Rolls-Royce plc Alert Service 
Bulletin No. RB.211-73-AG422, Revision 2, dated January 14, 2011.

Repetitive Cleaning and Inspection, or Replacement

    (11) Thereafter, repetitively clean and inspect the RH fuel 
manifold assembly or replace the RH fuel manifold assembly with a 
serviceable RH fuel manifold assembly, within 1,300 cycles since 
performing the last cleaning and inspection or replacement.

Optional Terminating Action

    (12) As optional terminating action to the repetitive actions in 
this AD, remove RH fuel manifold assembly, part number FW18706, and 
install a redesigned RH fuel manifold assembly. Guidance on 
installing the redesigned RH fuel manifold assembly can be found in 
Rolls-Royce plc Service Bulletin No. RB.211-73-G547, dated December 
7, 2010.

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 Airworthiness 
Directive 2011-0050, dated March 21, 2011, Rolls-Royce plc Alert 
Service Bulletin No. RB.211-73-AG422, Revision 2, dated January 14, 
2011, and Rolls-Royce plc Service Bulletin No. RB.211-73-G547, dated 
December 7, 2010, for related information. Contact Rolls-Royce plc, 
Corporate Communications, P.O. Box 31, Derby, England, DE248BJ, 
telephone: 011-44-1332-242424; fax: 011-44-1332-245418; or e-mail 
via: http://www.rolls-royce.com/contact/civil_team.jsp, for a copy 
of this service information.
    (i) Contact Alan Strom, Aerospace Engineer, Engine Certification 
Office, FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; telephone 781-238-7143; fax 
781-238-7199; e-mail: alan.strom@faa.gov, for more information about 
this AD.

Material Incorporated by Reference

    (j) None.


    Issued in Burlington, Massachusetts, on June 14, 2011.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2011-15677 Filed 6-23-11; 8:45 am]
BILLING CODE 4910-13-P


