Airworthiness Directives; Rolls-Royce plc RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 Series Turbofan Engines, 65511-65514 [E8-25891]
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Federal Register / Vol. 73, No. 214 / Tuesday, November 4, 2008 / Rules and Regulations
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(2) Special Flight Permits: We are limiting
special flight permits to one ferry flight to a
maintenance station to replace the engine
clutch. The maximum flight duration must
not exceed 2 hours and is limited to VFR
conditions.
Related Information
(h) Refer to MCAI EASA Airworthiness
Directive 2008–0106–E, dated May 30, 2008,
for related information.
(i) Contact Jason Yang, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: jason.yang@faa.gov; telephone
(781) 238–7747; fax (781) 238–7199, for more
information about this AD.
Material Incorporated by Reference
(j) You must use Thielert Aircraft Engines
GmbH Service Bulletin TM TAE 125–1006
P1, Revision 1, dated May 30, 2008, to do the
actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Thielert Aircraft Engines
GmbH, Platanenstrasse 14 D–09350,
Lichtenstein, Germany, telephone: +49–
37204–696–0; fax: +49–37204–696–55; email: info@centurion-engines.com.
(3) 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
October 23, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–25892 Filed 11–3–08; 8:45 am]
BILLING CODE 4910–13–P
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]
dwashington3 on PRODPC61 with RULES
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc RB211–535E4–37, RB211–535E4–
B–37, and RB211–535E4–B–75 Series
Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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15:01 Nov 03, 2008
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ACTION:
Final rule.
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.
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65511
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 https://
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 RollsRoyce 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,
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Federal Register / Vol. 73, No. 214 / Tuesday, November 4, 2008 / Rules and Regulations
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
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15:01 Nov 03, 2008
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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
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.
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.
List of Subjects in 14 CFR Part 39
Costs of Compliance
Adoption of the Amendment
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.
■
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Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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
1. The authority citation for part 39
continues to read as follows:
■
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65513
Federal Register / Vol. 73, No. 214 / Tuesday, November 4, 2008 / Rules and Regulations
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
2008–22–24 Rolls-Royce plc: Amendment
39–15721. Docket No. FAA–2007–29343;
Directorate Identifier 2000–NE–13–AD.
[Amended]
2. The FAA amends § 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:
■
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
UL16135
UL20132
UL24525
UL27992
UL30817
UL33709
UL37276
UL16171
UL20616
UL24528
UL28601
UL30819
UL36992
UL37278
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
UL16182
UL21345
UL24530
UL28602
UL30933
UL37090
UL38029
UL19643
UL22286
UL24532
UL29511
UL30935
UL37272
UL38032
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.
UL20044
UL23122
UL24534
UL29556
UL33707
UL37274
(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
Engine location
(1) On-wing .............................
Initial
inspection
within
(CSN)
Type action
20,000
In accordance with mandatory service bulletin (MSB)
(i) Root Probe inspect, OR ....
RB.211–72–C879
Revision
6,
3.A.(1)
through 3.A.(7), dated December 14, 2007.
RB.211–72–C879
Revision
6,
3.B.(1)
through 3.B.(7), dated December 14, 2007.
RB.211–72–C879
Revision
6,
3.C.(1)
through 3.C.(4), dated December 14, 2007.
(ii) Wave Probe inspect .........
(2) In shop ..............................
20,000
(g) On RB211–535E4 engines, operated to
Flight Profile B:
Root Probe inspect. Relubricate if blade life is more
than 19,650 cycles.
(1) Ultrasonically inspect the fan blade
root, and if required, relubricate using one of
the methods in Table 3 of this AD.
Repeat
inspection
within
cycles since
last
inspection
(CSLI)
1,400
1,150
1,400
(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
Engine location
(1) On-wing .............................
Initial
inspection
within
(CSN)
15,000
Type action
In accordance with MSB
(i) Root Probe inspect, OR ....
RB.211–72–C879
Revision
6,
3.A.(1)
through 3.A.(7), dated December 14, 2007.
RB.211–72–C879
Revision
6,
3.B.(1)
through 3.B.(7), dated December 14, 2007.
