[Federal Register: August 28, 2003 (Volume 68, Number 167)]
[Rules and Regulations]
[Page 51682-51685]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr28au03-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NE-16-AD; Amendment 39-13290; AD 2003-17-15]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc. RB211-535 Turbofan
Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD)
[[Page 51683]]
that applies to Rolls-Royce plc. (RR) models RB211-535E4-37, RB211-
535E4-B-37, and RB211-535E4-B-75 turbofan engines, with certain part
number (P/N) low pressure (LP) turbine stage 2 discs installed. That AD
currently requires establishing new reduced LP turbine stage 2 disc
cyclic limits. That AD also requires removing from service affected
discs that already exceed the new reduced cyclic limits, and removing
other affected discs before exceeding their cyclic limits, using a
drawdown schedule. This amendment requires changing certain cyclic
limits, changing the effective date of certain disc cyclic lives, and
would allow intermix of Flight Plan A and Flight Plan B intermix
calculations. This amendment is prompted by a reassessment of the
thermal and stress data from recent operational experience and comments
received from operators on the current AD. We are issuing this AD to
prevent LP turbine stage 2 disc failure, which could result in
uncontained engine failure and possible loss of the airplane.
DATES: Effective October 2, 2003. The incorporation by reference of
certain publications listed in the regulations is approved by the
Director of the Federal Register as of October 2, 2003.
ADDRESSES: The service information referenced in this AD may be
obtained from Rolls-Royce plc, P.O. Box 31 Derby, DE24 8BJ, United
Kingdom; telephone 011-44-1332-242424; fax 011-44-1332-249936. 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: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7178; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 2002-23-08,
Amendment 39-12952 (67 FR 71094, November 29, 2002), which applies to
RR models RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75
turbofan engines, with certain P/N low pressure LP turbine stage 2
discs installed was published in the Federal Register on March 25, 2003
(68 FR 14355). That action proposed to require establishing new reduced
LP turbine stage 2 disc cyclic limits. That AD also requires removing
from service affected discs that already exceed the new reduced cyclic
limits, and removing other affected discs before exceeding their cyclic
limits, using a drawdown schedule in accordance with mandatory service
bulletin (MSB) RB.211-72-D181, Revision 3, dated August 16, 2002.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public. The FAA
has determined that air safety and the public interest require the
adoption of the rule as proposed.
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 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, Incorporation by
reference, Safety.
Adoption of the Amendment
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 removing Amendment 39-12952 (67 FR
71094, November 29, 2002) and by adding a new airworthiness directive,
Amendment 39-13290, to read as follows:
2003-17-15 Rolls-Royce plc: Amendment 39-13290. Docket No. 2002-NE-
16-AD. Supersedes AD 2002-23-08, Amendment 39-12952.
Applicability: This airworthiness directive (AD) is applicable
to Rolls-Royce plc. (RR) models RB211-535E4-37, RB211-535E4-B-37,
and RB211-535E4-B-75 turbofan engines, with low pressure (LP)
turbine stage 2 discs part numbers (P/Ns) UL11508, UL17141, UL18947,
UL29029, and UL37352 installed. These engines are installed on, but
not limited to, Boeing 757 and Tupolev Tu204 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 (h) 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 done.
To prevent LP turbine stage 2 disc failure, which could result
in an uncontained engine failure and possible loss of the airplane,
do the following:
Cycle Limits
(a) Change the RR Time Limits Manual cyclic limits for LP
turbine stage 2 discs as specified in the following Table 1:
[[Page 51684]]
Table 1.--Time Limits Manual (TLM) Cyclic Limits
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Life limits for
RB211-535E4 engines Life limits for
operating in flight RB211-535E4 engines
Date of reduced life limit plan A, and RB211- operating in flight
535E4-B engines plan B
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(1) December 31, 2001....... 23,200 cycles-since- 19,700 CSN.
new (CSN).
(2) December 31, 2002....... 22,500 CSN.......... 19,000 CSN.
(3) December 31, 2003....... 21,500 CSN.......... 18,000 CSN.
(4) December 31, 2004....... 20,000 CSN.......... 16,500 CSN.
(5) December 31, 2005....... 18,100 CSN.......... 14,600 CSN.
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RB211-535E4 Engines Operating to Flight Plan A, and RB211-535E4-B
Engines
(b) For RB211-535E4 engines operating to flight plan A, and
RB211-535E4-B engines, remove the LP turbine stage 2 disc from
service using the CSN and Action times listed in the following Table
2.
Table 2.--Drawdown Schedule for RB211-535E4 Engines Operating to Flight Plan A, and RB211-535E4-B Engines
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Replace disc
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Disc CSN Action Without eddy current With eddy current
inspection inspection
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(1) 20,001 CSN or greater on December Remove disc from Within 21 days after Within 3,000 cycles-in-
31, 2000. service or perform the effective date of service (CIS) after
optional on-wing eddy this AD. the inspection, but do
current disc not exceed the new
inspection within 21 reduced life limit
days after the specified in Table 1
effective date of this of this AD
AD.
