[Federal Register Volume 70, Number 238 (Tuesday, December 13, 2005)]
[Rules and Regulations]
[Pages 73576-73577]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-23834]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-38-AD; Amendment 39-14404; AD 2005-25-11]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series 
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 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 low pressure (LP) compressor fan blades, 
part number (P/N) FW18548 installed. That AD currently requires LP 
compressor fan blade replacement with new or previously reworked 
blades, or rework of the existing LP compressor fan blades. This ad 
requires the same actions but at reduced compliance times for certain 
airplane and engine rating combinations and certain maximum gross 
weight limits. This AD results from a number of new production LP 
compressor fan blades found with surfaces formed outside of design 
intent. We are issuing this AD to prevent possible multiple uncontained 
LP compressor fan blade failure, due to cracking in the blade root 
caused by increased stresses in the shear key slots.

DATES: This AD becomes effective January 17, 2006. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of January 17, 2006.

ADDRESSES: 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 AD.
    You may examine the AD docket at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA. You may examine the service information, at the FAA, 
New England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine And Propeller 
Directorate, 12 New England Executive Park; Burlington, MA 01803-5299; 
telephone (781) 238-7175; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39 
with a new AD, applicable to 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 LP compressor fan blades, P/N FW18548 
installed. We published the proposed AD in the Federal Register on May 
27, 2005 (70 FR 30653). That action proposed to require LP compressor 
fan blade replacement with new or previously reworked blades, or rework 
of the existing LP compressor fan blades, at reduced compliance times 
from the previous AD, for certain airplane and engine rating 
combinations and certain maximum gross weight limits.

Examining the AD Docket

    You may examine the AD Docket (including any comments and service 
information), by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. See ADDRESSES for the 
location.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We considered the one comment received. The 
commenter supports the proposal.

Conclusion

    We carefully reviewed the available data, including the comment 
received, and determined that air safety and the public interest 
require adopting the AD as proposed.

Costs of Compliance

    About 392 RR RB211 Trent 800 series turbofan engines of the 
affected design are in the worldwide fleet. About 106 engines installed 
on airplanes of U.S. registry will be affected by this AD. We estimate 
about 100 work hours per engine are needed to perform blade rework, and 
that the average labor rate is $65 per work hour. Based on these 
figures, we estimate the total cost of the AD to U.S. operators to be 
$689,000.

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 have determined 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2003-NE-38-AD'' in your request.

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 73577]]

the Federal Aviation Administration 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 39-13736 (69 FR 
44925, August 12, 2004) and by adding a new airworthiness directive, 
Amendment 39-14404, to read as follows:

2005-25-11 Rolls-Royce plc: Amendment 39-14404. Docket No. 2003-NE-
38-AD.

Effective Date

    (a) This AD becomes effective January 17, 2006.

Affected ADs

    (b) This AD supersedes AD 2004-15-02, Amendment 39-13736.

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 low pressure 
(LP) compressor fan blades, part number FW18548 installed. These 
engines are installed on, but not limited to, Boeing 777 series 
airplanes.

Unsafe Condition

    (d) This AD results from a number of new production LP 
compressor blades found with surfaces formed outside of design 
intent. We are issuing this AD to prevent possible multiple 
uncontained LP compressor fan blade failure, due to cracking in the 
blade root caused by increased stresses in the shear key slots.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Actions Required for LP Compressor Fan Blades

    (f) Replace LP compressor fan blades with new or previously 
reworked LP compressor blades before accumulating the specified 
cycles-since-new (CSN) in the following Table 1, or rework the 
existing blades as specified in paragraph (g) of this AD.

                        Table 1.--LP Compressor Fan Blade Replacement or Rework Schedule
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                                   Airplane  maximum                                       Replace or  rework LP
      Boeing 777 Series:         gross weight  (times       RB211 Trent Engine Model       compressor fan blades
                                     1,000 pounds)                                         before accumulating:
----------------------------------------------------------------------------------------------------------------
-300..........................  660, 632.5              -884, -892, -884B                 2,400 CSN.
-200..........................  656                     -892, -895                        2,400 CSN.
-200..........................  648                     -892, -892B                       3,200 CSN.
-200..........................  632.5                   -892B                             3,200 CSN.
-200..........................  632.5                   -892                              4,100 CSN.
-200..........................  555                     -884                              4,100 CSN.
-200..........................  545                     -877                              4,100 CSN.
-200..........................  535                     -875                              4,100 CSN.
-200..........................  506                     -875                              4,100 CSN.
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    (g) Rework LP compressor fan blades at or before accumulating 
the specified CSN in Table 1 of this AD. Follow paragraphs 3.B.(1) 
through 3.B.(22) of Accomplishment Instructions of RR service 
bulletin (SB) No. RB.211-72-E044, Revision 2, dated October 8, 2004, 
to do the blade rework.
    (h) For engines moved between configurations, calculate the 
cycles remaining using either of the following:
    (1) Subtract the total CSN from the most limiting 
configuration's limit from Table 1 of this AD; or
    (2) Calculate the cycles remaining using the following equation:
    [GRAPHIC] [TIFF OMITTED] TR13DE05.008
    
Where:

Xr = Cycles remaining in current configuration.
Lc = Cyclic limit of current configuration from Table 1 of this AD.
Xn = Cycles accumulated in configuration n.
Ln = Cyclic limit in configuration n from Table 1 of this AD.

    (i) Information on the source life of the cycle limits in Table 
1 of this AD can be found in RR Alert SB No. RB.211-72-AE055, 
Revision 3, dated May 28, 2004.

Alternative Methods of Compliance

    (j) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (k) You must use Rolls-Royce plc Service Bulletin No. RB.211-72-
E044, Revision 2, dated October 8, 2004, to perform the blade rework 
required by this AD. The Director of the Federal Register approved 
the incorporation by reference of this service bulletin in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a 
copy from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; 
telephone: 011-44-1332-242424; fax: 011-44-1332-245418. You can 
review a copy at the FAA, New England Region, Office of the Regional 
Counsel, 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.

Related Information

    (l) CAA airworthiness directive G-2004-030, dated December 23, 
2004, and RR Alert SB No. RB.211-72-AE055, Revision 4, dated 
December 9, 2004, pertain to the subject of this AD.

    Issued in Burlington, Massachusetts, on December 5, 2005.
Carlos Pestana,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-23834 Filed 12-12-05; 8:45 am]
BILLING CODE 4910-13-P