Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG (RRD) Models Tay 650-15 and Tay 651-54 Turbofan Engines, 24825-24828 [2010-10739]
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Federal Register / Vol. 75, No. 87 / Thursday, May 6, 2010 / Proposed Rules
these standards can also be found in
section 1.4 of the framework document.
In addition, Section 136(c)(4)(A) of
EPACT 2005 amended EPCA to mandate
that DOE set standards for the following
additional categories of commercial
refrigeration equipment: Ice-cream
freezers; self-contained commercial
refrigerators, freezers, and refrigeratorfreezers without doors; and remote
condensing commercial refrigerators,
freezers, and refrigerator-freezers
(42 U.S.C. 6313(c)(4)(A)). DOE
undertook a rulemaking process
beginning in April 2006, when it
published a Rulemaking Framework for
Commercial Refrigeration Equipment
Including Ice-Cream Freezers; SelfContained Commercial Refrigerators,
Freezers, and Refrigerator-Freezers
without doors; and Remote Condensing
Commercial Refrigerators, Freezers, and
Refrigerator-Freezers. The final rule was
published on January 9, 2009. (74 FR
1091).
The EPACT 2005 amendments to
EPCA also require DOE to conduct two
cycles of rulemakings to determine
whether to amend the standards for
commercial refrigeration, both those
prescribed by EPACT 2005 and those
prescribed by DOE. (42 U.S.C.
6313(c)(5)(A)–(B)). In the first cycle, the
subject of this rulemaking, DOE must
publish a final rule establishing such
amended standards by January 1, 2013
if DOE determines to amend the
standards. (42 U.S.C. 6313(c)(5)(A)).
Any amended standards adopted by
DOE would apply to products
manufactured three years or more after
the date of publication, except that if
DOE decides that a three-year period is
inadequate, it shall provide a longer
period not to exceed five years. (42
U.S.C. 6313(c)(5)(C)). This framework
document is being published as a first
step in meeting these statutory
requirements.
DOE also considered standby and off
mode for commercial refrigeration
equipment and does not currently
believe that these modes of operation
are applicable to this equipment. As
described in more detail in the
framework document, commercial
refrigeration equipment generally
operates continuously. DOE plans,
however, to examine the issue and
address standby and off mode energy
use in the analyses conducted over the
course of the energy conservation
standards rulemaking.
To initiate this rulemaking cycle for
the consideration of amended energy
conservation standards for commercial
refrigeration equipment, DOE has
prepared a framework document to
explain the relevant issues, analyses,
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and processes it anticipates using to
determine whether to amend the
standards, and, if so, for the
development of such amended
standards. The focus of the public
meeting noted above will be to discuss
the analyses presented and issues
identified in the framework document.
At the public meeting, DOE will make
a number of presentations, invite
discussion on the rulemaking process as
it applies to commercial refrigeration
equipment, and solicit comments, data,
and information from participants and
other interested parties.
DOE is planning to conduct in-depth
technical analyses in the following
areas: (1) Engineering; (2) energy-use
characterization; (3) product price; (4)
life-cycle cost (LCC) and payback period
(PBP); (5) national impacts analysis
(NIA); (6) manufacturer impact analysis;
(7) utility impact analysis; (8)
employment impact analysis; (9)
environmental assessment; and (10)
regulatory impact analysis. DOE will
also conduct several other analyses that
support those previously listed,
including the market and technology
assessment, the screening analysis
(which contributes to the engineering
analysis), and the shipments analysis
(which contributes to the national
impact analysis).
DOE encourages those who wish to
participate in the public meeting to
obtain the framework document and to
be prepared to discuss its contents. A
copy of the draft framework document
is available at: https://
www1.eere.energy.gov/buildings/
appliance_standards/commercial/
refrigeration_equipment.html.
Public meeting participants need not
limit their comments to the issues
identified in the framework document.
DOE is also interested in comments on
other relevant issues that participants
believe would affect energy
conservation standards for this
equipment, applicable test procedures,
or the preliminary determination on the
scope of coverage. DOE invites all
interested parties, whether or not they
participate in the public meeting, to
submit in writing by June 7, 2010,
comments and information on matters
addressed in the framework document
and on other matters relevant to DOE’s
consideration of amended standards for
commercial refrigeration equipment.
