[Federal Register: November 8, 2004 (Volume 69, Number 215)]
[Rules and Regulations]
[Page 64653-64656]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08no04-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19559; Directorate Identifier 2004-NE-03-AD;
Amendment 39-13858; AD 2004-23-03]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Trent 700 Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Rolls-Royce plc (RR) RB211 Trent 700 series turbofan engines. This AD
requires initial and repetitive borescope inspections of the high
pressure-and-intermediate pressure (HP-IP) turbine internal and
external oil vent tubes for coking and carbon buildup, and cleaning or
replacing the vent tubes if necessary. This AD results from a report of
a RB211 Trent 700 series engine experiencing a disk shaft separation,
overspeed of the IP turbine rotor, and multiple blade release of IP
turbine blades. Preliminary findings suggest these events resulted from
an internal oil fire in the HP-IP turbine oil vent tubes due to coking
and carbon buildup. This fire led to a second fire in the internal air
cavity below the IP turbine disk drive shaft. We are issuing this AD to
prevent internal oil fires due to coking and carbon buildup, that could
cause uncontained engine failure and damage to the airplane.
DATES: Effective November 23, 2004. The Director of the Federal
Register approved the incorporation by reference of certain
publications listed in the regulations as of November 23, 2004.
We must receive any comments on this AD by January 7, 2005.
ADDRESSES: Use one of the following addresses to comment on this AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
[[Page 64654]]
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 20590-001.
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, PO Box 31, Derby, England; telephone: 011-
44-1332-249428; fax: 011-44-1332-249223 for the service information
referenced in this AD. You may examine the comments on this AD in the
AD docket on the Internet at http://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7178; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: As a member of the National Transportation
Safety Board (NTSB) investigation team, we are investigating an
incident event and possible unsafe condition on RR RB211 Trent 700
series engines. The Civil Aviation Authority (CAA), which is the
airworthiness authority for the United Kingdom (UK) is helping us
investigate. A report was received of a RB211 Trent 700 series engine
experiencing a disk shaft separation, overspeed of the IP turbine
rotor, and multiple blade release of IP turbine blades. Preliminary
findings suggest these events resulted from an internal oil fire in the
HP-IP turbine oil vent tubes due to coking and carbon buildup. This
fire led to a second fire in the internal air cavity below the IP
turbine disk drive shaft. Because the oil vent tubes on the event
engine were destroyed, the partner engine on the same airplane was
inspected. That inspection revealed heavy coking and carbon buildup,
with partial blockage of the HP-IP turbine oil vent tubes. Both engines
had the same on-wing life of 15,169 hours with 2,344 cycles-since-new.
Both engines contained Mobil Jet Oil 291, which also is suspect and
will be removed from the list of approved oils for these engines. The
NTSB investigation is ongoing and a finding of probable cause has not
yet been made. The fire, disk overspeed, and blade release appear to be
the result of the coking and carbon buildup, evident in the sister
engine and linked by cycles and oil use to the event engine.
Relevant Service Information
We have reviewed and approved the technical contents of RR Alert
Service Bulletin (ASB) No. RB.211-72-AE302, Revision 1, dated May 25,
2004, that describes procedures for:
Initial and repetitive borescope inspections for coking
and carbon buildup in the HP-IP turbine oil vent tubes; and
Cleaning the tubes if necessary, and removing the engine
from service to clean or replace the tubes.
This ASB requires that all operators submit inspection data to the
manufacturer. The CAA classified this ASB as mandatory and issued AD G-
2004-0016, dated June 20, 2004, in order to ensure the airworthiness of
these RB211 Trent 700 series engines in the UK.
Bilateral Airworthiness Agreement
These engine models are manufactured in the UK 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. As a member of the NTSB investigation team, we have
examined the findings with 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 RB211 Trent 700 series turbofan engines of the same type design.
We are issuing this AD to prevent internal oil fires due to coking and
carbon buildup, that could cause uncontained engine failure and damage
to the airplane. This AD requires:
Initial and repetitive borescope inspections of the HP-IP
turbine oil vent tubes for coking and carbon buildup; and
Cleaning or replacing the oil vent tubes if they fail the
inspection.
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.
Interim Action
These actions are interim actions and we may take further
rulemaking actions in the future.
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 submit any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. FAA-2004-19559;
Directorate Identifier 2004-NE-03-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 http://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
http://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 DMS Docket Offices
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.
