[Federal Register: February 20, 2003 (Volume 68, Number 34)]
[Proposed Rules]
[Page 8157-8161]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20fe03-9]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-NE-13-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce RB211 Series Turbofan
Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
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SUMMARY: This notice revises an earlier proposed airworthiness
directive (AD), applicable to Rolls-Royce (RR) plc RB211-535E4-37,
RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines. That
proposal would have required initial and repetitive ultrasonic
inspections of low pressure compressor (LPC) fan blade roots for
cracks, and relubrication of LPC fan blades before reinstallation. That
proposal was prompted by the discovery of cracks on LPC fan blade roots
during an engine overhaul. This action revises the proposed rule by
introducing an alternative technique to ultrasonically inspect
installed fan blades on-wing using a surface wave ultrasonic probe.
This action also adds the application of
[[Page 8158]]
Metco 58 blade root coating as an optional terminating action. The
actions specified by this proposed AD are intended to detect cracks in
LPC fan blade roots, which if not detected, could lead to uncontained
multiple fan blade failure, and damage to the airplane.
DATES: Comments must be received by April 21, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 2000-NE-13-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at
this location, by appointment, between 8:00 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 the proposed rule may be
obtained from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ;
telephone: 011-44-1332-242-424; fax: 011-44-1332-249-936. 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.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this action may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal 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 2000-NE-13-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRM's
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, New England Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2000-NE-13-AD, 12 New England Executive
Park, Burlington, MA 01803-5299.
Discussion
A proposal to amend part 39 of the Federal Aviation Regulations (14
CFR part 39) to add an airworthiness directive (AD), applicable to RR
plc RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 series
turbofan engines, was published as an NPRM in the Federal Register on
August 9, 2001 (66 FR 41808). That NPRM would have required initial and
repetitive ultrasonic inspections of LPC fan blade roots for cracks,
and relubrication of LPC fan blades before reinstallation. That NPRM
was prompted by the discovery of cracks on LPC fan blade roots during
an engine overhaul. That condition, if not corrected, could result in
uncontained multiple fan blade failure, and damage to the airplane.
The FAA received the following comments on the initial NPRM. The
latest revision to RR Mandatory Service Bulletin (MSB) RB.211-72-C879,
Revision 3, dated October 9, 2002, addresses those comments.
Two commenters request the incorporation of Metco 58 blade root
coating as a terminating action to the AD inspection requirements.
The FAA agrees. The Civil Aviation Authority (CAA), which is the
airworthiness authority for the United Kingdom (UK), has notified the
FAA that incorporation of Metco 58 blade root coating using RR Service
Bulletin (SB) RB.211-72-C946, dated August 6, 2002, is considered a
terminating action to the inspections. The FAA has examined the
information provided by RR and the CAA and agrees with the conclusions.
Incorporation of Metco 58 blade root coating has been added to the
proposed AD as a terminating action.
One commenter requests a draw down inspection schedule for engines
that have not previously had repetitive inspections. The commenter
states that due to the age of its fleet, it would be difficult to do
repetitive inspections in accordance with the AD.
The FAA does not agree with the request due to the potential safety
hazard associated with a possible multiple fan blade release. However,
RR MSB RB211-72-C879, Revision 3, dated October 9, 2002, allows an
alternative on-wing ultrasonic inspection method.
Since the above comments expand the scope of the originally
proposed rule, the FAA has determined that it is necessary to reopen
the comment period to provide additional opportunity for public
comment.
Manufacturer's Service Information
RR has issued MSB RB.211-72-C879, Revision 3, dated October 9,
2002, that specifies ultrasonic inspection of high cyclic life blades
on-wing with either the LPC fan blades in place or removed from the
LPC. The CAA classified this service bulletin as mandatory and issued
AD 002-01-2000 in order to ensure the airworthiness of these RR engines
in the UK.
Bilateral Agreement Information
These engines are manufactured in the United Kingdom (UK), and are
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 Proposed Actions
Since an unsafe condition has been identified that is likely to
exist or develop on other RR RB211-535E4 series turbofan engines of the
same type design, that are used on Boeing 757 airplanes registered in
the United States, the proposed AD would require initial and repetitive
ultrasonic inspections of LPC fan blade roots on-wing and during
overhaul, and relubrication, according to accumulated life cycles.
Economic Analysis
There are approximately 1,021 engines of the affected design in the
worldwide fleet. The FAA estimates that 545 engines installed on
aircraft of U.S.
[[Page 8159]]
registry would be affected by this proposed AD. It will take
approximately 7.0 work hours per engine to conduct an on-wing initial
inspection, and 2 hours per engine to do an overhaul initial inspection
of the proposed actions. The average labor rate is $60 per work hour.
Since the actions are inspections, there are no required parts costs.
Based on these figures, the FAA estimates the total cost for on-wing
initial inspections only, of the proposed AD on U.S. operators, to be
$228,900, and for overhaul initial inspections only, to be $65,400.
Regulatory Analysis
This proposed 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 proposed rule.
For the reasons discussed above, I certify that this proposed
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) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action 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.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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: Rolls-Royce plc: Docket No. 2000-NE-13-AD.