The public meeting will be conducted
in an informal, facilitated, conference
style. There shall be no discussion of
proprietary information, costs or prices,
market shares, or other commercial
matters regulated by U.S. antitrust laws.
A court reporter will record the
proceedings of the public meeting, after
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24825
which a transcript will be available for
purchase from the court reporter and
placed on the DOE Web site at: https://
www.eere.energy.gov/buildings/
appliance_standards/commercial/
refrigeration_equipment.html.
After the public meeting and the close
of the comment period on the
framework document, DOE will begin
collecting data, conducting the analyses
as discussed in the framework
document and at the public meeting,
and reviewing the public comments it
receives.
DOE considers public participation to
be a very important part of the process
for determining whether to amend
energy conservation standards, and if
so, in setting those amended standards.
DOE actively encourages the
participation and interaction of the
public during the comment period in
each stage of the rulemaking process.
Beginning with the framework
document, and during each subsequent
public meeting and comment period,
interactions with and between members
of the public provide a balanced
discussion of the issues to assist DOE in
the standards rulemaking process.
Accordingly, anyone who wishes to
participate in the public meeting,
receive meeting materials, or be added
to the DOE mailing list to receive future
notices and information about this
rulemaking should contact Ms. Brenda
Edwards at (202) 586–2945, or via email at Brenda.Edwards@ee.doe.gov.
Issued in Washington, DC, on April 30,
2010.
Cathy Zoi,
Assistant Secretary, Energy Efficiency and
Renewable Energy.
[FR Doc. 2010–10655 Filed 5–5–10; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0037; Directorate
Identifier 2007–NE–41–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Deutschland Ltd. & Co. KG (RRD)
Models Tay 650–15 and Tay 651–54
Turbofan Engines
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to supersede an
existing airworthiness directive (AD) for
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Tay 650–15 turbofan engines. That AD
currently requires initial and repetitive
inspections of the low-pressure (LP)
turbine discs stage 2 and stage 3 for
corrosion, on certain Tay 650–15 serial
number engines. 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: Strip results from some of
the engines listed in the applicability
section of this AD revealed excessively
corroded low-pressure turbine disks
stage 2 and stage 3. The corrosion is
considered to be caused by the
environment in which these engines are
operated. Following a life assessment
based on the strip findings it is
concluded that inspections for corrosion
attack are required. The action specified
by this European Aviation Safety
Agency (EASA) AD 2008–0122 was
intended to avoid a failure of a lowpressure turbine disk stage 2 or stage 3
due to potential corrosion problems
which could result in uncontained
engine failure and damage to the
airplane. It has been later realized that
the same unsafe condition could
potentially occur on more serial
numbers for the Tay 650–15 engines and
on the Tay 651–54 engines. This AD,
superseding EASA AD 2008–0122,
retaining its requirements, is therefore
issued to expand the Applicability in
adding further engine serial numbers for
the Tay 650–15 engines and in adding
the Tay 651–54 engines.
We are proposing this AD to detect
corrosion that could cause the stage 2 or
stage 3 disk of the LP turbine to fail and
result in an uncontained failure of the
engine.
DATES: We must receive comments on
this proposed AD by June 21, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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 Deutschland Ltd
& Co KG, Eschenweg 11, Dahlwitz,
15827 Blankenfelde-Mahlow, Germany;
phone: 011 49 (0) 33–7086–1883; fax:
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011 49 (0) 33–7086–3276, for the service
information identified in this proposed
AD.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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: Tara
Chaidez, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
e-mail: tara.chaidez@faa.gov; phone:
(781) 238–7773; 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–2007–0037; Directorate Identifier
2007–NE–41–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 https://
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
On October 8, 2009, the FAA issued
AD 2009–22–01 (Amendment 39–16052
(74 FR 55121, October 27, 2009), which
superseded AD 2008–10–14
(Amendment 39–15521, 73 FR 29405,
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May 21, 2008). AD 2009–22–01 requires
initial and repetitive inspections of the
LP turbine discs stage 2 and stage 3 for
corrosion on 79 engines by serial
number. That AD was the result of
MCAI issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. That condition, if not
corrected, could result in the stage 2 or
stage 3 disk of the LP turbine to fail and
result in an uncontained failure of the
engine.
