[Federal Register Volume 70, Number 9 (Thursday, January 13, 2005)]
[Rules and Regulations]
[Pages 2333-2336]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-484]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-05-AD; Amendment 39-13941; AD 2005-01-16]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Trent 700 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Rolls-Royce plc (RR) RB211 Trent 768-60, Trent 772-60, and 
Trent 772B-60 turbofan engines with low pressure compressor (LPC) fan 
blade part numbers FK22580, FK23411, FK25441, and FK25968 installed. 
That AD currently requires initial ultrasonic inspections of the fan 
blade root with blades removed, repetitive ultrasonic inspections of 
the fan blade root with blades removed or installed, and ultrasonic 
inspection of the fan blade root to be done with the fan blades removed 
at least every third inspection. This AD requires the same inspections 
but at lower thresholds and intervals, and eliminates the requirement 
for ultrasonic inspection with the fan blades removed at least every 
third inspection. This AD results from analysis of flight data returned 
to RR, that shows a need for consistent inspection thresholds for all 
engine models. We are issuing this AD to prevent possible multiple LPC 
fan blade failures, which could result in an uncontained engine failure 
and damage to the airplane.

DATES: Effective January 28, 2005. The Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulations as of January 28, 2005.
    We must receive any comments on this AD by March 14, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     By mail: Federal Aviation Administration (FAA), New 
England Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 2000-NE-05-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
     By fax: (781) 238-7055.
     By e-mail: [email protected].
    You can get the service information referenced in this AD from 
Rolls-Royce

[[Page 2334]]

plc, PO Box 31, Derby, England; telephone: 011-44-1332-249428; fax: 
011-44-1332-249223.
    You may review copies 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/code_of_federal_regulations/ibr_locations.html. You may examine the AD docket 
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: On August 1, 2001, we issued AD 2001-16-05, 
Amendment 39-12373 (66 FR 42105, August 10, 2001). That AD requires 
initial ultrasonic inspections of the fan blade root with blades 
removed, repetitive ultrasonic inspections of the fan blade root with 
blades removed or installed, and ultrasonic inspections to be done with 
the fan blades removed at least every third inspection. That AD 
resulted from reports of fan blade failures due to dovetail root 
cracks. That condition, if not corrected, could result in possible 
multiple LPC fan blade failures, uncontained engine failure, and damage 
to the airplane.

Actions Since AD 2001-16-05 Was Issued

    Since that AD was issued, analysis of flight data returned to RR 
shows a need for consistent inspection thresholds for all engine 
models. The actions specified in this AD are intended to prevent 
possible multiple LPC fan blade failures, which could result in an 
uncontained engine failure and damage to the airplane.

Special Flight Permits Paragraph Removed

    Paragraph (g) of the current AD, AD 2001-16-05, contains a 
paragraph pertaining to special flight permits. Even though this final 
rule does not contain a similar paragraph, we have made no changes with 
regard to the use of special flight permits to operate the airplane to 
a repair facility to do the work required by this AD. In July 2002, we 
published a new Part 39 that contains a general authority regarding 
special flight permits and airworthiness directives; see Docket No. 
FAA-2004-8460, Amendment 39-9474 (69 FR 47998, July 22, 2002). Thus, 
when we now supersede ADs we will not include a specific paragraph on 
special flight permits unless we want to limit the use of that general 
authority granted in section 39.23.

Relevant Service Information

    We have reviewed and approved the technical contents of RR 
Mandatory Service Bulletin (MSB) No. RB.211-72-C878, Revision 7, dated 
December 5, 2003, that:
     Removes LPC fan blades and performs initial and repetitive 
ultrasonic inspections for cracks in LPC fan blade dovetail roots, at 
earlier initial thresholds than the inspections required by the current 
AD, and, at adjusted repetitive inspection intervals from the current 
AD.
     Provides a procedure that does not require blade removal 
from the engine in order to perform repetitive ultrasonic inspections 
for cracks in LPC fan blade dovetail roots.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the United Kingdom and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the Civil Aviation Authority (CAA) 
has kept the FAA informed of the situation described above. The FAA has 
examined the findings of the CAA, reviewed all available information, 
and determined that AD action is necessary for products of this type 
design that are certificated for operation in the United States.

FAA's Determination of an Unsafe Condition and Proposed Actions

    Although none of these affected engine models are used on any 
airplanes that are registered in the United States, the possibility 
exists that the engine models could be used on airplanes that are 
registered in the United States in the future. Since an unsafe 
condition has been identified that is likely to exist or develop on 
other RR RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan 
engine models of the same type design, this AD is being issued to 
prevent possible multiple LPC fan blade failures, which could result in 
an uncontained engine failure and damage to the airplane. This AD 
requires:
     Initial ultrasonic inspections of the fan blade root with 
blades removed; at or before accumulating 1,100 cycles-since-new (CSN) 
on the fan blades after the effective date of the AD; and
     For blades with more than 1,100 CSN that have not been 
previously inspected, initial ultrasonic inspections of the fan blade 
root with blades removed; within 300 cycles-in-service (CIS) from the 
effective date of the AD or within 2,000 CSN, whichever occurs first; 
and
     Repetitive ultrasonic inspections of the fan blade root, 
with blades removed within 300 CIS intervals, or with blades not 
removed within 250 CIS intervals.

