[Federal Register: November 14, 2008 (Volume 73, Number 221)]
[Rules and Regulations]
[Page 67361-67363]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14no08-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1063; Directorate Identifier 2008-NE-32-AD;
Amendment 39-15725; AD 2008-23-04]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Trent 553-61,
553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61
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) 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 affecting
only RB211 Trent 500 series turbofan engines that have not incorporated
Rolls-Royce plc (RR) Service Bulletin (SB) No. RB.211-72-D733, dated
August 21, 2002, or Revision 1 of that SB, dated March 6, 2008, as
follows:
The intermediate-pressure (IP) turbine blade shrouds of the
RB211 Trent 500 series engines feature closure welds (dust caps).
Development engine testing has revealed the potential for dust caps
to crack, lift and release. The latter may potentially allow hot
annulus gas to be ingested down the core passages of IP turbine
blades. Radial inflow of annulus gas into the IP disc rim region
could cause local heating of the disc firtree, resulting in creep of
the disc material. Failure of the disc rim in creep could
simultaneously release two blades and a disc post. Failure to this
extent could be beyond the containment capabilities of the casing.
Consequently, release of the dust caps would constitute a
potentially unsafe condition.
This AD requires actions that are intended to address the unsafe
condition described in the MCAI, which could result in uncontained
release of IP turbine blades and disc posts, resulting in damage to the
airplane.
DATES: This AD becomes effective December 1, 2008.
We must receive comments on this AD by December 15, 2008.
The Director of the Federal Register approved the incorporation by
reference of Rolls-Royce plc Alert Service Bulletin (ASB) No. RB.211-
72-AF994, Revision 1, dated September 1, 2008 and SB No. RB.211-72-
D733, Revision 1, dated March 6, 2008, listed in the AD as of December
1, 2008.
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: James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine & 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
EASA, which is the Technical Agent for the Member States of the
European Community, has issued EASA AD 2008-0109 R1, dated June 17,
2008, to correct an unsafe condition for the specified products. The
EASA AD states that for RB211 Trent 500 series turbofan engines that
have not incorporated RR SB No. RB.211-72-D733, dated August 21, 2002,
or Revision 1 of that SB, dated March 6, 2008, the unsafe condition is
as follows:
The intermediate-pressure (IP) turbine blade shrouds of the
RB211 Trent 500 series engines feature closure welds (dust caps).
Development engine testing has revealed the potential for dust caps
to crack, lift and release. The latter may potentially allow hot
annulus gas to be ingested down the core passages of IP turbine
blades. Radial inflow of annulus gas into the IP disc rim region
could cause local heating of the disc firtree, resulting in creep of
the disc material. Failure of the disc rim in creep could
simultaneously release two blades and a disc post. Failure to this
extent could be beyond the containment capabilities of the casing.
Consequently, release of the dust caps would constitute a
potentially unsafe condition.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Rolls-Royce plc has issued ASB No. RB.211-72-AF994, Revision 1,
dated September 1, 2008 and SB No. RB.211-72-D733, Revision 1, dated
March 6, 2008. 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
Although no airplanes registered in the United States use these
engines, the possibility exists that the engines could be used on
airplanes registered in the United States in the future. The unsafe
condition described previously is likely to exist or develop on other
engines of
[[Page 67362]]
the same type design. We are issuing this AD to prevent release of IP
turbine blades and disc posts, resulting in damage to the airplane.
This AD requires:
Initial and repetitive borescope inspections for missing
or lifting IP turbine blade outer shroud dust caps; and
Installation of core restrictor plugs in the IP turbine
blade roots, if 20 or more IP turbine blade outer shroud dust caps are
found lifting, or if 1 or more dust caps are missing.
FAA's Determination of the Effective Date
Since there are currently no domestic operators of this engine
model, notice and opportunity for public comment before issuing this AD
are unnecessary. Therefore, a situation exists that allows the
immediate adoption of this regulation.
Differences Between the AD and the MCAI
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we require the initial
borescope inspection to be done within 5 flight cycles, since the MCAI
required the initial inspection to be done before July 1, 2008, which
has already passed.
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-2008-1063; Directorate
Identifier 2008-NE-32-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:
2008-23-04 Rolls-Royce plc: Amendment 39-15725.; Docket No. FAA-
2008-1063; Directorate Identifier 2008-NE-32-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
1, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 553-61,
553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61
turbofan engines that have not incorporated RR Service Bulletin (SB)
No. RB.211-72-D733, dated August 21, 2002, or Revision 1 of that SB,
dated March 6, 2008. These engines are installed on, but not limited
to, Airbus A340-500 and -600 series airplanes.