Since AD 2009–22–01 was issued,
RRD identified 14 additional Tay 650–
15 engines by serial number that require
the same inspections. RRD also
expanded the applicability to all Tay
651–54 engines. EASA, which is the
Technical Agent for the Member States
of the European Community, has issued
EASA AD 2010–0060R1, dated April 14,
2010. That MCAI extends the
applicability to include the 14
additional Tay 650–15 engine serial
numbers and Tay 651–54 engines for
inspections. You may obtain further
information by examining the MCAI in
the AD docket.
Relevant Service Information
Rolls-Royce Deutschland has issued
Alert Service Bulletin No. TAY–72–
A1524, Revision 3, dated March 24,
2010. 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
These products have been approved
by the United Kingdom (UK), and are
approved for operation in the United
States. Pursuant to our bilateral
agreement with the UK, they have
notified us of the unsafe condition
described in the MCAI ADs, and service
information referenced above. We are
proposing this AD because we evaluated
all pertinent information and
determined an unsafe condition exists
and is likely to exist or develop on other
products of the same type design. This
proposed AD would require initial and
repetitive eddy current inspections of
HP turbine discs.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about three Tay 651–54 engines
installed on airplanes of U.S. registry.
We also estimate that it would take
about three work-hours per engine to
comply with this proposed AD. The
average labor rate is $85 per work-hour.
Required parts would cost about
$40,000 per engine. Based on these
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figures, we estimate the cost of the
proposed AD on U.S. operators to be
$120,765.
PART 39—AIRWORTHINESS
DIRECTIVES
Authority for This Rulemaking
1. The authority citation for part 39
continues to read as follows:
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.
§ 39.13
Rolls-Royce Deutschland Ltd & Co KG (RRD)
(formerly Rolls-Royce plc, Derby,
England): Docket No. FAA–2007–0037;
Directorate Identifier 2007–NE–41–AD.
Comments Due Date
(a) We must receive comments by June 21,
2010.
Affected Airworthiness Directives (ADs)
Affected ADs
(b) This AD supersedes AD 2009–22–01,
Amendment 39–16052.
Applicability
(c) This AD applies to:
(1) RRD model Tay 650–15 turbofan
engines that have a serial number listed in
Table 1, Table 2, or Table 3 of this AD;
(2) All model Tay 651–54 turbofan engines;
and
(3) Engines with a low-pressure (LP)
turbine module M05300AA installed.
These engines are installed on, but not
limited to, Fokker F.28 Mark 0070 and 0100
airplanes, Boeing 727 airplanes modified in
accordance with Supplemental Type
Certificate No. SA8472SW, and Gulfstream
G–IV airplanes.
TABLE 1—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (CARRIED
FORWARD FROM AD 2008–10–14
AND AD 2009–22–01)
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The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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17358
17370
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17433
17438
17445
17446
17460
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17478
17490
17491
17517
17518
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
16:10 May 05, 2010
Engine serial number
Authority: 49 U.S.C. 106(g), 40113, 44701.
List of Subjects in 14 CFR Part 39
VerDate Mar<15>2010
TABLE 2—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (CARRIED
FORWARD FROM AD 2009–22–01)
PO 00000
Engine serial number
17251
17255
17256
17273
17275
17280
17281
17282
17300
17301
17327
17332
17365
17393
17437
17443
17470
17520
17521
17523
17539
17542
17556
Frm 00004
17561
17562
17563
17580
17581
17612
17618
17635
17637
17645
17661
17686
17699
17701
17702
17736
17737
17738
17739
17741
17742
17808
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Sfmt 4702
17522
17534
17535
17536
17538
17540
17541
17552
17553
17585
17613
17723
17724
17740
17759
17760
17807
TABLE 3—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (ADDED
NEW IN THIS AD)
Engine serial number
17344
17360
17376
17413
17537
17694
17698
17707
17716
17718
17719
17731
17756
17757
Reason
(d) Strip results from some of the engines
listed in the applicability section of this AD
revealed excessively corroded low-pressure
turbine disks stage 2 and stage 3. The
corrosion is considered to be caused by the
environment in which these engines are
operated. Following a life assessment based
on the strip findings it is concluded that
inspections for corrosion attack are required.