    The actions are required to be done using the service bulletin 
described previously.

Immediate Adoption of This AD

    Since there are currently no domestic operators of these engine 
models, notice and opportunity for prior public comment are 
unnecessary. Therefore, a situation exists that allows the immediate 
adoption of this regulation.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2000-NE-05-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the rule 
that might suggest a need to modify it. If a person contacts us 
verbally, and that contact relates to a substantive part of this AD, we 
will summarize the contact and place the summary in the docket. We will 
consider all comments received by the closing date and may amend the AD 
in light of those comments.

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.

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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 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 that the 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 summary of the costs to satisfy the initial 
requirements of 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. 2000-NE-05-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, 
the FAA amends part 39 of the Federal Aviation Regulations (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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing Amendment 39-12373 (66 FR 42105, August 10, 2001), and by 
adding a new airworthiness directive (AD), Amendment 39-13941, to read 
as follows:

2005-01-16 Rolls-Royce plc: Amendment 39-13941. Docket No. 2000-NE-
05-AD. Supersedes AD 2001-16-05, Amendment 39-12373.

Effective Date

    (a) This AD becomes effective January 28, 2005.

Affected ADs

    (b) This AD supersedes AD 2001-16-05, Amendment 39-12373.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 768-60, 
Trent 772-60, and Trent 772B-60 turbofan engines with low pressure 
compressor (LPC) fan blade part numbers FK22580, FK23411, FK25441, 
and FK25968 installed. These engines are installed on, but not 
limited to, Airbus A330 series airplanes.

Unsafe Condition

    (d) This AD supersedure results from analysis of flight data 
returned to RR, that shows a need for consistent inspection 
thresholds for all engine models. We are issuing this AD to prevent 
possible multiple LPC fan blade failures, which could result in an 
uncontained engine failure and damage to the airplane.

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.

Initial Ultrasonic Inspection

    (f) Perform an initial ultrasonic inspection of the LPC fan 
blade dovetail roots using Method A (paragraphs 3.A.(1) through 
3.A.(8); blades removed from engine) of Accomplishment Instructions 
of RR Mandatory Service Bulletin (MSB) No. RB.211-72-C878, Revision 
7, dated December 5, 2003, as follows:
    (1) Inspect before accumulating 1,100 cycles-since-new (CSN) on 
the fan blades; or
    (2) For fan blades that have accumulated more than 800 CSN on 
the effective date of this AD that have not been previously 
inspected, inspect within 300 cycles-in-service (CIS) from the 
effective date of this AD or within 2,000 CSN, whichever occurs 
first.

Repetitive Ultrasonic Inspections

    (g) Perform repetitive inspections of the LPC fan blades using 
Method A, or Method B (paragraphs 3.B.(1) through 3.B.(5); blades 
not removed from the engine) of the Accomplishment Instructions of 
RR MSB No. RB.211-72-C878, Revision 7, dated December 5, 2003, as 
follows:
    (1) Inspect within 300 CIS since-last-inspected with Method A of 
the SB; or
    (2) Inspect within 250 CIS since-last-inspected with Method B of 
the SB.

Alternative Methods of Compliance

    (h) 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

    (i) You must use the Rolls-Royce plc service information 
specified in Table 1 of this AD to perform the blade inspections and 
replacements required by this AD. The Director of the Federal 
Register approved the incorporation by reference of the documents 
listed in Table 1 of this AD 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 DE24 6BJ, UK; telephone 44 (0) 1332 242424; fax 44 (0) 1332 
249936. You may review copies at the FAA, New England Region, Office 
of the Regional Counsel, Attention: Rules Docket No. 2000-NE-05-AD, 
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/code_of_federal_regulations/ibr_locations.html. Table 1 follows:

                                      Table 1.--Incorporation by Reference
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    Mandatory service bulletin No.                Page              Revision                  Date
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RB.211-72-C878........................  All.....................            7  December 5, 2003.
    Total Pages: 9
RB.211-72-C878, Appendix 1............  All.....................            7  December 5, 2003.
    Total Pages: 4
RB.211-72-C878, Appendix 2............  All.....................            7  December 5, 2003.

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    Total Pages: 5
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Related Information

    (j) United Kingdom Civil Aviation Authority airworthiness 
directive 003-11-99 also addresses the subject of this AD.

    Issued in Burlington, Massachusetts, on January 4, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-484 Filed 1-12-05; 8:45 am]
BILLING CODE 4910-13-P