[Federal Register: November 4, 2008 (Volume 73, Number 214)]
[Rules and Regulations]
[Page 65511-65514]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr04no08-8]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29343; Directorate Identifier 2000-NE-13-AD;
Amendment 39-15721; AD 2008-22-24]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211-535E4-37, RB211-
535E4-B-37, and RB211-535E4-B-75 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, and
RB211-535E4-B-75 series turbofan engines. That AD currently requires
initial and repetitive ultrasonic inspections of installed low pressure
compressor (LPC) fan blade roots on-wing and during overhaul, and
relubrication according to accumulated life cycles. Also, that AD
introduces application of Metco 58 blade root coating as an optional
terminating action. This AD requires the same actions but adds
compliance paragraphs to relax the compliance schedule for repetitive
inspections for fan blades operating within RB211-535E4 flight profiles
A and B, if certain requirements are met. This AD also relaxes the
initial compliance threshold by extending the cycles at which an
initial inspection is required. This AD results from RR issuing
Mandatory Service Bulletin (MSB) No. RB.211-72-C879, Revision 5 and
Revision 6, that introduced a relaxed repetitive compliance schedule
for fan blades operating within RB211-535E4 flight profiles A and B, if
certain requirements are met, and introduced a relaxed initial
compliance threshold. We are issuing this AD 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: This AD becomes effective December 9, 2008. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of December 9, 2008.
ADDRESSES: You can get the service information identified in this AD
from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone:
011-44-1332-242-424; fax: 011-44-1332-249-936.
The Docket Operations office is located at Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue,
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
ian.dargin@faa.gov; telephone: (781) 238-7178; fax: (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by
superseding AD 2005-02-05, Amendment 39-13950 (70 FR 3863, January 27,
2005), with a proposed AD. The proposed AD applies to RR RB211-535E4-
37, RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines. We
published the proposed AD in the Federal Register on October 25, 2007
(72 FR 60606). That action proposed to require initial and repetitive
ultrasonic inspections of installed LPC fan blade roots on-wing and
during overhaul, and relubrication according to accumulated life
cycles. That action also proposed to add compliance paragraphs to relax
the compliance schedule for repetitive inspections for RB211-535E4
engines operating in flight profiles A and B, if certain requirements
are met.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is provided in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received.
One commenter states that Rolls-Royce plc issued Mandatory Service
Bulletin No. RB.211-72-C879, Revision 6, dated December 14, 2007, while
the proposed AD comment period was still open, and the AD should
reference Revision 6.
We agree. Revision 6 contains the changes from Revision 5, and
relaxes the initial compliance threshold by extending the cycles at
which an inspection is required. We changed the AD to reference
Revision 6, and made the following changes based on Revision 6:
We deleted proposed AD paragraph (f), which referenced
full sets of fan blades modified using RR Service Bulletin No. RB.211-
72-C946, Revision 2, dated September 26, 2002, as the reference is
unnecessary. As a result we recodified paragraphs (f) through (n).
We clarified that the ultrasonic inspection is performed
on the fan blade roots.
Proposed AD paragraph (g) is changed from ``On RB211-535E4
engines, operated to Flight Profile A, ultrasonically inspect, and if
required,
[[Page 65512]]
relubricate using the following Table 2'' to the following:
``(f) On RB211-535E4 engines, operated to Flight Profile A:
(1) Ultrasonically inspect the fan blade root, and if required,
relubricate using one of the methods in Table 2 of this AD.
(2) If the initial inspection is complete prior to 18,600 cycles-
since-new (CSN), then the next inspection may be postponed until 20,000
CSN.''
Proposed AD paragraph (h) is changed from ``On RB211-535E4
engines, operated to Flight Profile B, ultrasonically inspect, and if
required, relubricate using the following Table 3:'' to the following:
``(g) On RB211-535E4 engines, operated to Flight Profile B:
(1) Ultrasonically inspect the fan blade root, and if required,
relubricate using one of the methods in Table 3 of this AD.
(2) If the initial inspection is complete prior to 14,150 CSN, then
the next inspection may be postponed until 15,000 CSN.''
Proposed AD paragraph (i) is changed from ``On RB211-535E4
engines, operated to Flight Profile A and B, ultrasonically inspect,
and if required, relubricate using the following Table 4:'' to the
following:
``(i) For fan blades operated to any combination of RB211-535E4
Flight Profile A, -535E4 Flight Profile B, -535E4-B, -535E4-B and -
535E4-C engines:
(1) Calculate an equivalent CSN as defined in the Time Limits
Manual. See References Section 1.G.(3), of MSB RB.211-72-C879, Revision
6, dated December 14, 2007.
