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, 67361-67363 [E8-26200]
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Federal Register / Vol. 73, No. 221 / Friday, November 14, 2008 / Rules and Regulations
Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) Airworthiness
Directive 2007–0249, dated September 24,
2007; and Airbus Mandatory Service Bulletin
A320–26A1068, Revision 01, dated July 19,
2007; for related information.
Material Incorporated by Reference
(i) You must use Airbus Mandatory Service
Bulletin A320–26A1068, Revision 01,
excluding Appendix 01, dated July 19, 2007,
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 Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 33 33; Internet
https://www.airbus.com.
(3) You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; 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: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on October
9, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–25640 Filed 11–13–08; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
sroberts on PROD1PC70 with RULES
AGENCY:
15:52 Nov 13, 2008
Jkt 217001
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
https://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.
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.
Examining the AD Docket
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
VerDate Aug<31>2005
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:
67361
FAA’s Determination and Requirements
of This AD
You may examine the AD docket on
the Internet at https://
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
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
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
E:\FR\FM\14NOR1.SGM
14NOR1
67362
Federal Register / Vol. 73, No. 221 / Friday, November 14, 2008 / Rules and Regulations
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.
sroberts on PROD1PC70 with RULES
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 https://
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
VerDate Aug<31>2005
15:52 Nov 13, 2008
Jkt 217001
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
§ 39.13
[Amended]
2. The FAA amends § 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:
E:\FR\FM\14NOR1.SGM
14NOR1
Federal Register / Vol. 73, No. 221 / Friday, November 14, 2008 / Rules and Regulations
67363
TABLE 1—REQUIRED ACTIONS AND COMPLIANCE TIMES
Results of Borescope inspection
Actions that must be carried out
(i) Total number of IP turbine blade outer shroud dust
caps lifting is 0.
At intervals not to exceed 100 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.
At intervals not to exceed 20 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.
At intervals not to exceed 10 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.
Within 10 cycles, remove the engine from service and install 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.
Before further flight, remove the engine from service and install 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.
(ii) Total number of IP turbine blade outer shroud
dust caps lifting exceeds 0 but is equal to or fewer
than 10.
(iii) Total number of IP turbine blade outer shroud
dust caps lifting exceeds 10 but is equal to or
fewer than 20.
(iv) Total number of IP turbine blade outer shroud
dust caps lifting exceeds 20.
(v) Total number of IP turbine blade outer shroud
dust caps missing exceeds 1.
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.
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.
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
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
Document No.
Page
Alert Service Bulletin No. RB.211–72–AF994 .....................................................................
Total Pages: 24.
Service Bulletin No. RB.211–72–D733, including Supplement ...........................................
Total Pages: 9.
All ............
1
September 1, 2008.
All .............
1
March 6, 2008.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
sroberts on PROD1PC70 with RULES
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]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
15:52 Nov 13, 2008
Jkt 217001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1200; Directorate
Identifier 2008–NM–178–AD; Amendment
39–15737; AD 2008–23–16]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2B19 (Regional Jet
Series 100 & 440) Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to certain Bombardier
Model CL–600–2B19 (Regional Jet
Series 100 & 440) airplanes. The existing
AD currently requires inspecting to
identify the wing anti-ice ducts (piccolo
tubes) in the wing leading edge. For
airplanes with affected piccolo tubes,
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
Revision
Date
the existing AD requires revising the
airplane flight manual (AFM) to
introduce new procedures for operation
in icing conditions. The existing AD
provides an optional implementation of
repetitive inspections for cracks of
affected piccolo tubes, and corrective
actions if necessary, which terminates
the operational limitations. The existing
AD also provides an optional
installation of certain new piccolo
tubes, which terminates both the AFM
revision and the inspections. This AD
adds airplanes to the applicability,
requires revising the AFM to introduce
new procedures for operation in icing
conditions, and requires inspecting to
determine if certain anti-ice piccolo
ducts are installed, and replacing or
repairing the piccolo duct if necessary.
This AD also provides an optional
terminating action of replacing all
affected piccolo ducts. This AD results
from reports of failed piccolo tubes. We
are issuing this AD to prevent cracked
piccolo tubes, which could result in air
leakage, a possible adverse effect on the
anti-ice air distribution pattern and antiice capability without annunciation to
E:\FR\FM\14NOR1.SGM
14NOR1
]]>Agencies
[Federal Register Volume 73, Number 221 (Friday, November 14, 2008)]
[Rules and Regulations]
[Pages 67361-67363]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-26200]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 https://
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 https://
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 https://
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
------------------------------------------------------------------------
Results of Borescope inspection Actions that must be carried out
------------------------------------------------------------------------
(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.
------------------------------------------------------------------------
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
------------------------------------------------------------------------
Document No. Page Revision Date
------------------------------------------------------------------------
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.
------------------------------------------------------------------------
(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: https://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]
BILLING CODE 4910-13-P
