Airworthiness Directives; Rolls-Royce plc RB211 Trent 500 Series Turbofan Engines, 6673-6675 [06-1145]
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Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Rules and Regulations
the AD specifies otherwise. The Director of
the Federal Register approved the
incorporation by reference of these
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact Boeing
Commercial Airplanes, Long Beach Division,
3855 Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and Service
Management, Dept. C1–L5A (D800–0024), for
a copy of this service information. You may
review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street SW., Room PL–401,
Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
TABLE 3.—MATERIAL INCORPORATED
BY REFERENCE
Service Bulletin
Boeing Service Bulletin DC10–57–154.
Boeing Service Bulletin MD11–57–076.
Date
February 2, 2005.
February 2, 2005.
Dated: Issued in Renton, Washington, on
January 30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–1148 Filed 2–8–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–23279; Directorate
Identifier 2005–NE–44–AD; Amendment 39–
14478; AD 2006–03–14]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc RB211 Trent 500 Series Turbofan
Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
cprice-sewell on PROD1PC66 with RULES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for Rolls
Royce plc (RR) RB211 Trent 500 series
turbofan engines. This AD requires
initial and repetitive borescope
inspections of the high pressure-andintermediate pressure (HP–IP) turbine
oil vent tubes and bearing chambers for
coking and carbon buildup and
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12:39 Feb 08, 2006
Jkt 208001
replacing the vent tubes if necessary.
This AD results from a report of an
RB211 Trent 700 series engine that
experienced a disk shaft separation,
overspeed of the IP turbine rotor, and
multiple blade release of IP turbine
blades. Since the design arrangement in
the Trent 500 series engines is similar
to that of the Trent 700 series engines,
the same failure could occur in the
Trent 500 series engines. We are issuing
this AD to prevent internal oil fires
caused by coking and carbon buildup,
that could result in uncontained engine
failure and damage to the airplane.
DATES: Effective February 24, 2006. The
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulations as of February 24, 2006.
We must receive any comments on
this AD by April 10, 2006.
ADDRESSES: Use one of the following
addresses to comment on this AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Rolls-Royce plc, Technical
Publications, P.O. Box 31, Derby, DE24
8BJ, UK; telephone: 011–44–1332–
242424; fax: 011–44–1332–249936, for
the service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT:
Christopher Spinney, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803–5299; telephone
(781) 238–7175; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION: The Civil
Aviation Authority (CAA), which is the
airworthiness authority for the United
Kingdom (UK) recently notified us that
an unsafe condition might exist on RR
RB211 Trent 500 Series turbofan
engines. The CAA advises that a
previous service incident in a Trent 700
engine indicates that carbon restriction
in the vent tube can cause overpressurization of the HP–IP bearing
chamber leading to oil ejection from the
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6673
rear of the chamber. If this oil spray
ignites, the fire can cause an IPT shaft
failure, leading to overspeed and
uncontained failure of the IPT disc.
Since the design arrangement in the
Trent 500 engines is similar to that of
the Trent 700 engines, the same failure
could occur in the Trent 500 series
engines. We are issuing this AD to
prevent internal oil fires caused by
coking and carbon buildup, that could
result in uncontained engine failure and
damage to the airplane.
Relevant Service Information
We have reviewed and approved the
technical contents of RR Alert Service
Bulletin (ASB) RB.211–72–AE836,
Revision 1, dated October 5, 2005. That
ASB describes procedures for initial and
repetitive borescope inspection and
assessment of the HP–IP turbine oil vent
tubes and bearing chamber. The CAA
classified this service bulletin as
mandatory and issued AD No. G–2005–
0029, dated October 4, 2005, in order to
ensure the airworthiness of these RR
Trent 500 series engines in the U.K.
Bilateral Airworthiness Agreement
These RB211 Trent 500 series
turbofan engines are manufactured in
the U.K. and are type certificated for
operation in the United States under the
provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. Under this
bilateral airworthiness agreement, the
CAA kept the FAA informed of the
situation described above. We have
examined the findings of the CAA,
reviewed all available information, and
determined that AD action is necessary
for products of this type design that are
certificated for operation in the United
States.
FAA’s Determination and Requirements
of This AD
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 500 series
turbofan engines of the same type
design. This AD requires initial and
repetitive borescope inspections of the
HP–IP turbine bearing oil vent tubes and
bearing chambers for coking and carbon
buildup; and replacement of the tubes if
necessary.