The action specified by this European
Aviation Safety Agency (EASA) AD 2008–
0122 was intended to avoid a failure of a lowpressure turbine disk stage 2 or stage 3 due
to potential corrosion problems which could
result in uncontained engine failure and
damage to the airplane. It has been later
realized that the same unsafe condition could
potentially occur on more serial numbers for
the Tay 650–15 engines and on the Tay 651–
54 engines. This AD, superseding EASA AD
2008–0122, retaining its requirements, is
therefore issued to expand the Applicability
in adding further engine serial numbers for
the Tay 650–15 engines and in adding the
Tay 651–54 engines. We are issuing this AD
to detect corrosion that could cause the stage
2 or stage 3 disk of the LP turbine to fail and
result in an uncontained failure of the
engine.
Actions and Compliance
(e) Unless already done, do the following
actions.
(1) Prior to accumulating 11,700 flight
cycles (FC) since new of disk life, and
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thereafter at intervals not exceeding 11,700
FC of disk life, inspect the LP turbine disks
stage 2 and stage 3 for corrosion using RRD
Alert Service Bulletin (ASB) No. TAY–72–
A1524, Revision 3, dated March 24, 2010.
(2) For engines with disk life that already
exceed 11,700 FC on the effective date of this
AD, perform the inspection within 90 days
after the effective date of this AD.
(3) When, during any of the inspections as
required by paragraphs (e)(1) and (e)(2) of
this AD, corrosion is found, replace the
affected parts. RRD TAY 650 Engine
Manual—E–TAY–3RR, Tasks 72–52–23–200–
000 and 72–52–24–200–000, and RRD TAY
651 Engine Manual—E–TAY–5RR, Tasks 72–
52–23–200–000 and 72–52–24–200–000,
contain guidance on performing the
inspection for corrosion and rejection
criteria.
Previous Credit
(f) Initial inspections done before the
effective date of this AD on LP turbine disks
stage 2 and stage 3 listed in Table 1 and
Table 2 of this AD using RRD ASB No. TAY–
72–A1524, Revision 1, dated September 1,
2006, or Revision 2, dated June 13, 2008,
comply with the initial inspection
requirements specified in this AD.
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 AD 2010–060R1, dated
April 14, 2010, for related information.
Contact Rolls-Royce Deutschland Ltd & Co
KG, Eschenweg 11, Dahlwitz, 15827
Blankenfelde-Mahlow, Germany; phone: 011
49 (0) 33–7086–1883; fax: 011 49 (0) 33–
7086–3276, for a copy of the service
information referenced in this AD.
(i) Contact Tara Chaidez, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: tara.chaidez@faa.gov; phone:
(781) 238–7773; fax (781) 238–7199, for more
information about this AD.
Issued in Burlington, Massachusetts, on
April 29, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
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[FR Doc. 2010–10739 Filed 5–5–10; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF ENERGY
Federal Energy Regulatory
Commission
18 CFR Part 37
[Docket No. RM10–22–000]
Promoting a Competitive Market for
Capacity Reassignments
April 29, 2010.
Federal Energy Regulatory
Commission.
ACTION: Notice of Proposed Rulemaking.
AGENCY:
SUMMARY: Based on the Commission’s
experience to date and a two-year study,
released April 15, 2010, the Federal
Energy Regulatory Commission
proposes in this Notice of Proposed
Rulemaking to lift the price cap for all
transmission customers reassigning
transmission capacity beyond October 1,
2010. The reforms proposed in this
order are intended to facilitate the
development of a market for capacity
reassignments as a competitive
alternative to primary capacity.
DATES: Comments are due July 6, 2010.
ADDRESSES: You may submit comments,
identified by docket number by any of
the following methods:
• Agency Web site: Documents
created electronically using word
processing software should be filed in
native applications or print-to-PDF
format and not in a scanned format.
• Mail/Hand Delivery: Commenters
unable to file comments electronically
must mail or hand deliver an original
and 14 copies of their comments to:
Federal Energy Regulatory Commission,
Office of the Secretary, 888 First Street,
NE., Washington, DC 20426.
Instructions: For detailed instructions
on submitting comments and additional
information on the rulemaking process,
see the Comment Procedures Section of
this document.
FOR FURTHER INFORMATION CONTACT:
Laurel Hyde (Technical Information),
Office of Energy Market Regulation,
Federal Energy Regulatory
Commission, 888 First Street, NE.,
Washington, DC 20426, (202) 502–
8146,
A. Cory Lankford (Legal Information),
Office of the General Counsel, Federal
Energy Regulatory Commission, 888
First Street, NE., Washington, DC
20426, (202) 502–6711.
