AD 2000-24-26

[Federal Register Volume 65, Number 240 (Wednesday, December 13, 2000)]
[Rules and Regulations]
[Pages 77778-77780]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-31066]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-33-AD; Amendment 39-12033; AD 2000-24-26]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Rolls-Royce plc RB211 Trent 800 series 
turbofan engines, that currently requires initial and repetitive 
ultrasonic inspections of fan blade roots for cracks, and replacement, 
if necessary, with serviceable parts. This amendment requires the 
reduction of the initial cyclic compliance threshold and repetitive 
inspection intervals. This amendment also allows inspections to be 
accomplished within 100 cycles-in-service if the initial or repetitive 
thresholds are exceeded on the effective date of this AD. This 
amendment is prompted by an improved understanding of the crack 
propagation mechanism and the latest service operational data. The 
actions specified by this AD are intended to detect and prevent fan 
blade failure, which could result in multiple fan blade releases, 
uncontained engine failure, and possible damage to the airplane.

DATES: Effective February 12, 2001. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of February 12, 2001.

ADDRESSES: The service information referenced in this AD may be 
obtained from Rolls-Royce North America, Inc., 2001 South Tibbs Ave., 
Indianapolis, IN 46241; telephone: (317) 230-3995, fax: (317) 230-4743. 
This information may be examined at the Federal Aviation Administration 
(FAA), New England Region, Office of the Regional Counsel, 12 New 
England Executive Park, Burlington, MA 01803-5299; or at the Office of 
the Federal Register, 800 North Capitol Street, NW, suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Richard Woldan, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone: (781) 
238-7136, fax: (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-19-21, 
Amendment 39-10762 (63 FR 50484, September 22, 1998, corrected by 63 FR 
52961, October 2, 1998), applicable to Rolls-Royce plc (RR) RB211 Trent 
800 series turbofan engines, was published in the Federal Register on 
December 3, 1999 (64 FR 67806). That action proposed to require the 
reduction of initial compliance thresholds and repetitive cyclic 
inspection intervals. The action also proposed the allowance for 
inspections to be accomplished within 100 cycles-in-service if the 
initial or repetitive thresholds are exceeded on the effective date of 
the AD.

Comments Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the one comment received.

Request To Revise Economic Analysis

    The comment states that all RR Trent 800 series engines on the US 
registry that will be affected by the AD have already been modified to 
RR Service Bulletin RB.211-72-C629. Therefore, the estimate of the 
total cost impact of the proposed action on US operators is zero.
    The FAA disagrees. Although some Trent 800 series engines on US 
registered airplanes may have already been modified to RR Service 
Bulletin RB.211-72-C629 and the actual cost may be reduced, the 
original economic analysis is retained.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Regulatory Impact

    This rule does not have federalism implications, as defined in 
Executive Order (EO) 13132, because it does 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this rule.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under EO 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. A final 
evaluation has been prepared for this action and it is contained in the 
Rules Docket. A copy of it may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 77779]]

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration (FAA) amends part 39 
of the Federal Aviation Regulations (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. Section 39.13 is amended by removing Amendment 39-10762 (63 FR 
50484, September 22, 1998) and by adding a new airworthiness directive, 
Amendment 39-12033, to read as follows:

AD 2000--24-26  Rolls-Royce plc.: Amendment 39-12033. Docket 98-ANE-
33-AD. Supersedes AD 98-19-21, Amendment 39-10762.

    Applicability: Rolls-Royce plc (RR) RB211 Trent 875, RB211 Trent 
877, RB211 Trent 884, RB211 Trent 892, and RB211 Trent 892B series 
turbofan engines, except if the fan blades described in RR Service 
Bulletin (SB) RB.211-72-C629 were installed as complete sets. These 
engines are installed on but not limited to Boeing 777 series 
airplanes.

