[Federal Register Volume 75, Number 66 (Wednesday, April 7, 2010)]
[Proposed Rules]
[Pages 17630-17632]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-7830]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0364; Directorate Identifier 2009-NE-27-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Trent 700 and
Trent 800 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed 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: In completing a review of Engine Manual repair/acceptance
limits for titanium compressor shafts, Rolls-Royce has found the
specified limits to be incorrect such that the shot peened surface
layer at life critical features (the axial dovetail slots) may have
been inadvertently removed in-service. Removal of the shot peened layer
results in increased vulnerability of the part to tensile stresses,
which could reduce the life of the shaft to below the published life
limits.
We are proposing this AD to prevent failure of the intermediate-
pressure (IP) and high-pressure (HP) shaft, which could result in an
overspeed condition, possible uncontained disc failure and damage to
the airplane.
DATES: We must receive comments on this proposed AD by May 24, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: 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.
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 proposed 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 and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; 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-2010-0364;
Directorate Identifier 2009-NE-27-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.).
[[Page 17631]]
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78).
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2009-0021 (Corrected February 9, 2009), dated
February 6, 2009 (referred to after this as ``the MCAI''), to correct
an unsafe condition for the specified products. The MCAI states:
In completing a review of Engine Manual repair/acceptance limits
for titanium compressor shafts, Rolls-Royce has found the specified
limits to be incorrect such that the shot peened surface layer at
life critical features (the axial dovetail slots) may have been
inadvertently removed in-service. Removal of the shot peened layer
results in increased vulnerability of the part to tensile stresses,
which could reduce the life of the shaft to below the published life
limits. The acceptable limits for material loss on these surfaces
have now been corrected in the Engine Manual.
This AD identifies shafts for which such dressing operations
have been known to have been carried out and requires that an
inspection for compliance with the corrected Engine Manual limits be
accomplished and that the shafts be dispositioned accordingly.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Rolls-Royce plc has issued Alert Service Bulletin RB.211-72-AG086,
dated December 4, 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 Proposed AD
This product has been approved by the aviation authority of the
United Kingdom, and is approved for operation in the United States.
Pursuant to our bilateral agreement with the United Kingdom, they have
notified us of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all information provided by EASA and determined the unsafe
condition exists and is likely to exist or develop on other products of
the same type design.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 12 products of U.S. registry. We also estimate that
it would take about 8 work-hours per product to comply with this
proposed AD. The average labor rate is $85 per work-hour. Required
parts would cost about $15,000 per product. Based on these figures, we
estimate the cost of the proposed AD on U.S. operators to be $188,160.
Our cost estimate is exclusive of possible warranty coverage.
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 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 this proposed
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 regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
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 FAA 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 adding the following new AD:
Rolls-Royce plc: Docket No. FAA-2010-0364; Directorate Identifier
2009-NE-27-AD.
Comments Due Date
(a) We must receive comments by May 24, 2010.
Affected Airworthiness Directives (ADs)
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc model (RR) RB211 Trent
768-60, 772-60, 772B-60, 875-17, 877-17, 884-17, 884B-17, 892-17,
892B-17, and 895-17 turbofan engines that have a compressor shaft
listed by part number and serial number in Table 1 of this AD. These
engines are installed on, but not limited to, Airbus A330 series and
Boeing 777 series airplanes.
Reason
(d) This AD results from a review of engine manual repair/
acceptance limits for titanium compressor shafts by RR. We are
issuing this AD to prevent failure of the intermediate-pressure (IP)
and high-pressure (HP) shaft, which could result in an overspeed
condition, possible uncontained disc failure and damage to the
airplane.
Actions and Compliance
(e) Unless already done, do the following actions.
(1) Perform a one-time, piece-part, full-focused inspection of
the IP and HP compressor shafts listed by part number and serial
number in Table 1 of this AD before exceeding the compliance period
specified in Table 1 of this AD.
(2) Guidance on full-focused inspections and acceptance limits
can be found in the current, applicable RR engine manual.
[[Page 17632]]
Table 1--List of Affected Shafts
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Compliance
period
(flight cycles
Engine series Affected component Part No. Shaft serial No. in service
after December
4, 2008.)
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Trent 800........................ 1-8 IP Compressor FK24100............ MW0115238.......... 750
Shaft.
Trent 800........................ 1-4 HP Compressor FK32580............ MW0115512.......... 750
Shaft.
Trent 800........................ 1-4 HP Compressor FK32580............ MW0004708.......... 2000
Shaft.
Trent 800........................ 1-4 HP Compressor FK32580............ MW00063868......... 2500
Shaft.
Trent 800........................ 1-8 IP Compressor FK24100............ DN65507............ 2500
Shaft.
Trent 800........................ 1-8 IP Compressor FK24100............ DN65158............ 2500
Shaft.
Trent 800........................ 1-4 HP Compressor FK32580............ MW0125467.......... 3500
Shaft.
Trent 800........................ 1-4 HP Compressor FW11590............ DN65189............ 3500
Shaft.
Trent 800........................ 1-8 IP Compressor FK24100............ MW0091518.......... 3500
Shaft.
Trent 800........................ 1-8 IP Compressor FK24100............ MW0126365.......... 3500
Shaft.
Trent 800........................ 1-8 IP Compressor FK24100............ DN66422............ 4750
Shaft.
Trent 800........................ 1-8 IP Compressor FK24100............ MW0203314.......... 4750
Shaft.
Trent 700........................ 1-8 IP Compressor FK22279............ DN63228............ 3250
Shaft.
Trent 700........................ 1-8 IP Compressor FK26048............ MW0026046.......... 4500
Shaft.
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Other FAA AD Provisions
(f) 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
(g) Refer to MCAI EASA Airworthiness Directive 2009-0021
(Corrected 09 February, 2009), dated February 6, 2009, for related
information.
(h) Contact James Lawrence, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on March 31, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-7830 Filed 4-6-10; 8:45 am]
BILLING CODE 4910-13-P