Reason
(d) European Aviation Safety Agency (EASA) AD No. 2008-0109 R1,
dated June 17, 2008, states that for RB211 Trent 500 series turbofan
engines that have not incorporated RR SB No. RB.211-72-D733, dated
August 21, 2002, or Revision 1 of that SB, dated March 6, 2008, the
unsafe condition is as follows:
The intermediate-pressure (IP) turbine blade shrouds of the
RB211 Trent 500 series engines feature closure welds (dust caps).
Development engine testing has revealed the potential for dust caps
to crack, lift and release. The latter may potentially allow hot
annulus gas to be ingested down the core passages of IP turbine
blades. Radial inflow of annulus gas into the IP disc rim region
could cause local heating of the disc firtree, resulting in creep of
the disc material. Failure of the disc rim in creep could
simultaneously release two blades and a disc post. Failure to this
extent could be beyond the containment capabilities of the casing.
Consequently, release of the dust caps would constitute a
potentially unsafe condition.
We are issuing this AD to prevent uncontained release of IP turbine
blades and disc posts, resulting in damage to the airplane.
Actions and Compliance
(e) Unless already done, do the following actions.
(1) Within 5 flight cycles, on engines installed or not
installed, carry out the initial borescope inspection of the IP
turbine blade outer shroud dust caps, using Section 3,
Accomplishment Instructions of RR Alert Service Bulletin (ASB) No.
RB.211-72-AF994, Revision 1, dated September 1, 2008.
(2) Thereafter, depending on the results of the inspection
specified in paragraph (e)(1) of this AD, follow the appropriate
action in the following Table 1:
[[Page 67363]]
Table 1--Required Actions and Compliance Times
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Results of Borescope inspection Actions that must be carried out
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(i) Total number of IP turbine blade At intervals not to exceed 100
outer shroud dust caps lifting is 0. cycles, re-inspect the dust caps
using Section 3, Accomplishment
Instructions of Rolls-Royce plc
ASB No. RB.211-72-AF994,
Revision 1, dated September 1,
2008.
(ii) Total number of IP turbine blade At intervals not to exceed 20
outer shroud dust caps lifting cycles, re-inspect the dust caps
exceeds 0 but is equal to or fewer using Section 3, Accomplishment
than 10. Instructions of Rolls-Royce plc
ASB No. RB.211-72-AF994,
Revision 1, dated September 1,
2008.
(iii) Total number of IP turbine At intervals not to exceed 10
blade outer shroud dust caps lifting cycles, re-inspect the dust caps
exceeds 10 but is equal to or fewer using Section 3, Accomplishment
than 20. Instructions of Rolls-Royce plc
ASB No. RB.211-72-AF994,
Revision 1, dated September 1,
2008.
(iv) Total number of IP turbine blade Within 10 cycles, remove the
outer shroud dust caps lifting engine from service and install
exceeds 20. core restrictor plugs in the IP
turbine blade roots, using
Section 3, Accomplishment
Instructions of RR Service
Bulletin (SB) No. RB.211-72-
D733, Revision 1, dated March 6,
2008.
(v) Total number of IP turbine blade Before further flight, remove the
outer shroud dust caps missing engine from service and install
exceeds 1. core restrictor plugs in the IP
turbine blade roots, using
Section 3, Accomplishment
Instructions of RR SB No. RB.211-
72-D733, Revision 1, dated March
6, 2008.
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FAA AD Differences
(f) This AD differs from the Mandatory Continuing Airworthiness
Information (MCAI) EASA AD by requiring the initial borescope
inspection to be done within 5 flight cycles. The MCAI required the
initial inspection to be done before July 1, 2008, which has already
passed.
(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 MCAI EASA AD 2008-0109 R1, dated June 17, 2008, for
related information.
(i) Contact James Lawrence, Aerospace Engineer, Engine
Certification Office, FAA, Engine & 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 the Rolls-Royce plc service information
specified in the following Table 2 to do the actions required by
this AD.
Table 2--Material Incorporated by Reference
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Document No. Page Revision Date
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Alert Service Bulletin No. All........... 1 September 1,
RB.211-72-AF994. 2008.
Total Pages: 24.
Service Bulletin No. RB.211- All........... 1 March 6, 2008.
72-D733, including
Supplement.
Total Pages: 9.
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(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; 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 October 28, 2008.
Diane S. Romanosky,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-26200 Filed 11-13-08; 8:45 am]
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