We are issuing this AD to prevent
internal oil fires from coking and carbon
buildup that could cause uncontained
engine failure and damage to the
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Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Rules and Regulations
airplane. You must use the service
information described previously to
perform the actions required by this AD.
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.
A situation exists that allows the
immediate adoption of this regulation.
cprice-sewell on PROD1PC66 with RULES
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to send us any
written relevant data, views, or
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
FAA–2005–23279; Directorate Identifier
2005–NE–44–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the rule that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
dms.dot.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 DMS Web site,
anyone can find and read the comments
in any of our dockets, including 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) or you may visit
https://dms.dot.gov.
Examining the AD Docket
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
Facility Docket Office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The Docket
Office (telephone (800) 647–5227) is
located on the plaza level of the
Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the DMS
receives them.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
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12:39 Feb 08, 2006
Jkt 208001
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 have 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 that the regulation:
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 summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘AD Docket No. FAA–2005–
23279; Directorate Identifier 2005–NE–
44–AD’’ in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Under the authority delegated to me
by the Administrator, the Federal
Aviation Administration amends part 39
of the Federal Aviation Regulations (14
CFR part 39) as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
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Frm 00012
Fmt 4700
Sfmt 4700
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
I
2006–03–14 Rolls-Royce plc: Amendment
39–14478. Docket No. FAA–2005–23279;
Directorate Identifier 2005–NE–44–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective February 24, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc (RR)
RB211 Trent 553–61, 553A2–61, 556B–61,
556A2–61, 556–61, 556B2–61, 560–61, and
560A2–61 turbofan engines. These engines
are installed on, but not limited to, Airbus
A340–500 and A340–600 series airplanes.
Unsafe Condition
(d) This AD results from a report of an
RB211 Trent 700 series engine that
experienced a disk shaft separation,
overspeed of the IP turbine rotor, and
multiple blade release of IP turbine blades.
We are issuing this AD to prevent internal oil
fires caused by coking and carbon buildup,
that could result in uncontained engine
failure and damage to the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
Initial Inspection
(f) Using section 3, Parts A and B of the
Accomplishment Instructions of RR Alert
Service Bulletin (ASB) RB.211–72–AE836,
Revision 1, dated October 5, 2005, perform
an initial inspection of the high pressureand-intermediate-pressure (HP–IP) turbine
bearing oil vent tubes and bearing chambers
as follows:
(1) For IP Turbine modules (05 modules)
with 9,600 hours time-since-new (TSN) or
1,200 cycles-since-new (CSN) or more on the
effective date of this AD, carry out the
inspection within 2,400 hours time-in-service
(TIS) or 300 cycles-in-service (CIS) from the
effective date of this AD, whichever occurs
first.
(2) For 05 modules that are below 9,600
hours TSN or 1,200 CSN on the effective date
of this AD, carry out the inspection prior to
12,000 hours TSN or 1,500 CSN, whichever
occurs first,.
Repetitive Inspections
(g) Repeat the inspection at intervals not to
exceed 12,000 hours time-since-previousinspection (TSPI) or 1,500 cycles-sinceprevious-inspection (CSPI), whichever occurs
first, if at the previous inspection, any of the
following conditions were observed:
(1) There was no carbon buildup of a
visible thickness.
(2) The cleaning tool, HU82105, could pass
along the full length of the internal vent tube
into the bearing chamber.
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Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Rules and Regulations
(3) The 8 mm diameter borescope could
pass along the full length of the internal vent
tube into the bearing chamber.
(h) Repeat the inspection at intervals not to
exceed 1,600 hours TSPI or 400 CSPI,
whichever occurs first, if, at the previous
inspection, the carbon restriction prevented
the 8 mm diameter flexible borescope from
passing through the internal vent tube, but
the 6 mm diameter borescope could pass
along the full length of the internal vent tube
into the bearing chamber.
(i) Remove the engine within 10 CSPI, if
the carbon restriction prevented the 6 mm
diameter borescope from passing through the
full length of the internal vent tubes.
DEPARTMENT OF TRANSPORTATION
05 Modules in the Shop
SUMMARY: This amendment amends
Standard Instrument Approach
Procedures (SIAPs) for operations at
certain airports. These regulatory
actions are needed because of changes
occurring in the National Airspace
System, such as the commissioning of
new navigational facilities, addition of
new obstacles, or changes in air traffic
requirements. These changes are
designed to provide safe and efficient
use of the navigable airspace and to
promote safe flight operations under
instrument flight rules at the affected
airports.