(2) 18,100 to 20,000 CSN on December Remove disc from Before accumulating Within 3,000 CIS after
31, 2000. service or perform 21,000 CSN or within the inspection, but do
optional on-wing eddy 21 days after the not exceed the new
current disc effective date of this reduced life limit
inspection. AD, whichever occurs specified in Table 1
first. of this AD.
(3) Fewer than 18,100 CSN on December Remove disc from Before accumulating Within 3,000 CIS after
31, 2000 and greater than 20,000 CSN service or perform 20,500 CSN or by the inspection, but do
on December 31, 2004. optional on-wing eddy December 31, 2004, not exceed the new
current disc whichever occurs first. reduced life limit
inspection. specified in Table 1
of this AD.
(4) Fewer than 18,100 CSN on December Remove disc from Before accumulating Within 3,000 CIS after
31, 2000 and greater than 18,100 CSN service or perform on- 20,000 CSN or by the inspection, but do
on December 31, 2005. wing eddy current disc December 31, 2005, not exceed the new
inspection. whichever occurs first. reduced life limit
specified in Table 1
of this AD.
(5) Fewer than 18,100 CSN on December No action required..... N/A.................... N/A.
31, 2000 and fewer than 18,100 CSN
on December 31, 2005.
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(c) Information regarding disc removal may be found in 3.A. of
the Accomplishment Instructions of Mandatory Service Bulletin (MSB)
RB.211-72-D181, Revision 3, dated August 16, 2002.
(d) The optional on-wing eddy current disc inspection noted in
Table 2 of this AD must be performed in accordance with 3.C.(1)
through 3.C.(6) of the Accomplishment Instructions of MSB RB.211-72-
D181, Revision 3, dated August 16, 2002.
RB211-535E4 Engines Operating to Flight Plan B
(e) For RB211-535E4 engines operating to flight plan B, remove
the LP turbine stage 2 disc from service using the CSN and Action
times listed in the following Table 3.
Table 3.--Drawdown Schedule for RB211-535E4 Engines Operating to Flight Plan B
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Replace disc
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Disc CSN Action Without eddy current With eddy current
inspection inspection
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(1) 16,501 CSN or greater on December Remove disc from Within 21 days after Within 3,000 CIS after
31, 2000. service or perform the effective date of the inspection, but do
optional on-wing eddy this AD. not exceed the new
current disc reduced life limit
inspection within 21 specified in Table 1
days after the of this AD.
effective date of this
AD.
(2) Greater than 14,600 CSN on Remove disc from Before accumulating Within 3,000 CIS after
December 31, 2000. service or perform 17,500 CSN or within the inspection, but do
optional on-wing eddy 21 days after the not exceed the new
current disc effective date of this reduced life limit
inspection. AD, whichever occurs specified in Table 1
first. of this AD.
[[Page 51685]]
(3) Fewer than 14,600 CSN on December Remove disc from Before accumulating Within 3,000 CIS after
31, 2000 and greater than 16,500 CSN service or perform 17,000 CSN or by the inspection, but do
on December 31, 2004. optional on-wing eddy December 31, 2004, not exceed the new
current disc whichever occurs first. reduced life limit
inspection. specified in Table 1
this AD.
(4) Fewer than 14,600 CSN on December Remove disc from Before accumulating Within 3,000 CIS after
31, 2000 and greater than 14,600 CSN service or perform on- 16,500 CSN or by the inspection, but do
on December 31, 2005. wing eddy current disc December 31, 2005, not exceed the new
inspection. whichever occurs first. reduced life limit
specified in this AD.
(5) Fewer than 14,600 CSN on December No action required..... N/A.................... N/A.
31, 2000 and fewer than 14,600 CSN
on December 31, 2005.
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(f) Information regarding disc removal may be found in 3.A. of
the Accomplishment Instructions of MSB RB.211-72-D181, Revision 3,
dated August 16, 2002.
(g) The optional on-wing eddy current disc inspection must be
performed in accordance with 3.C.(1) through 3.C.(6) of the
Accomplishment Instructions of MSB RB.211-72-D181, Revision 3, dated
August 16, 2002.
Note 2: For engines moving from Flight Plans A to B or B to A,
the intermix calculations found in MSB RB.211-72-D181, Revision 3,
dated August 16, 2002, may be applied to the life limits.
Alternative Methods of Compliance
(h) 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 3: 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
(i) 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.
Documents That Have Been Incorporated By Reference
(j) The actions must be done in accordance with Rolls-Royce plc
mandatory service bulletin RB.211-72-D181, Revision 3, dated August
16, 2002. This incorporation by reference was 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 plc, P.O.
Box 31 Derby, DE24 8BJ, United Kingdom; telephone 011-44-1332-
242424; fax 011-44-1332-249936. Copies may be inspected at the 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.
Note 4: The subject of this AD is addressed in CAA airworthiness
directive 006-05-2001, dated August 3, 2001.
Effective Date
(k) This amendment becomes effective on October 2, 2003.
Issued in Burlington, Massachusetts, on August 20, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 03-21740 Filed 8-27-03; 8:45 am]
BILLING CODE 4910-13-P