[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)
------------------------------------------------------------------------
                            Engine Serial No.
-------------------------------------------------------------------------
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)
------------------------------------------------------------------------
                            Engine Serial No.
-------------------------------------------------------------------------
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
------------------------------------------------------------------------


Table 3--Affected Tay 650-15 Engines by Serial Number (Added New in This
                                   AD)
------------------------------------------------------------------------
                            Engine Serial No.
-------------------------------------------------------------------------
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 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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