[Federal Register: November 29, 2002 (Volume 67, Number 230)]
[Rules and Regulations]
[Page 71094-71097]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29no02-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NE-16-AD; Amendment 39-12952; AD 2002-23-08]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc. RB211-535 Turbofan
Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable 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. This
action requires establishing new reduced LP turbine stage 2 disc cyclic
limits. This action also requires removing from service affected discs
that already exceed the new reduced cyclic limit, and removing other
affected discs before exceeding their cyclic limits, using a drawdown
schedule. The actions specified in this AD are intended to prevent LP
turbine stage 2 disc failure, which could result in uncontained engine
failure and possible loss of the airplane.
DATES: Effective December 30, 2002. The incorporation by reference of
certain publications listed in the rule is approved by the Director of
the Federal Register as of December 30, 2002.
Comments for inclusion in the Rules Docket must be received on or
before January 28, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 2002-NE-16-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. Comments may also be sent via
the Internet using the following address: 9-ane-adcomment@faa.gov.
Comments sent via the Internet must contain the docket number in the
subject line.
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 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: The Civil Aviation Authority (CAA), which is
the airworthiness authority for the United Kingdom (U.K.), recently
notified the FAA that an unsafe condition may exist on RR models RB211-
535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 turbofan engines. The
CAA advises that a reassessment of the safe cyclic limits of LP turbine
stage 2 discs, P/N's UL11508, UL17141, UL18947, UL29029, and UL37352
has been performed by the manufacturer. The cyclic limits of these
discs are reduced based on more recent thermal and stress data obtained
from operational experience. This condition, if not corrected, could
result in uncontained engine failure and possible loss of the airplane.
Manufacturer's Service Information
Rolls-Royce plc. has issued mandatory service bulletin (MSB)
RB.211-72-D181, Revision 3, dated August 16, 2002, that specifies a
drawdown schedule for removing from service affected LP turbine stage 2
discs, using new Time Limits Manual (TLM) cyclic limits. This MSB
provides a scheduled reduction, by engine and flight plan, of LP
turbine stage 2 disc lives until the full life-cycle reduction on
December 31, 2005. This MSB also provides instructions for performing a
one-time on-wing eddy current inspection for cracks of affected LP
turbine stage 2 discs to allow a disc to remain in service for an
additional 3,000 cycles, if it does not exceed the new, lower TLM
cyclic limit. The CAA has classified this service bulletin as mandatory
and issued AD 006-05-2001 in order to assure the airworthiness of these
Rolls-Royce plc. turbofan engines in the U.K.
[[Page 71095]]
Bilateral Airworthiness Agreement
This engine model is manufactured in the U.K. 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 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 Required Actions
Since an unsafe condition has been identified that is likely to
exist or develop on other RR models RB211-535E4-37, RB211-535E4-B-37,
and RB211-535E4-B-75 turbofan engines of the same type design, this AD
is being issued to prevent LP stage 2 turbine disc failure, which could
result in uncontained engine failure and possible loss of the airplane.
This AD requires:
[sbull] Reducing the LP turbine stage 2 disc life-cyclic limits;
and
[sbull] Removing from service affected discs that already exceed
the new reduced cyclic limits; and
[sbull] Removing other affected discs before exceeding their cyclic
limits, using a drawdown schedule.
The actions must be done in accordance with the MSB described
previously.
Immediate Adoption of This AD
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2002-NE-16-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979). If it is determined
that this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket. A copy of it, if filed, 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.
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
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 adding the following new
airworthiness directive:
2002-23-08 Rolls-Royce plc.: Amendment 39-12952.
Docket No. 2002-NE-16-AD.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/N's)
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 (d) 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: Compliance with this AD is required as indicated,
unless already 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:
Cyclic Limits
(a) Change the RR Time Limits Manual cyclic limits for LP
turbine stage 2 discs as specified in the following Table 1:
[[Page 71096]]
Table 1.--Time Limits Manual (TLM) Cyclic Limits
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Life limits for
RB211-535E4 Life limits for
engines operating RB211-535E4
Date of reduced life limit in flight plan A, engines operating
and RB211-535E4-B in flight plan B
engines
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(1) December 31, 2001........... 22,500 cycles- 19,700 CSN.
since-new (CSN).
(2) December 31, 2002........... 22,500 cycles- 19,000 CSN.
since-new (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)(1) 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
Disc CSN on the effective date of -------------------------------------------------
this AD Action Without Eddy current With Eddy current
inspection inspection
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(i) 20,001 CSN or greater............ Remove disc from Within 21 days after Within 3,000 cycles-in-
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.
(ii) 18,100 to 20,000 CSN............ Remove disc from Before accumulating Within 3,000 cycles-in-
service or perform 21,000 CSN or by service (CIS) after
optional on-wing eddy December 31, 2002, the inspection, but do
current disc whichever occurs first. not exceed the new
inspection. reduced life limit
specified in Table 1
of this AD.
(iii) Fewer than 18,100 CSN.......... Remove disc from Before accumulating Within 3,000 cycles-in-
service or perform 20,500 CSN or by service (CIS) after
optional on-wing eddy December 31, 2004, the inspection, but do
current disc whichever occurs first. not exceed the new
inspection. reduced life limit
specified in Table 1
of this AD.
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(2) 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.
(3) 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
(c)(1) 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
Disc CSN on the effective date of -------------------------------------------------
this AD Action Without Eddy current With Eddy current
inspection inspection
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(i) 16,501 CSN or greater............ Remove disc from Within 21 days after Within 3,000 cycles-in-
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.
(ii) 14,600 to 16,500 CSN............ Remove disc from Before accumulating Within 3,000 cycles-in-
service or perform 17,500 CSN or by service (CIS) after
optional on-wing eddy December 31, 2002, the inspection, but do
current disc whichever occurs first. not exceed the new
inspection. reduced life limit
specified in Table 1
of this AD.
(iii) Fewer than 14,600 CSN.......... Remove disc from Before accumulating Within 3,000 cycles-in-
service or perform 17,000 CSN or by service (CIS) after
optional on-wing eddy December 31, 2004, the inspection, but do
current disc whichever occurs first. not exceed the new
inspection. reduced life limit
specified in Table 1
of this AD.
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[[Page 71097]]
(2) 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.
(3) 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.
Alternative Methods of Compliance
(d) 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 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 airworthiness directive,
if any, may be obtained from the ECO.
Special Flight Permits
(e) 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
(f) The disc removals and inspections must be done in accordance
with Roll-Royce MSB 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, PO Box 31,
Derby, England; telephone: 011-44-1332-249428; fax 011-44-1332-
249223. 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 3: The subject of this AD is addressed in CAA airworthiness
directive 006-05-2001.
Effective Date
(g) This amendment becomes effective on December 16, 2002.
Issued in Burlington, Massachusetts, on November 8, 2002.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 02-29001 Filed 11-27-02; 8:45 am]
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