(j) For 05 modules in the shop on the
effective date of this AD, inspect the vent
tube for carbon buildup of a visible thickness
and repair the vent tube as necessary prior
to further flight. Information regarding the
inspection and repair of vent tubes for 05
modules in the shop can be found in section
B. of RR ASB RB.211–72–AE836, Revision 1,
dated October 5, 2005.
Alternative Methods of Compliance
(k) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(l) United Kingdom Civil Aviation
Authority airworthiness directive G–2005–
0029, dated October 4, 2005, also addresses
the subject of this AD.
Material Incorporated by Reference
cprice-sewell on PROD1PC66 with RULES
(m) You must use Rolls-Royce plc Alert
Service Bulletin RB.211–72–AE836, Revision
1, dated October 5, 2005, to perform the
inspections required by this AD. The Director
of the Federal Register approved the
incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Contact Rolls-Royce plc,
Technical Publications, P.O. Box 31, Derby,
DE24 8BJ, UK; telephone: 011–44–1332–
242424; fax: 011–44–1332–249936, for a copy
of this service information. You may review
copies at the Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building, Room
PL–401, Washington, DC 20590–0001, on the
internet at https://dms.dot.gov; 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.
Issued in Burlington, Massachusetts, on
February 1, 2006.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 06–1145 Filed 2–8–06; 8:45 am]
BILLING CODE 4910–13–P
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12:39 Feb 08, 2006
Jkt 208001
Federal Aviation Administration
14 CFR Part 97
[Docket No. 30479; Amdt. No. 3153]
Standard Instrument Approach
Procedures; Miscellaneous
Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This rule is effective February 9,
2006. The compliance date for each
SIAP is specified in the amendatory
provisions.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of February 9,
2006.
ADDRESSES: Availability of matter
incorporated by reference in the
amendment is as follows:
For Examination—
1. FAA Rules Docket, FAA
Headquarters Building, 800
Independence Ave, SW., Washington,
DC 20591;
2. The FAA Regional Office of the
region in which affected airport is
located; or
3. The National Flight Procedures
Office, 6500 South MacArthur Blvd.,
Oklahoma City, OK 73169 or,
4. 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.
For Purchase-—Individual SIAP
copies may be obtained from:
1. FAA Public Inquiry Center (APA–
200), FAA Headquarters Building, 800
Independence Avenue, SW.,
Washington, DC 20591; or
DATES:
PO 00000
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6675
2. The FAA Regional Office of the
region in which the affected airport is
located.
By Subscription—Copies of all SIAPs,
mailed once every 2 weeks, are for sale
by the Superintendent of Documents,
U.S. Government Printing Office,
Washington, DC 20402.
FOR FURTHER INFORMATION CONTACT:
Donald P. Pate, Flight Procedure
Standards Branch (AFS–420), Flight
Technologies and Programs Division,
Flight Standards Service, Federal
Aviation Administration, Mike
Monroney Aeronautical Center, 6500
South MacArthur Blvd. Oklahoma City,
OK. 73169 (Mail Address: P.O. Box
25082 Oklahoma City, OK. 73125)
telephone: (405) 954–4164.
SUPPLEMENTARY INFORMATION: This
amendment to Title 14, Code of Federal
Regulations, part 97 (14 CFR part 97)
amends Standard Instrument Approach
Procedures (SIAPs). The complete
regulatory description of each SIAP is
contained in the appropriate FAA Form
8260, as modified by the the National
Flight Data Center (FDC)/Permanent
Notice to Airmen (P-NOTAM), which is
incorporated by reference in the
amendment under 5 U.S.C. 552(a), 1
CFR part 51, and § 97.20 of the Code of
Federal Regulations. Materials
incorporated by reference are available
for examination or purchase as stated
above.
The large number of SIAPs, their
complex nature, and the need for a
special format make their verbatim
publication in the Federal Register
expensive and impractical. Further,
airmen do not use the regulatory text of
the SIAPs, but refer to their graphic
depiction on charts printed by
publishers of aeronautical materials.
Thus, the advantages of incorporation
by reference are realized and
publication of the complete description
of each SIAP contained in FAA form
documents is unnecessary. The
provisions of this amendment state the
affected CFR sections, with the types
and effective dates of the SIAPs. This
amendment also identifies the airport,
its location, the procedure identification
and the amendment number.