    Note 1: This airworthiness directive (AD) applies to each engine 
identified in the preceding applicability provision, regardless of 
whether it has been modified, altered, or repaired in the area 
subject to the requirements of this AD. For engines that have been 
modified, altered, or repaired so that the performance of the 
requirements of this AD is affected, the owner/operator must request 
approval for an alternative method of compliance in accordance with 
paragraph (b) of this AD. The request should include an assessment 
of the effect of the modification, alteration, or repair on the 
unsafe condition addressed by this AD; and, if the unsafe condition 
has not been eliminated, the request should include specific 
proposed actions to address it.

Compliance

    Required as indicated, unless accomplished previously.
    To prevent fan blade failure, which could result in multiple fan 
blade releases, uncontained engine failure, and possible damage to 
the airplane, accomplish the following:

Ultrasonic Inspections (Reduced Thresholds and Repetitive Intervals)

    (a) Perform initial and repetitive inspections of fan blade 
roots for cracks, in accordance with RR SB No. RB211-72-C445, 
Revision 6, dated September 3, 1999, as follows:
    (1) For Trent 875 series engines, inspect as follows:
    (i) Initially, prior to accumulating 3,000 cycles-since-new 
(CSN).
    (ii) Thereafter, at intervals not to exceed 400 cycles-in-
service (CIS) since last inspection.
    (2) For Trent 877 series engines, inspect as follows:
    (i) Initially, prior to accumulating 2,000 CSN.
    (ii) Thereafter, at intervals not to exceed 350 CIS since last 
inspection.
    (3) For Trent 884 series engines, inspect as follows:
    (i) Initially, prior to accumulating 1,500 CSN.
    (ii) Thereafter, at intervals not to exceed 350 CIS since last 
inspection.
    (4) For Trent 892 and 892B series engines, inspect as follows:
    (i) Initially, prior to accumulating 900 CSN.
    (ii) Thereafter, at intervals not to exceed 200 CIS since last 
inspection.

Engines Exceeding Thresholds and Repetitive Intervals

    (5) For engines that exceed the initial inspection thresholds 
listed in paragraphs (a)(1)(i), (a)(2)(i), (a)(3)(i), and (a)(4)(i) 
on the effective date of this AD, conduct initial inspection within 
100 CIS after the effective date of this AD.
    (6) For engines that exceed the repetitive inspection intervals 
listed in paragraphs (a)(1)(ii), (a)(2)(ii), (a)(3)(ii), and 
(a)(4)(ii) on the effective date of this AD, inspect within 100 CIS 
after the effective date of this AD.

Cracked Parts

    (7) Prior to further flight, remove from service cracked fan 
blades and replace with serviceable parts.

Alternate Method of Compliance

    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office (ECO). 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the ECO.

Ferry Flights

    (c) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the inspection requirements of this AD can be accomplished.

Incorporation by Reference Material

    (d) The actions required by this AD must be done in accordance 
with the following Rolls-Royce SB:

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           Document No.                      Pages                    Revision                    Date
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RB.211-72-C445...................  1-9......................  6.......................  September 3, 1999.
Appendix 1.......................  1........................  Original................  February 13, 1998.
                                   2........................  6.......................  September 3, 1999.
                                   3-4......................  Original................  February 13, 1998.
Appendix 2.......................  1........................  Revision 4..............  November 6, 1998.
                                   2-3......................  Original................  February 13, 1998.
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[[Page 77780]]

    Total pages: 16.
    The incorporations by reference were approved by the Director of 
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51. Copies may be obtained from Rolls-Royce North America, 
Inc., 2001 South Tibbs Ave., Indianapolis, IN 46241; telephone: 
(317) 230-3995; fax: (317) 230-4743. Copies may be inspected at the 
FAA, New England Region, Office of the Regional Counsel, 12 New 
England Executive Park, Burlington, MA 01803-5299; or at the Office 
of the Federal Register, 800 North Capitol Street, NW, suite 700, 
Washington, DC.

Effective Date

    (e) This amendment becomes effective on February 12, 2001.

    Issued in Burlington, Massachusetts, on November 30, 2000.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-31066 Filed 12-12-00; 8:45 am]
BILLING CODE 4910-13-U