Applicability
This airworthiness directive (AD) is applicable to Rolls-Royce (RR)
plc RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 series
turbofan engines with low pressure compressor (LPC) fan blades with the
part numbers (P/N's) listed in the following Table 1 of this AD. These
engines are installed on, but not limited to Boeing 757 and Tupolev
Tu204 series airplanes. Table 1 follows:
Table 1.--Applicable LPC Fan Blade P/N's
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UL16135 UL16171 UL16182 UL19643 UL20044
UL20132 UL20616 UL21345 UL22286 UL23122
UL24525 UL24528 UL24530 UL24532 UL24534
UL27992 UL28601 UL28602 UL29511 UL29556
UL30817 UL30819 UL30933 UL30935 UL33707
UL33709 UL36992 UL37090 UL37272 UL37274
UL37276 UL37278 UL38029 UL38032 ............
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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 (g) 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 detect cracks in LPC fan blade roots, which if not detected,
could lead to uncontained multiple fan blade failure, and damage to the
airplane, do the following:
(a) If you have a full set of fan blades, modified using RR SB
RB.211-72-C946, dated August 6, 2002, that can be identified by a blue
triangle etched on the blade airfoil suction surface close to the
leading edge tip of each blade, no further action is required.
(b) On RB211-535E4 engines, operated to Flight Profile A,
ultrasonically inspect, and if required, relubricate using the
following Table 2:
Table 2.--RB211-535E4 Flight Profile A
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Initial Repeat
inspection inspection
Engine location within Type action In accordance with within
(CSN) (CSN)
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(1) On-wing................... 17,350. (i) Root Probe, RB.211-72-C879 Revision 3, 1,400.
inspect and 3.A.(1) through 3.A.(7), dated
relubricate, OR. October 9, 2002.
........... (ii) Wave Probe...... RB.211-72-C879 Revision 3, 1,150.
3.B.(1) through 3.B.(7), dated
October 9, 2002.
(2) In Shop................... 17,350. Root Probe, inspect RB.211-72-C879 Revision 3, 1,400.
and relubricate. 3.C.(1) through 3.C.(4), dated
October 9, 2002.
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[[Page 8160]]
(c) On RB211-535E4 engines, operated to Flight Profile B,
ultrasonically inspect, and if required, relubricate using the
following Table 3:
Table 3.--RB211-535E4 Flight Profile B
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Repeat
Initial inspection
Engine location inspection Type action In accordance with within
ithin (CSN) (CSN)
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(1) On-wing................... 12,350. (i) Root Probe, RB.211-72-C879 Revision 3, 850.
inspect and 3.A.(1) through 3.A.(7), dated
relubricate, OR. October 9, 2002.
........... (ii) Wave Probe...... RB.211-72-C879 Revision 3, 700.
3.B.(1) through 3.B.(7), dated
October 9, 2002.
(2) In Shop................... 12,350. Root Probe, inspect RB.211-72-C879 Revision 3, 850.
and relubricate. 3.C.(1) through 3.C.(4), dated
October 9, 2002.
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(d) On RB211-535E4 engines, operated to combined Flight Profile A
and B, ultrasonically inspect, and if required, relubricate using the
following Table 4:
Table 4.--RB211-535E4 Flight Profile A and B
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Initial inspection Repeat inspection
Engine location within (CSN) Type action In accordance with within (CSN)
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(1) On-wing................. 65% hard life (To (i) Root Probe, RB.211-72-C879 As current flight
calculate, inspect and Revision 3, profile.
Compliance Section relubricate, OR. 3.A.(1) through
1.C.(4)). see 3.A.(7), dated
October 9, 2002.
(ii) Wave Probe.... RB.211-72-C879 As current flight
Revision 3, profile.
3.B.(1) through
3.B.(7), dated
October 9, 2002.
(2) In Shop................. 65% hard life (To Root Probe, inspect RB.211-72-C879 As current flight
calculate, and relubricate. Revision 3, profile.
Compliance Section 3.C.(1) through
1.C.(4)). see 3.C.(4), dated
October 9, 2002.
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Note 2: Fan blades that have been operated within RB211-535E4
Flight Profile A and B will have final life as defined in the Time
Limits Manual. See References Section 1.G.(3), of MSB RB.211-72-
C879, Revision 3, dated October 9, 2002.
(e) On RB211-535E4-B engines, ultrasonically inspect, and if
required, relubricate using the following Table 5:
Table 5.--RB211-535E4-B
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Initial inspection Repeat within (CSN)
Engine location within (CSN) Type action In accordance with inspection
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(1) On-wing................. 17,000............. (i) Root Probe, RB.211-72-C879 1,200.
inspect and Revision 3,
relubricate OR. 3.A.(1) through
3.A.(7), dated
October 9, 2002.
(ii) Wave Probe.... RB.211-72-C879 1,000.
Revision 3,
3.B.(1) through
3.B.(7), dated
October 9, 2002.
(2) In Shop................. 17,000............. Root Probe, inspect RB.211-72-C879 1,200
and relubricate. inspect and
Revision 3,
3.C.(1) through
3.C.(4), dated
October 9, 2002.
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Optional Terminating Action
(f) Application of Metco 58 blade root coating using RR SB RB.211-
72-C946, Revision 1, dated August 6, 2002, constitutes terminating
action to the repetitive inspection requirements specified in
paragraphs (b), (c), (d), and (e) of this AD.
Alternative Methods of Compliance
(g) 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
(h) 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 aircraft to a location
[[Page 8161]]
where the requirements of this AD can be done.
Note 4: The subject of this AD is addressed in CAA airworthiness
directive AD 002-01-2000, dated October 9, 2002.
Issued in Burlington, Massachusetts, on February 10, 2003.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 03-4057 Filed 2-19-03; 8:45 am]
BILLING CODE 4910-13-U