[Federal Register Volume 75, Number 191 (Monday, October 4, 2010)]
[Proposed Rules]
[Pages 61114-61116]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-24745]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 75, No. 191 / Monday, October 4, 2010 /
Proposed Rules
[[Page 61114]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1165; Directorate Identifier 2008-NE-38-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211-Trent 800 Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
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SUMMARY: This supplemental NPRM revises an earlier proposed
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:
During manufacture of high-pressure (HP) compressor stage 1
discs, a small number of parts have been rejected due to a machining
defect that was found during inspection. Analysis of the possibility
of less severe examples having been undetected and passed into
service has concluded that action is required to reduce the risk of
failure. It was therefore necessary to reduce the life limit.
The HP compressor stage 1 disc is part of the HP compressor stage 1-4
shaft, part number (P/N) FK32580. We are proposing this AD to prevent
failure of the HP compressor stage 1 disc, uncontained engine failure,
and damage to the airplane.
DATES: We must receive comments on this proposed AD by November 18,
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.
Contact Rolls-Royce plc, P.O. Box 31, Derby, England, DE248BJ;
telephone: 011-44-1332-242424; fax: 011-44-1332-245418 for the service
information identified in this proposed AD.
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 (phone (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:
[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-2008-1165;
Directorate Identifier 2008-NE-38-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).
Discussion
This supplemental NPRM revises an earlier proposed AD, for Rolls-
Royce plc RB211-Trent 800 series turbofan engines. That proposed AD
would have required removing HP compressor stage 1-4 shafts, P/N
FK32580, from service at reduced life limits based on part assessment
using either ``Multiple Flight Profile Monitoring'', or ``Heavy Flight
Profile'' calculations. That proposed AD resulted from MCAI issued by
an aviation authority of another country. This supplemental NPRM
revises the proposed AD to correct certain life limits for the Heavy
Flight Profile Parts. We are proposing this supplemental NPRM to
prevent failure of the HP compressor stage 1 disc, uncontained engine
failure, and damage to the airplane. The European Aviation Safety
Agency (EASA), which is the Technical Agent for the Member States of
the European Community, has issued MCAI AD 2010-0087, date May 5, 2010
(corrected, May 6, 2010), to correct an unsafe condition for the
specified products. The MCAI states:
During manufacture of high-pressure (HP) compressor stage 1
discs, a small number of parts have been rejected due to a machining
defect that was found during inspection. Analysis of the possibility
of less severe examples having been undetected and passed into
service has concluded that action is required to reduce the risk of
failure. It is therefore necessary to reduce the life limit.
Since we issued the original proposed AD on February 10, 2009 (74 FR
7563, February 18, 2009):
EASA issued AD 2010-0087, dated May 5, 2010, and AD 2010-
0087 (corrected May 6, 2010) to correct certain life limits for the
Heavy Flight Profile Parts.
[[Page 61115]]
EASA issued AD 2010-0087, dated May 5, 2010 (corrected May
6, 2010), which retains certain requirements of superseded EASA AD
2008-0099, and imposes more restrictive life limits in the Heavy Flight
Profile Parts.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We provided the public the opportunity to participate in the
development of the original proposed AD. We considered the comments
received.
NPRM Would Allow a Part To Go Beyond the Current Time Limits Manual
(TLM) Limit
One commenter, Delta Airlines through the Airline Transport
Association (ATA), states that the NPRM would require a 5,280 cycle
life limit established in the long term for shafts that are used in the
``Heavy Flight Profile''. In the draw down period from the initial
effective date, the NPRM would allow a shaft in the ``Heavy Flight
Profile'' category to remain in service for up to 7,480 flight cycles
in the worst case scenario. However, the existing TLM Section 05-10-01-
800-802, Subtask 05-10-01-860-169 (dated March 15, 2008) states that
the current declared life limit for HP compressor stage 1-4 shaft, P/N
FK32580, is only 6,850 flight cycles. The NPRM would allow a part to go
beyond the current TLM limit in the interim draw down period which
seems to contradict the intent of the NPRM.
We agree. We changed the supplemental NPRM to use the correct life
limit reduction.
Allow Later Approved Revisions of the Alert Service Bulletin (ASB) as
Acceptable for Compliance
One commenter, American Airlines through the ATA, states that
subsequent to the writing of the NPRM, Rolls-Royce plc published
Revision 2 of ASB No. RB.211-72-AF825. The commenter requests that the
AD should include language that allows later approved revisions of the
ASB as acceptable for compliance.
We partially agree. We agree that our ADs should be as current and
accurate as possible. We changed the AD to include the reference to ASB
Revision 3 in the related information paragraph.
