[Federal Register Volume 76, Number 122 (Friday, June 24, 2011)]
[Rules and Regulations]
[Pages 36981-36983]
From the Federal Register Online via the Government Publishing 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: [email protected].
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: [email protected], 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]
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