(2) For fan blades that are currently flying in Profile A, inspect
using paragraph (f) and Table 2 of this AD using equivalent CSN.
(3) For fan blades that are currently flying in Profile B, inspect
using paragraph (g) and Table 3 of this AD using equivalent CSN.
(4) For fan blades that are currently flying in an RB211-535E4-B
engine, inspect using paragraph (h) and Table 4 of this AD using
equivalent CSN.''
We deleted proposed AD Table 4 because the information in
it was redundant. We recodified proposed AD Table 5 to Table 4.
We clarified in three of the proposed AD tables that
relubrication is to be done at shop visit if blade life is more than
19,650 cycles, 14,650 cycles, and 19,650 respectively.
Proposed AD paragraph (j) is changed from ``For RB211-
535E4 engines that are currently flying in Profile A, if the initial
inspection is completed before X minus 1,400 cycles then the next
inspection may be delayed to X, where X is 65% of the revised life
limit'' to ``(i)(2) For fan blades that are currently flying in Profile
A, inspect using paragraph (f) and Table 2 of this AD using equivalent
CSN''.
Proposed AD paragraph (k) is changed from ``For RB211-
535E4 engines that are currently flying in Profile B, if the initial
inspection is completed before X minus 850 cycles then the next
inspection may be delayed to X, where X is 65% of the revised life
limit'' to ``(i)(3) For fan blades that are currently flying in Profile
B, inspect using paragraph (g) and Table 3 of this AD using equivalent
CSN''.
Proposed AD paragraph (l) is deleted and incorporated into
paragraph (i).
Proposed AD paragraph (m) is changed from ``On RB211-
535E4-B engines, ultrasonically inspect, and if required, relubricate
using the following Table 5:'' to the following:
``(h) On RB211-535E4-B engines:
(1) Ultrasonically inspect the fan blade root, and if required,
relubricate using one of the methods in Table 4 of this AD.
(2) If the initial inspection is complete prior to 18,800 CSN, then
the next inspection may be postponed until 20,000 CSN.''
In addition, we updated our estimate of the total cost of the AD to
U.S. operators to $441,280. The proposed AD estimated the total cost of
the AD to U.S. operators to be $358,540. The estimate in the proposed
AD was based on an estimated average labor rate of $65 per work-hour.
The latest estimated average labor rate is $80 per work-hour.
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD with the change described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 788 engines installed on
airplanes of U.S. registry. We also estimate that it will take about 7
work-hours per engine to perform the actions, and that the average
labor rate is $80 per work-hour. Based on these figures, we estimate
the total cost of the AD to U.S. operators to be $441,280.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will 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.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 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.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
[[Page 65513]]
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-13950 (70 FR
3863, January 27, 2005), and by adding a new airworthiness directive,
Amendment 39-15721, to read as follows:
2008-22-24 Rolls-Royce plc: Amendment 39-15721. Docket No. FAA-2007-
29343; Directorate Identifier 2000-NE-13-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
9, 2008.
Affected ADs
(b) This AD supersedes AD 2005-02-05, Amendment 39-13950.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) 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/
Ns) listed in 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/Ns
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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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Unsafe Condition
(d) This AD results from RR issuing Mandatory Service Bulletin
(MSB) No. RB.211-72-C879, Revision 5 and Revision 6, that introduced
a relaxed repetitive compliance schedule for fan blades operating
within RB211-535E4 flight profiles A and B, if certain requirements
are met, and introduced a relaxed initial compliance threshold. We
are issuing this AD to detect cracks in low pressure compressor
(LPC) fan blade roots, which if not detected, could lead to
uncontained multiple fan blade failure, and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
(f) On RB211-535E4 engines, operated to Flight Profile A:
(1) Ultrasonically inspect the fan blade root, and if required,
relubricate using one of the methods in Table 2 of this AD.
(2) If the initial inspection is complete prior to 18,600
cycles-since-new (CSN), then the next inspection may be postponed
until 20,000 CSN.
Table 2--RB211-535E4 Flight Profile A
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Repeat
inspection
Initial In accordance with within cycles
Engine location inspection Type action mandatory service since last
within (CSN) bulletin (MSB) inspection
(CSLI)
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(1) On-wing....................... 20,000 (i) Root Probe RB.211-72-C879 1,400
inspect, OR. Revision 6, 3.A.(1)
through 3.A.(7),
dated December 14,
2007.
(ii) Wave Probe RB.211-72-C879 1,150
inspect. Revision 6, 3.B.(1)
through 3.B.(7),
dated December 14,
2007.
(2) In shop....................... 20,000 Root Probe inspect. RB.211-72-C879 1,400
Relubricate if blade Revision 6, 3.C.(1)
life is more than through 3.C.(4),
19,650 cycles. dated December 14,
2007.
