[Federal Register: April 27, 2009 (Volume 74, Number 79)]
[Proposed Rules]
[Page 19025-19027]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27ap09-17]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-1369; Directorate Identifier 2003-NE-03-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for Rolls-Royce plc RB211 Trent 875-17, Trent 877-17,
Trent 884-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan
engines with high pressure (HP) compressor rotor rear stage 5 and 6
discs and cone shafts, part numbers (P/Ns) FK25230 and FK27899
installed. This proposed AD would require removing these parts at new
reduced cycle limits. This proposed AD results from Rolls-Royce plc
reducing the lives of these parts and changing the life calculating
method to use ``Standard Duty Cycles'' with ``Multiple Flight Profile
Monitoring'' and ``Flight Cycles'' with ``Heavy Flight Profile
Monitoring''. We are proposing this AD to prevent stage 5 and 6 disc
crack initiation and propagation that might lead to uncontained disc
failure and damage to the airplane.
DATES: We must receive any comments on this proposed AD by June 26,
2009.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, 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.
FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine and 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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-1369;
Directorate Identifier 2003-NE-03-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this proposed AD. Using the search
function of the Web site, anyone can find and read the comments in any
of our dockets, including, if provided, the name of the individual who
sent the comment (or signed the comment on behalf of an association,
business, labor union, etc.). You may review the DOT's complete Privacy
Act Statement in the Federal Register published on April 11, 2000 (65
FR 19477-78).
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.
Discussion
On July 23, 2003, we issued AD 2003-15-06, Amendment 39-13249 (68
FR 44610, July 30, 2003). That AD requires removal from service of HP
compressor rotor rear stage 5 and 6 discs and cone shafts, P/Ns FK25230
and FK27899, before reaching newly reduced life limits. The Civil
Aviation Authority (CAA), which is the airworthiness authority for the
United Kingdom (U.K.), had notified the FAA that an unsafe condition
may exist on Rolls-Royce plc RB211 Trent 875, Trent 877, Trent 884,
Trent 892, Trent 892B, and Trent 895 turbofan engines. The CAA advised
that three HP compressor rotor rear stage 5 and 6 discs and cone
shafts, P/Ns FK25230 and FK27899, were found with crack indications in
the stage 5 and 6 blade loading slots, during overhaul inspection. The
manufacturer's analysis had not yet been able to identify the root
cause of these cracks, or to fully explain the crack propagation rate.
As a result of the analysis, a new lower life limit of 7,500 cycles-
since-new had been assigned by the manufacturer to these HP compressor
rotor rear stage 5 and 6 discs and cone shafts. This condition, if not
corrected,
[[Page 19026]]
could result in stage 5 and 6 disc crack initiation and propagation
that might lead to uncontained disc failure and damage to the airplane.
Actions Since AD 2003-15-06 Was Issued
Since AD 2003-15-06 was issued, Rolls-Royce plc has further reduced
the lives of HP compressor rotor rear stage 5 and 6 discs and cone
shafts, P/Ns FK25230 and FK27899, and changed the life calculating
method to use ``Standard Duty Cycles'' with ``Multiple Flight Profile
Monitoring'' and ``Flight Cycles'' with ``Heavy Flight Profile
Monitoring''.
Bilateral Agreement Information
This engine model is manufactured in the United Kingdom and is 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 European Aviation Safety Agency (EASA)
kept us informed of the situation described above. We have examined the
findings of EASA, 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 the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would require
changing the life calculating method to use ``Standard Duty Cycles''
with ``Multiple Flight Profile Monitoring'' and ``Flight Cycles'' with
``Heavy Flight Profile Monitoring'', and reducing the lives of the
affected parts to 5,000 ``Standard Duty Cycles'' or 5,000 Flight
cycles'', respectively.
Costs of Compliance
We estimate that this proposed AD would affect 94 Rolls-Royce plc
RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 892-17, Trent
892B-17, and Trent 895-17 turbofan engines installed on airplanes of
U.S. registry. Removal of these HP compressor rotor rear stage 5 and 6
discs and cone shafts would not impose any additional labor costs if
performed at the time of scheduled engine overhaul. The prorated life
loss is about $225,000 per engine. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $21,150,000.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed 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. Would 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 proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Amendment 39-13249 (68 FR
44610, July 30, 2003) and by adding a new airworthiness directive, to
read as follows:
Rolls-Royce plc: Docket No. FAA-2009-1369; Directorate Identifier
2003-NE-03-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by June 26,
2009.
Affected ADs
(b) This AD supersedes AD 2003-15-06, Amendment 39-13249.
Applicability
(c) This AD applies to Rolls-Royce plc RB211 Trent 875-17, Trent
877-17, Trent 884-17, Trent 892-17, Trent 892B-17, and Trent 895-17
turbofan engines with high pressure (HP) compressor rotor rear stage
5 and 6 discs and cone shafts, part numbers (P/Ns) FK25230 and
FK27899 installed. These engines are installed on, but not limited
to, Boeing 777 series airplanes.
Unsafe Condition
(d) This AD results from Rolls-Royce plc reducing the lives of
these parts and changing the life calculating method to use
``Standard Duty Cycles'' with ``Multiple Flight Profile
Monitoring'', and ``Flight Cycles'' with ``Heavy Flight Profile
Monitoring''. We are issuing this AD to prevent stage 5 and 6 disc
crack initiation and propagation that might lead to uncontained disc
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.
(f) For operators using ``Multiple Flight Profile Monitoring''
(Flight Profiles ``A'' through ``F''), remove HP compressor rotor
rear stage 5 and 6 discs and cone shafts from service at or before
accumulating 5,000 ``Standard Duty Cycles''. Information on
``Multiple Flight Profile Monitoring'' can be found in the Aircraft
Maintenance Manual, Chapter 70-01-10.
(g) For operators using ``Heavy Flight Profile Monitoring'',
remove HP compressor rotor rear stage 5 and 6 discs and cone shafts
from service at or before accumulating 5,000 ``Flight Cycles''.
Information on ``Heavy Flight Profile Monitoring'' can be found in
the Aircraft Maintenance Manual, Chapter 70-01-10.
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.
[[Page 19027]]
Related Information
(i) Contact James Lawrence, Aerospace Engineer, Engine
Certification Office, FAA, Engine and 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.
(j) European Aviation Safety Agency AD 2007-0004, dated January
8, 2007, also addresses the subject of this AD.
(k) Rolls-Royce plc Alert Service Bulletin No. RB.211-72-AE082,
Revision 7, dated June 18, 2008, pertains to the subject of this AD.
Contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, UK, telephone
44 (0) 1332 242424; fax 44 (0) 1332 249936, for a copy of this
service information.
(l) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of the Aircraft Maintenance Manual
referenced in this AD.
Issued in Burlington, Massachusetts, on April 17, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E9-9479 Filed 4-24-09; 8:45 am]
BILLING CODE 4910-13-P