SUPPLEMENTARY INFORMATION:
1. Based on the Commission’s
experience to date and a two-year study,
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released April 15, 2010,1 the Federal
Energy Regulatory Commission
(Commission) proposes in this Notice of
Proposed Rulemaking (NOPR) to lift the
price cap for all transmission customers
reassigning transmission capacity
beyond October 1, 2010. The reforms
proposed in this order are intended to
facilitate the development of a market
for capacity reassignments as a
competitive alternative to primary
capacity.
I. Background
2. In Order No. 888, the Commission
concluded that a transmission
provider’s pro forma Open Access
Transmission Tariff (OATT) must
explicitly permit the voluntary
reassignment of all or part of a holder’s
firm point-to-point capacity rights to
any eligible customer.2 The Commission
also found that allowing holders of firm
transmission capacity rights to reassign
capacity would help parties manage the
financial risks associated with their
long-term commitment, reduce the
market power of transmission providers
by enabling customers to compete, and
foster efficient capacity allocation.
3. With respect to the appropriate rate
for capacity reassignment, the
Commission concluded it could not
permit reassignments at market-based
rates because it was unable to determine
that the market for reassigned capacity
was sufficiently competitive so that
assignors would not be able to exert
market power. Instead, the Commission
capped the rate at the highest of (1) the
original transmission rate charged to the
purchaser (assignor), (2) the
transmission provider’s maximum
stated firm transmission rate in effect at
the time of the reassignment, or (3) the
assignor’s own opportunity costs
capped at the cost of expansion (price
cap). The Commission further explained
that opportunity cost pricing had been
permitted at ‘‘the higher of embedded
costs or legitimate and verifiable
opportunity costs, but not the sum of
the two (i.e., ‘or’ pricing is permitted;
1 FERC Staff, Staff Findings on Capacity
Reassignment (2010), available at: https://
www.ferc.gov (Staff Report).
2 Promoting Wholesale Competition Through
Open Access Non-Discriminatory Transmission
Services by Public Utilities; Recovery of Stranded
Costs by Public Utilities and Transmitting Utilities,
Order No. 888, 61 FR 21540 (May 10, 1996), FERC
Stats. & Regs. ¶ 31,036, at 31,696 (1996), order on
reh’g, Order No. 888–A, 62 FR 12274 (Mar. 14,
1997), FERC Stats. & Regs. ¶ 31,048 (1997), order
on reh’g, Order No. 888–B, 81 FERC ¶ 61,248
(1997), order on reh’g, Order No. 888–C, 82 FERC
¶ 61,046 (1998), aff’d in relevant part sub nom.
Transmission Access Policy Study Group v. FERC,
225 F.3d 667 (DC Cir. 2000), aff’d sub nom. New
York v. FERC, 535 U.S. 1 (2002).
E:\FR\FM\06MYP1.SGM
06MYP1
]]>Agencies
[Federal Register Volume 75, Number 87 (Thursday, May 6, 2010)]
[Proposed Rules]
[Pages 24825-24828]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-10739]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0037; Directorate Identifier 2007-NE-41-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG
(RRD) Models Tay 650-15 and Tay 651-54 Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede an existing airworthiness directive
(AD) for
[[Page 24826]]
Tay 650-15 turbofan engines. That AD currently requires initial and
repetitive inspections of the low-pressure (LP) turbine discs stage 2
and stage 3 for corrosion, on certain Tay 650-15 serial number engines.
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: Strip results from some of the
engines listed in the applicability section of this AD revealed
excessively corroded low-pressure turbine disks stage 2 and stage 3.
The corrosion is considered to be caused by the environment in which
these engines are operated. Following a life assessment based on the
strip findings it is concluded that inspections for corrosion attack
are required. The action specified by this European Aviation Safety
Agency (EASA) AD 2008-0122 was intended to avoid a failure of a low-
pressure turbine disk stage 2 or stage 3 due to potential corrosion
problems which could result in uncontained engine failure and damage to
the airplane. It has been later realized that the same unsafe condition
could potentially occur on more serial numbers for the Tay 650-15
engines and on the Tay 651-54 engines. This AD, superseding EASA AD
2008-0122, retaining its requirements, is therefore issued to expand
the Applicability in adding further engine serial numbers for the Tay
650-15 engines and in adding the Tay 651-54 engines.