We disagree that the NPRM, or this supplemental NPRM, require the
use of the ASB for compliance, or that we should permit an unknown
future revision be used for compliance. Since we do not know the
content of later documents like ASBs, we do not issue a regulation that
mandates compliance with the unknown. We did not change the proposed AD
to permit compliance to unknown future revisions.
Request To Change the Base-Lined Compliance Time in the AD
One commenter, Rolls-Royce plc, states that their SB compliance
time is base-lined from May 1, 2008. The FAA NPRM is understood to
permit the same cyclic draw down as the SB. However, the baseline date
for the applicable draw down would be the issue date of the FAA AD.
Rolls-Royce plc requests that we change the base-lined compliance time
in the proposed AD to the compliance base line in the RR SB.
We do not agree. We cannot pre-date the compliance times in the
proposed AD. We did not change the AD.
Differences Between This Proposed AD and the MCAI
We have reviewed the MCAI and, in general, agree with its
substance. But we have found it necessary to not incorporate the June
4, 2008 compliance date which is in EASA AD 2010-0087, dated May 5,
2010 (corrected May 6, 2010). We updated the compliance times in the
proposed AD based on a more recent assessment of the unsafe condition.
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. This proposed AD requires removing HP compressor
stage 1-4 shafts, P/N FK32580, from service at reduced life limits
based on part assessment using either ``Multiple Flight Profile
Monitoring'', or ``Heavy Flight Profile'' calculations.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 78 products of U.S. registry. Required parts would
cost about $15,095 per product. We estimate that no additional labor
costs would be incurred to perform the proposed actions, as we
anticipate that the removal from service of the HP compressor stage 1-4
shafts will occur while the engine is inducted into the shop for
routine maintenance. Based on these figures, we estimate the cost of
the proposed AD on U.S. operators to be $1,177,410.
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:
[[Page 61116]]
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-2008-1165; Directorate Identifier
2008-NE-38-AD.
Comments Due Date
(a) We must receive comments by November 18, 2010.
Affected Airworthiness Directives (ADs)
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) models RB211-Trent
875-17, -Trent 877-17, -Trent 884-17, -Trent 884B-17, -Trent 892-17,
-Trent 892B-17, and -Trent 895-17 turbofan engines, with high-
pressure (HP) compressor stage 1-4 shafts, part number (P/N)
FK32580, installed. These engines are installed on, but not limited
to, Boeing 777 series airplanes.
Reason
(d) European Aviation Safety Agency (EASA) AD 2010-0087, dated
May 5, 2010 (corrected May 6, 2010) states the unsafe condition is
as follows:
During manufacture of high-pressure (HP) compressor stage 1
discs, a small number of parts have been rejected due to a machining
defect that was found during inspection. Analysis of the possibility
of less severe examples having been undetected and passed into
service has concluded that action is required to reduce the risk of
failure. It was therefore necessary to reduce the life limit.
The HP compressor stage 1 disc is part of the HP compressor stage 1-
4 shaft, P/N FK32580. We are issuing this AD to prevent failure of
the HP compressor stage 1 disc, uncontained engine failure, and
damage to the airplane.
Actions and Compliance
(e) Unless already done, do the following actions.
Multiple Flight Profile Monitoring Parts
(1) For RB211-Trent 800 engines being monitored by ``Multiple
Flight Profile Monitoring,'' remove the HP compressor stage 1-4
shaft, P/N FK32580, before accumulating 5,580 standard duty cycles
(SDC) since-new or within 960 SDC from the effective date of this
AD, whichever occurs later.
Heavy Flight Profile Parts
(2) For RB211-Trent 800 engines being monitored by ``Heavy
Flight Profile,'' remove the HP compressor stage 1-4 shaft, P/N
FK32580, before accumulating 5,280 flight cycles since new or within
860 flight cycles from the effective data of this AD, whichever
occurs later.
FAA Differences
(f) We have found it necessary to not incorporate the June 4,
2008 compliance date which is in EASA AD 2010-0087, dated May 5,
2010 (corrected May 6, 2010). We also updated the compliance times
in the AD based on a more recent assessment of the unsafe condition.
Alternative Methods of Compliance (AMOCs)
(g) 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 EASA Airworthiness Directive 2010-0087, dated May
5, 2010 (corrected May 6, 2010), and Rolls-Royce plc Alert Service
Bulletin No. RB.211-72-AF825, Revision 3, dated August 25, 2009 for
related information. Contact Rolls-Royce plc, P.O. Box 31, Derby,
England, DE248BJ; telephone: 011-44-1332-242424; fax: 011-44-1332-
245418, for a copy of this service information.
(i) Contact James Lawrence, Aerospace Engineer, Engine
Certification Office, FAA, Engine & 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 September 27, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-24745 Filed 10-1-10; 8:45 am]
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