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
[[Page 64655]]
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Under the authority delegated to me by the Administrator, the FAA
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2004-23-03 Rolls-Royce plc: Amendment 39-13858. Docket No. FAA-2004-
19559; Directorate Identifier 2004-NE-03-AD.
Effective Date
(a) This AD becomes effective November 23, 2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 768-60,
RB211 Trent 772-60, and RB211 Trent 772B-60 series turbofan engines.
These engines are installed on, but not limited to, Airbus A330-243,
-341, -342 and -343 series airplanes.
Unsafe Condition
(d) This AD results from a report of a RB211 Trent 700 series
engine experiencing a disk shaft separation, overspeed of the IP
turbine rotor, and multiple blade release of IP turbine blades.
Preliminary findings suggest these events resulted from an internal
oil fire in the HP-IP turbine oil vent tubes due to coking and
carbon buildup. This fire led to a second fire in the internal air
cavity below the IP turbine disk drive shaft. We are issuing this AD
to prevent internal oil fires due to coking and carbon buildup, that
could cause 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 Visual Inspection
(f) Using the inspection schedule in Table 1 of this AD, perform
an initial borescope inspection of the high pressure-and-
intermediate pressure (HP-IP) turbine internal and external oil vent
tubes for coking and carbon buildup as follows:
(1) Insert an 8 mm diameter flex borescope to see if it will
pass along the full length of the vent tube into the bearing
chamber.
(2) If the vent tube prevents an 8 mm diameter flex borescope
from passing along the full length of the tube into the bearing
chamber, repeat the action using a 6mm flex borescope.
(3) If the 6 mm diameter flex borescope passes through to the
bearing chamber, continue using the engine in service, and perform
the repetitive inspections in this AD at the required intervals.
(4) If the vent tube prevents the 6 mm diameter flex borescope
from passing along the full length of the tube into the bearing
chamber, clean or replace the vent tube. Information on oil vent
tube cleaning or replacement can be found in Rolls-Royce plc Alert
Service Bulletin No. RB.211-72-AE302, Revision 1, dated May 25,
2004.
Table 1.--Initial Inspection Schedule
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If the engine or the 05 module: Then initially inspect:
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Has reached 10,000 hours time-since- Within 3 months after the effective
new (TSN) or reached 2,500 cycles- date of this AD.
since-new (CSN) on the effective
date of this AD.
Has fewer than 10,000 hours TSN or Within 3 months after reaching
fewer than 2,500 CSN on the 10,000 hours TSN or 2,500 CSN,
effective date of this AD. whichever occurs first.
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Repetitive Visual Inspections
(g) Using the inspection schedule in Table 2 of this AD and
paragraphs (f)(1) through (f)(4) of this AD, perform repetitive
borescope inspections of the HP-IP turbine internal and external oil
vent tubes for coking and carbon buildup.
Table 2.--Repetitive Inspection Schedule
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If at the previous inspection,
before any cleaning was performed: Then:
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(1) There was no coking and carbon Reinspect within 6,400 hours time-
buildup of a visible thickness; or since-last-inspection (TSLI) or
an 8 mm diameter flex borescope within 1,600 cycles-since-last-
could pass along the full length inspection (CSLI), whichever
of the internal vent tube into the occurs first.
bearing chamber.
(2) The coking or carbon buildup Reinspect within 1,600 hours TSLI
prevented an 8 mm diameter flex or within 400 CSLI, whichever
borescope from passing through the occurs first.
internal vent tube, but a 6 mm
diameter flex borescope could pass
along the full length of the
internal vent tube into the
bearing chamber.
(3) The coking or carbon buildup Clean or replace the vent tubes
prevented the 6 mm diameter flex within 10 CSLI. Information on oil
borescope from passing through the vent tube cleaning or replacement
full length of the internal vent can be found in Rolls-Royce plc
tube and into the bearing chamber. Alert Service Bulletin No. RB.211-
72-AE302, Revision 1, dated May
25, 2004.
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Alternative Methods of Compliance
(h) 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.
Material Incorporated by Reference
(i) None.
[[Page 64656]]
Related Information
(j) CAA airworthiness directive No. G-2004-0016, dated June 20,
2004, also addresses the subject of this AD.
Issued in Burlington, Massachusetts, on November 1, 2004.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 04-24817 Filed 11-5-04; 8:45 am]
BILLING CODE 4910-13-P