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(g) On RB211-535E4 engines, operated to Flight Profile B:
(1) Ultrasonically inspect the fan blade root, and if required,
relubricate using one of the methods in Table 3 of this AD.
(2) If the initial inspection is complete prior to 14,150 CSN,
then the next inspection may be postponed until 15,000 CSN.
Table 3--RB211-535E4 Flight Profile B
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Initial Repeat
Engine location inspection Type action In accordance with inspection
within (CSN) MSB within CSLI
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(1) On-wing....................... 15,000 (i) Root Probe RB.211-72-C879 850
inspect, OR. Revision 6, 3.A.(1)
through 3.A.(7),
dated December 14,
2007.
(ii) Wave Probe RB.211-72-C879 700
inspect. Revision 6, 3.B.(1)
through 3.B.(7),
dated December 14,
2007.
(2) In shop....................... 15,000 Root Probe, inspect. RB.211-72-C879 850
Relubricate if blade Revision 6, 3.C.(1)
life is more than through 3.C.(4),
14,650 cycles. dated December 14,
2007.
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[[Page 65514]]
(h) On RB211-535E4-B engines:
(1) Ultrasonically inspect the fan blade root, and if required,
relubricate using one of the methods in Table 4 of this AD.
(2) If the initial inspection is complete prior to 18,800 CSN,
then the next inspection may be postponed until 20,000 CSN.
Table 4--RB211-535E4-B
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Initial Repeat
Engine location inspection Type action In accordance with inspection
within (CSN) MSB within (CSLI)
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(i) On-wing....................... 20,000 (A) Root Probe RB.211-72-C879 1,200
inspect, OR. Revision 6, 3.A.(1)
through 3.A.(7),
dated December 14,
2007.
(B) Wave Probe RB.211-72-C879 1,000
inspect. Revision 6, 3.B.(1)
through 3.B.(7),
dated December 14,
2007.
(ii) In shop...................... 20,000 Root Probe inspect. RB.211-72-C879 1,200
Relubricate if blade Revision 6, 3.C.(1)
life is more than through 3.C.(4),
19,650 cycles. dated December 14,
2007.
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(i) For fan blades operated to any combination of RB211-535E4
Flight Profile A, -535E4 Flight Profile B, -535E4-B, -535E4-B and -
535E4-C engines:
(1) Calculate an equivalent CSN as defined in the Time Limits
Manual. See References Section 1.G.(3), of MSB RB.211-72-C879,
Revision 6, dated December 14, 2007.
(2) For fan blades that are currently flying in Profile A,
inspect using paragraph (f) and Table 2 of this AD using equivalent
CSN.
(3) For fan blades that are currently flying in Profile B,
inspect using paragraph (g) and Table 3 of this AD using equivalent
CSN.
(4) For fan blades that are currently flying in an RB211-535E4-B
engine, inspect using paragraph (h) and Table 4 of this AD using
equivalent CSN.
Optional Terminating Action
(j) Application of Metco 58 blade root coating using RR SB No.
RB.211-72-C946, Revision 2, dated September 26, 2002, constitutes
terminating action to the repetitive inspection requirements
specified in paragraphs (f), (g), (h), and (i) of this AD.
Alternative Methods of Compliance
(k) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Previous Credit
(l) Inspections and relubrication done before the effective date
of this AD that use AD 2003-12-15 (Amendment 39-13200, 68 FR 37735,
June 25, 2003), RR MSB No. RB.211-72-C879, Revision 3, dated October
9, 2002, MSB No. RB.211-72-C879, Revision 4, dated April 2, 2004, or
MSB No. RB.211-72-C879, Revision 5, dated March 8, 2007, comply with
the requirements specified in this AD.
Related Information
(m) United Kingdom Civil Aviation Authority airworthiness
directive AD 002-01-2000, dated October 9, 2002, also addresses the
subject of this AD.
(n) Contact Ian Dargin, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-mail: ian.dargin@faa.gov;
telephone: (781) 238-7178; fax: (781) 238-7199, for more information
about this AD.
Material Incorporated by Reference
(o) You must use Rolls-Royce plc Mandatory Service Bulletin No.
RB.211-72-C879, Revision 6, dated December 14, 2007 to perform the
inspections and relubrication required by this AD. The Director of
the Federal Register approved the incorporation by reference of this
service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. Contact Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ;
telephone: 011-44-1332-242424; fax: 011-44-1332-249936, for a copy
of this service information. You may review copies at the FAA, New
England Region, 12 New England Executive Park, Burlington, MA; or at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued in Burlington, Massachusetts, on October 23, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-25891 Filed 11-3-08; 8:45 am]
BILLING CODE 4910-13-P