We are proposing this AD to detect corrosion that could cause the
stage 2 or stage 3 disk of the LP turbine to fail and result in an
uncontained failure of the engine.
DATES: We must receive comments on this proposed AD by June 21, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://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 Deutschland Ltd & Co KG, Eschenweg 11,
Dahlwitz, 15827 Blankenfelde-Mahlow, Germany; phone: 011 49 (0) 33-
7086-1883; fax: 011 49 (0) 33-7086-3276, for the service information
identified in this proposed AD.
Examining the AD Docket
You may examine the AD docket on the Internet at https://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: Tara Chaidez, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
tara.chaidez@faa.gov; phone: (781) 238-7773; 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-2007-0037;
Directorate Identifier 2007-NE-41-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 https://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
On October 8, 2009, the FAA issued AD 2009-22-01 (Amendment 39-
16052 (74 FR 55121, October 27, 2009), which superseded AD 2008-10-14
(Amendment 39-15521, 73 FR 29405, May 21, 2008). AD 2009-22-01 requires
initial and repetitive inspections of the LP turbine discs stage 2 and
stage 3 for corrosion on 79 engines by serial number. That AD was the
result of MCAI issued by an aviation authority of another country to
identify and correct an unsafe condition on an aviation product. That
condition, if not corrected, could result in the stage 2 or stage 3
disk of the LP turbine to fail and result in an uncontained failure of
the engine.
Since AD 2009-22-01 was issued, RRD identified 14 additional Tay
650-15 engines by serial number that require the same inspections. RRD
also expanded the applicability to all Tay 651-54 engines. EASA, which
is the Technical Agent for the Member States of the European Community,
has issued EASA AD 2010-0060R1, dated April 14, 2010. That MCAI extends
the applicability to include the 14 additional Tay 650-15 engine serial
numbers and Tay 651-54 engines for inspections. You may obtain further
information by examining the MCAI in the AD docket.
Relevant Service Information
Rolls-Royce Deutschland has issued Alert Service Bulletin No. TAY-
72-A1524, Revision 3, dated March 24, 2010. 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
These products have been approved by the United Kingdom (UK), and
are approved for operation in the United States. Pursuant to our
bilateral agreement with the UK, they have notified us of the unsafe
condition described in the MCAI ADs, and service information referenced
above. We are proposing this AD because we evaluated all pertinent
information and determined an unsafe condition exists and is likely to
exist or develop on other products of the same type design. This
proposed AD would require initial and repetitive eddy current
inspections of HP turbine discs.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about three Tay 651-54 engines installed on airplanes of
U.S. registry. We also estimate that it would take about three work-
hours per engine to comply with this proposed AD. The average labor
rate is $85 per work-hour. Required parts would cost about $40,000 per
engine. Based on these
[[Page 24827]]
figures, we estimate the cost of the proposed AD on U.S. operators to
be $120,765.
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, Incorporation by
reference, 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 Deutschland Ltd & Co KG (RRD) (formerly Rolls-Royce plc,
Derby, England): Docket No. FAA-2007-0037; Directorate Identifier
2007-NE-41-AD.
Comments Due Date
(a) We must receive comments by June 21, 2010.
Affected Airworthiness Directives (ADs)
Affected ADs
(b) This AD supersedes AD 2009-22-01, Amendment 39-16052.
Applicability
(c) This AD applies to:
(1) RRD model Tay 650-15 turbofan engines that have a serial
number listed in Table 1, Table 2, or Table 3 of this AD;
(2) All model Tay 651-54 turbofan engines; and
(3) Engines with a low-pressure (LP) turbine module M05300AA
installed.
These engines are installed on, but not limited to, Fokker F.28 Mark
0070 and 0100 airplanes, Boeing 727 airplanes modified in accordance
with Supplemental Type Certificate No. SA8472SW, and Gulfstream G-IV
airplanes.
Table 1--Affected Tay 650-15 Engines by Serial Number (Carried Forward
From AD 2008-10-14 and AD 2009-22-01)
------------------------------------------------------------------------
------------------------------------------------------------------------
Engine serial number
------------------------------------------------------------------------
17251 17561
17255 17562
17256 17563
17273 17580
17275 17581
17280 17612
17281 17618
17282 17635
17300 17637
17301 17645
17327 17661
17332 17686
17365 17699
17393 17701
17437 17702
17443 17736
17470 17737
17520 17738
17521 17739
17523 17741
17539 17742
17542 17808
17556 ...................................