The Rule
This amendment to 14 CFR part 97 is
effective upon publication of each
separate SIAP as amended in the
transmittal. For safety and timeliness of
change considerations, this amendment
incorporates only specific changes
contained for each SIAP as modified by
FDC/P–NOTAMs.
The SIAPs, as modified by FDC P–
NOTAM, and contained in this
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]]>Agencies
[Federal Register Volume 71, Number 27 (Thursday, February 9, 2006)]
[Rules and Regulations]
[Pages 6673-6675]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-1145]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23279; Directorate Identifier 2005-NE-44-AD;
Amendment 39-14478; AD 2006-03-14]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Trent 500 Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Rolls Royce plc (RR) RB211 Trent 500 series turbofan engines. This AD
requires initial and repetitive borescope inspections of the high
pressure-and-intermediate pressure (HP-IP) turbine oil vent tubes and
bearing chambers for coking and carbon buildup and replacing the vent
tubes if necessary. This AD results from a report of an RB211 Trent 700
series engine that experienced a disk shaft separation, overspeed of
the IP turbine rotor, and multiple blade release of IP turbine blades.
Since the design arrangement in the Trent 500 series engines is similar
to that of the Trent 700 series engines, the same failure could occur
in the Trent 500 series engines. We are issuing this AD to prevent
internal oil fires caused by coking and carbon buildup, that could
result in uncontained engine failure and damage to the airplane.
DATES: Effective February 24, 2006. The Director of the Federal
Register approved the incorporation by reference of certain
publications listed in the regulations as of February 24, 2006.
We must receive any comments on this AD by April 10, 2006.
ADDRESSES: Use one of the following addresses to comment on this AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Rolls-Royce plc, Technical Publications, P.O. Box 31,
Derby, DE24 8BJ, UK; telephone: 011-44-1332-242424; fax: 011-44-1332-
249936, for the service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (781) 238-7175; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is
the airworthiness authority for the United Kingdom (UK) recently
notified us that an unsafe condition might exist on RR RB211 Trent 500
Series turbofan engines. The CAA advises that a previous service
incident in a Trent 700 engine indicates that carbon restriction in the
vent tube can cause over-pressurization of the HP-IP bearing chamber
leading to oil ejection from the rear of the chamber. If this oil spray
ignites, the fire can cause an IPT shaft failure, leading to overspeed
and uncontained failure of the IPT disc. Since the design arrangement
in the Trent 500 engines is similar to that of the Trent 700 engines,
the same failure could occur in the Trent 500 series engines. We are
issuing this AD to prevent internal oil fires caused by coking and
carbon buildup, that could result in uncontained engine failure and
damage to the airplane.
Relevant Service Information
We have reviewed and approved the technical contents of RR Alert
Service Bulletin (ASB) RB.211-72-AE836, Revision 1, dated October 5,
2005. That ASB describes procedures for initial and repetitive
borescope inspection and assessment of the HP-IP turbine oil vent tubes
and bearing chamber. The CAA classified this service bulletin as
mandatory and issued AD No. G-2005-0029, dated October 4, 2005, in
order to ensure the airworthiness of these RR Trent 500 series engines
in the U.K.
Bilateral Airworthiness Agreement
These RB211 Trent 500 series turbofan engines are manufactured in
the U.K. and are type certificated for operation in the United States
under the provisions of section 21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the applicable bilateral airworthiness
agreement. Under this bilateral airworthiness agreement, the CAA kept
the FAA informed of the situation described above. We have examined the
findings of the CAA, reviewed all available information, and determined
that AD action is necessary for products of this type design that are
certificated for operation in the United States.
FAA's Determination and Requirements of This AD
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 500 series turbofan engines of the same type
design. This AD requires initial and repetitive borescope inspections
of the HP-IP turbine bearing oil vent tubes and bearing chambers for
coking and carbon buildup; and replacement of the tubes if necessary.
We are issuing this AD to prevent internal oil fires from coking
and carbon buildup that could cause uncontained engine failure and
damage to the
[[Page 6674]]
airplane. You must use the service information described previously to
perform the actions required by this AD.
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. A situation exists that allows the immediate adoption
of this regulation.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. FAA-2005-23279;
Directorate Identifier 2005-NE-44-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
dms.dot.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 DMS Web
site, anyone can find and read the comments in any of our dockets,
including 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) or you may visit
https://dms.dot.gov.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.
