[Federal Register Volume 75, Number 162 (Monday, August 23, 2010)]
[Rules and Regulations]
[Pages 51651-51654]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-20657]
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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;
Amendment 39-16404; AD 2010-17-12]
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: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for the products listed above. This 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.
[[Page 51652]]
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.
DATES: This AD becomes effective September 27, 2010. The Director of
the Federal Register approved the incorporation by reference of certain
publications listed in this AD as of September 27, 2010.
ADDRESSES: The Docket Operations office is located at Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue,
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; phone: (781) 238-7758; fax: (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA proposed to amend 14 CFR part 39 by superseding AD 2009-22-
01, Amendment 39-16052 (74 FR 55121, October 27, 2009), with a proposed
AD. The proposed AD applies to RRD Models Tay 650-15 and Tay 651-54
turbofan engines. We published the proposed AD in the Federal Register
on May 6, 2010 (75 FR 24825). That action proposed to correct an unsafe
condition for the specified products. The MCAI states:
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.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
Request to Reference the Current EASA Type Certificate Approval
One commenter, RRD, requests that we revise the AD to reference the
current EASA type certificate approval rather than the original United
Kingdom type certificate approval.
We agree that the current type certificate approval is from EASA,
but since we do not repeat the preamble section of the proposed AD that
references this information, we did not change the AD. We will
reference the correct information in future AD actions.
Request To Correct a Typographical Error
RRD requests that we correct a typographical error under FAA's
Determination and Requirements of this Proposed AD. Specifically,
change ``HP'' to ``LP''.
We agree that ``HP'' should be ``LP''. However, that paragraph is
not repeated in the Final Rule. We did not change the AD.
Request To Remove Gulfstream G-IV Airplane From the Applicability
RRD requests that we delete the Gulfstream G-IV airplane from the
applicability, as the Tay 650-15 and Tay 651-54 turbofan engines are
not installed on that airplane.
We agree and removed that airplane from the applicability.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Costs of Compliance
Based on the service information, we estimate that this AD will
affect about three Tay 651-54 engines installed on airplanes of U.S.
registry. We also estimate that it will take about three work-hours per
engine to comply with this AD. The average labor rate is $85 per work-
hour. Required parts will cost about $40,000 per engine. Based on these
figures, we estimate the cost of the 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 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
responsibilities among the various levels of government.
For the reasons discussed above, I certify this 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. 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 AD and placed it in the AD docket.
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 (phone (800) 647-5527) is provided in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
[[Page 51653]]
the FAA amends 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 FAA amends Sec. 39.13 by removing Amendment 39-16052 (74 FR
55121, October 27, 2009), and by adding a new airworthiness directive,
Amendment 39-16404, to read as follows:
2010-17-12 Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly
Rolls-Royce plc, Derby, England): Amendment 39-16404. Docket No.
FAA-2007-0037; Directorate Identifier 2007-NE-41-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective
September 27, 2010.
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, and Boeing 727 airplanes
modified in accordance with Supplemental Type Certificate No.
SA8472SW.
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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Engine Serial No.
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17251
17255
17256
17273
17275
17280
17281
17282
17300
17301
17327
17332
17365
17393
17437
17443
17470
17520
17521
17523
17539
17542
17556
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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Table 2--Affected Tay 650-15 Engines by Serial Number (Carried Forward
From AD 2009-22-01)
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Engine Serial No.
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17249
17303
17358
17370
17425
17426
17433
17438
17445
17446
17460
17474
17478
17490
17491
17517
17518
17522
17534
17535
17536
17538
17540
17541
17552
17553
17585
17613
17723
17724
17740
17759
17760
17807
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Table 3--Affected Tay 650-15 Engines by Serial Number (Added New in This
AD)
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Engine Serial No.
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17344
17360
17376
17413
17537
17694
17698
17707
17716
17718
17719
17731
17756
17757
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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 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
[[Page 51654]]
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 Mark Riley, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-mail: [email protected];
phone: (781) 238-7758; fax (781) 238-7199, for more information
about this AD.
Material Incorporated by Reference
(j) You must use RRD Alert Service Bulletin No. TAY-72-A1524,
Revision 3, dated March 24, 2010, to do the inspections required by
this AD.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, 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.
(3) You may review copies at the FAA, New England Region, 12 New
England Executive Park, Burlington, MA; or at the National Archives
and Records Administration (NARA). For information on the
availability of this material at NARA, call (202) 741-6030, or go
to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on August 6, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-20657 Filed 8-20-10; 8:45 am]
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