[Federal Register: July 30, 2003 (Volume 68, Number 146)]
[Rules and Regulations]
[Page 44610-44611]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30jy03-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NE-03-AD; Amendment 39-13249; AD 2003-15-06]
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 adopts a new airworthiness directive (AD) that
applies to Rolls-Royce plc (RR) RB211 Trent 875-17, Trent 877-17, Trent
884-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines
with high pressure (HP) compressor rotor rear stage 5 and 6 discs and
cone shafts, part numbers (P/Ns) FK25230 and FK27899 installed. This
amendment requires removal from service of these HP compressor rotor
rear stage 5 and 6 discs and cone shafts, before reaching newly reduced
life limits. This amendment is prompted by three reports of crack
indications in the stage 5 and stage 6 blade loading slots, found
during engine overhaul. We are issuing this AD to prevent stage 5 and 6
disc crack initiation and propagation leading to uncontained disc
failure and damage to the airplane.
DATES: Effective September 3, 2003.
ADDRESSES: The service information referenced in this AD may be
obtained from Rolls Royce plc, P.O. Box 31, DERBY, DE24 8BJ, UK,
telephone: 44 (0) 1332 242424; fax: 44 (0) 1332 249936. This
information may be examined, by appointment, at the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, 12 New England Executive Park, Burlington, MA; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299, telephone (781)
238-7176; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an AD that is
applicable to RR RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent
892-17, Trent 892B-17, and Trent 895-17 turbofan engines with HP
compressor rotor rear stage 5 and 6 discs and cone shafts, part numbers
(P/Ns) FK25230 and FK27899 installed was published in the Federal
Register on March 11, 2003. That action proposed to require removal
from service of these HP compressor rotor rear stage 5 and 6 discs and
cone shafts, before reaching newly reduced life limits. Information on
the reduced life limits of these HP compressor rotors may be found in
RR mandatory service bulletin (MSB) RB.211-72-E082, Revision 2, dated
November 22, 2002.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Request To Include a Reference to RR Service Information
One commenter requests that a reference to RR MSB RB.211-72-E082,
Revision 2, dated November 22, 2002, be included in the final rule. The
commenter believes that the reference to the MSB is necessary for
clarification and for traceability to the AD if future revisions to the
MSB are issued.
The FAA agrees. The MSB reference is included in the Supplementary
Information paragraph and in Compliance paragraph (a).
Request To Withdraw Unnecessary AD
One commenter states that the new life limit specified in the AD
has already been included in the RB211 Trent Time Limits Manual
(Chapter 5); therefore, the AD is unnecessary.
The FAA does not agree. Although the new life limits have been
included in the RB211 Time Limits Manual, the reduced life limits are
not enforceable unless mandated by an AD. Accordingly, the FAA will not
change the AD based on this comment.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest the adoption of the rule with the change described previously.
The FAA has determined that this change will neither increase the
economic burden on any operator nor increase the scope of the AD.
Regulatory Analysis
This final rule does not have federalism implications, as defined
in Executive Order 13132, because it would 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
[[Page 44611]]
various levels of government. Accordingly, the FAA has not consulted
with state authorities prior to publication of this final rule.
For the reasons discussed above, I certify that this action: (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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
by contacting the Rules Docket at the location provided under the
caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration 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. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2003-15-06 Rolls-Royce plc: Amendment 39-13249. Docket No. 2003-NE-
03-AD.
Applicability
This airworthiness directive (AD) applies to Rolls-Royce plc
(RR) RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 892-17,
Trent 892B-17, and Trent 895-17 turbofan engines with high pressure
(HP) compressor rotor rear stage 5 and 6 discs and cone shafts, part
numbers (P/Ns) FK25230 and FK27899 installed. These engines are
installed on, but not limited to Boeing 777 airplanes.
Note 1: This 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 (c) 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
You are responsible for having the actions required by this AD
performed within the compliance times specified unless the actions
have already been accomplished.
To prevent stage 5 and 6 disc crack initiation and propagation
leading to uncontained disc failure and damage to the airplane, do
the following:
(a) Remove HP compressor rotor rear stage 5 and 6 discs and cone
shafts, from service at or before accumulating 7,500 cycles-since-
new (CSN). Information on the reduced life limits may be found in RR
mandatory service bulletin RB.211-72-E082, Revision 2, dated
November 22, 2002.
(b) After the effective date of this AD, do not install any HP
compressor rotor rear stage 5 and 6 discs and cone shaft, listed in
this AD, that exceed 7,500 CSN.
Alternative Methods of Compliance
(c) 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 must submit their request 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 airworthiness directive,
if any, may be obtained from the ECO.
Special Flight Permits
(d) Special flight permits may be issued in accordance with
Sec. Sec. 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 requirements of this AD can be done.
Note 3: The subject of this AD is addressed in CAA airworthiness
directive 002-08-2002, dated November 22, 2002.
Effective Date
(e) This amendment becomes effective on September 3, 2003.
Issued in Burlington, Massachusetts, on July 23, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 03-19306 Filed 7-29-03; 8:45 am]
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