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 have 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 that the regulation:
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 summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. FAA-2005-23279; Directorate Identifier 2005-NE-44-AD''
in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Under the authority delegated to me by the Administrator, the Federal
Aviation Administration amends part 39 of the Federal Aviation
Regulations (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 airworthiness
directive:
2006-03-14 Rolls-Royce plc: Amendment 39-14478. Docket No. FAA-2005-
23279; Directorate Identifier 2005-NE-44-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective February
24, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 553-61,
553A2-61, 556B-61, 556A2-61, 556-61, 556B2-61, 560-61, and 560A2-61
turbofan engines. These engines are installed on, but not limited
to, Airbus A340-500 and A340-600 series airplanes.
Unsafe Condition
(d) This AD results from a report of an RB211 Trent 700 series
engine that experienced a disk shaft separation, overspeed of the IP
turbine rotor, and multiple blade release of IP turbine blades. We
are issuing this AD to prevent internal oil fires caused by coking
and carbon buildup, that could result in uncontained engine failure
and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Initial Inspection
(f) Using section 3, Parts A and B of the Accomplishment
Instructions of RR Alert Service Bulletin (ASB) RB.211-72-AE836,
Revision 1, dated October 5, 2005, perform an initial inspection of
the high pressure-and-intermediate-pressure (HP-IP) turbine bearing
oil vent tubes and bearing chambers as follows:
(1) For IP Turbine modules (05 modules) with 9,600 hours time-
since-new (TSN) or 1,200 cycles-since-new (CSN) or more on the
effective date of this AD, carry out the inspection within 2,400
hours time-in-service (TIS) or 300 cycles-in-service (CIS) from the
effective date of this AD, whichever occurs first.
(2) For 05 modules that are below 9,600 hours TSN or 1,200 CSN
on the effective date of this AD, carry out the inspection prior to
12,000 hours TSN or 1,500 CSN, whichever occurs first,.
Repetitive Inspections
(g) Repeat the inspection at intervals not to exceed 12,000
hours time-since-previous-inspection (TSPI) or 1,500 cycles-since-
previous-inspection (CSPI), whichever occurs first, if at the
previous inspection, any of the following conditions were observed:
(1) There was no carbon buildup of a visible thickness.
(2) The cleaning tool, HU82105, could pass along the full length
of the internal vent tube into the bearing chamber.
[[Page 6675]]
(3) The 8 mm diameter borescope could pass along the full length
of the internal vent tube into the bearing chamber.
(h) Repeat the inspection at intervals not to exceed 1,600 hours
TSPI or 400 CSPI, whichever occurs first, if, at the previous
inspection, the carbon restriction prevented the 8 mm diameter
flexible borescope from passing through the internal vent tube, but
the 6 mm diameter borescope could pass along the full length of the
internal vent tube into the bearing chamber.
(i) Remove the engine within 10 CSPI, if the carbon restriction
prevented the 6 mm diameter borescope from passing through the full
length of the internal vent tubes.
05 Modules in the Shop
(j) For 05 modules in the shop on the effective date of this AD,
inspect the vent tube for carbon buildup of a visible thickness and
repair the vent tube as necessary prior to further flight.
Information regarding the inspection and repair of vent tubes for 05
modules in the shop can be found in section B. of RR ASB RB.211-72-
AE836, Revision 1, dated October 5, 2005.
Alternative Methods of Compliance
(k) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Related Information
(l) United Kingdom Civil Aviation Authority airworthiness
directive G-2005-0029, dated October 4, 2005, also addresses the
subject of this AD.
Material Incorporated by Reference
(m) You must use Rolls-Royce plc Alert Service Bulletin RB.211-
72-AE836, Revision 1, dated October 5, 2005, to perform the
inspections required by this AD. The Director of the Federal
Register approved the incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Rolls-Royce plc, Technical Publications, P.O. Box 31, Derby,
DE24 8BJ, UK; telephone: 011-44-1332-242424; fax: 011-44-1332-
249936, for a copy of this service information. You may review
copies at the Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-
401, Washington, DC 20590-0001, on the internet at https://
dms.dot.gov; 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.
Issued in Burlington, Massachusetts, on February 1, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 06-1145 Filed 2-8-06; 8:45 am]
BILLING CODE 4910-13-P