------------------------------------------------------------------------
Table 2--Affected Tay 650-15 Engines by Serial Number (Carried Forward
From AD 2009-22-01)
------------------------------------------------------------------------
------------------------------------------------------------------------
Engine serial number
------------------------------------------------------------------------
17249 17522
17303 17534
17358 17535
17370 17536
17425 17538
17426 17540
17433 17541
17438 17552
17445 17553
17446 17585
17460 17613
17474 17723
17478 17724
17490 17740
17491 17759
17517 17760
17518 17807
------------------------------------------------------------------------
Table 3--Affected Tay 650-15 Engines by Serial Number (Added New in This
AD)
------------------------------------------------------------------------
------------------------------------------------------------------------
Engine serial number
------------------------------------------------------------------------
17344 17707
17360 17716
17376 17718
17413 17719
17537 17731
17694 17756
17698 17757
------------------------------------------------------------------------
Reason
(d) Strip results from some of the engines listed in the
applicability section of this AD revealed excessively corroded low-
pressure turbine disks stage 2 and stage 3. The corrosion is
considered to be caused by the environment in which these engines
are operated. Following a life assessment based on the strip
findings it is concluded that inspections for corrosion attack are
required. The action specified by this European Aviation Safety
Agency (EASA) AD 2008-0122 was intended to avoid a failure of a low-
pressure turbine disk stage 2 or stage 3 due to potential corrosion
problems which could result in uncontained engine failure and damage
to the airplane. It has been later realized that the same unsafe
condition could potentially occur on more serial numbers for the Tay
650-15 engines and on the Tay 651-54 engines. This AD, superseding
EASA AD 2008-0122, retaining its requirements, is therefore issued
to expand the Applicability in adding further engine serial numbers
for the Tay 650-15 engines and in adding the Tay 651-54 engines. We
are issuing this AD to detect corrosion that could cause the stage 2
or stage 3 disk of the LP turbine to fail and result in an
uncontained failure of the engine.
Actions and Compliance
(e) Unless already done, do the following actions.
(1) Prior to accumulating 11,700 flight cycles (FC) since new of
disk life, and
[[Page 24828]]
thereafter at intervals not exceeding 11,700 FC of disk life,
inspect the LP turbine disks stage 2 and stage 3 for corrosion using
RRD Alert Service Bulletin (ASB) No. TAY-72-A1524, Revision 3, dated
March 24, 2010.
(2) For engines with disk life that already exceed 11,700 FC on
the effective date of this AD, perform the inspection within 90 days
after the effective date of this AD.
(3) When, during any of the inspections as required by
paragraphs (e)(1) and (e)(2) of this AD, corrosion is found, replace
the affected parts. RRD TAY 650 Engine Manual--E-TAY-3RR, Tasks 72-
52-23-200-000 and 72-52-24-200-000, and RRD TAY 651 Engine Manual--
E-TAY-5RR, Tasks 72-52-23-200-000 and 72-52-24-200-000, contain
guidance on performing the inspection for corrosion and rejection
criteria.
Previous Credit
(f) Initial inspections done before the effective date of this
AD on LP turbine disks stage 2 and stage 3 listed in Table 1 and
Table 2 of this AD using RRD ASB No. TAY-72-A1524, Revision 1, dated
September 1, 2006, or Revision 2, dated June 13, 2008, comply with
the initial inspection requirements specified in this AD.
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 AD 2010-060R1, dated April 14, 2010, for
related information. Contact Rolls-Royce Deutschland Ltd & Co KG,
Eschenweg 11, Dahlwitz, 15827 Blankenfelde-Mahlow, Germany; phone:
011 49 (0) 33-7086-1883; fax: 011 49 (0) 33-7086-3276, for a copy of
the service information referenced in this AD.
(i) Contact Tara Chaidez, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
tara.chaidez@faa.gov; phone: (781) 238-7773; fax (781) 238-7199, for
more information about this AD.
Issued in Burlington, Massachusetts, on April 29, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-10739 Filed 5-5-10; 8:45 am]
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