RB.211–72–C879
Revision
6,
3.C.(1)
through 3.C.(4), dated December 14, 2007.
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(ii) Wave Probe inspect .........
(2) In shop ..............................
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15,000
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Root Probe, inspect. Relubricate if blade life is more
than 14,650 cycles.
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Repeat
inspection
within CSLI
850
700
850
65514
Federal Register / Vol. 73, No. 214 / Tuesday, November 4, 2008 / Rules and Regulations
(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
Engine location
(i) On-wing ..............................
Initial
inspection
within
(CSN)
20,000
Type action
In accordance with MSB
(A) Root Probe inspect, OR ..
RB.211–72–C879
Revision
6,
3.A.(1)
through 3.A.(7), dated December 14, 2007.
RB.211–72–C879
Revision
6,
3.B.(1)
through 3.B.(7), dated December 14, 2007.
RB.211–72–C879
Revision
6,
3.C.(1)
through 3.C.(4), dated December 14, 2007.
(B) Wave Probe inspect .........
(ii) In shop ..............................
20,000
(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.
dwashington3 on PRODPC61 with RULES
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:
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15:01 Nov 03, 2008
Jkt 217001
Root Probe inspect. Relubricate if blade life is more
than 19,650 cycles.
(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: https://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
COMMODITY FUTURES TRADING
COMMISSION
17 CFR Part 190
Interpretative Statement Regarding
Funds Related to Cleared-Only
Contracts Determined To Be Included
in a Customer’s Net Equity
Commodity Futures Trading
Commission.
ACTION: Interpretative Statement;
correction.
AGENCY:
This interpretation by the
Commodity Futures Trading
Commission (‘‘Commission’’) is issued
to clarify the appropriate treatment
under the commodity broker provisions
SUMMARY:
PO 00000
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Repeat
inspection
within (CSLI)
1,200
1,000
1,200
of the Bankruptcy Code and Part 190 of
the Commission’s Regulations of claims
arising from contracts (‘‘cleared-only
contracts’’) that, although not executed
or traded on a Designated Contract
Market or a Derivatives Transaction
Execution Facility, are subsequently
submitted for clearing through a Futures
Commission Merchant (‘‘FCM’’) to a
Derivatives Clearing Organization
(‘‘DCO’’). The Commission first
published this interpretation in the
Federal Register of October 2, 2008 (73
FR 57235). A statement of concurrence
on a different matter was printed at the
end of the interpretation, in error. The
Commission is republishing the
interpretation to clarify that the
statement of concurrence is not related
to the interpretation.
FOR FURTHER INFORMATION CONTACT:
Robert B. Wasserman, Associate
Director, rwasserman@cftc.gov, (202)
418–5092, or Amanda Olear, AttorneyAdvisor, Division of Clearing and
Intermediary Oversight, aolear@cftc.gov,
(202) 418–5283, Commodity Futures
Trading Commission, Three Lafayette
Centre, 1155 21st Street, NW.,
Washington, DC 20581.
Section 20 of the Commodity
Exchange Act 1 (Act) empowers the
Commission to provide how the net
equity of a customer is to be
determined:
The Commission may provide, with
respect to a commodity broker that is a
debtor under chapter 7 of title 11 of the
United States Code, by rule or regulation—
(1) that certain cash, securities, other
property, or commodity contracts are to be
included in or excluded from customer
property or member property; * * * and (5)
how the net equity of a customer is to be
determined.
Subchapter IV of Chapter 7 of the
Bankruptcy Code, governing commodity
brokers, has the same effect, explicitly
basing the definition of ‘‘net equity’’ on
17
U.S.C. 24.
E:\FR\FM\04NOR1.SGM
04NOR1
]]>Agencies
[Federal Register Volume 73, Number 214 (Tuesday, November 4, 2008)]
[Rules and Regulations]
[Pages 65511-65514]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-25891]
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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 https://
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
----------------------------------------------------------------------------------------------------------------
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
----------------------------------------------------------------------------------------------------------------
Repeat
inspection
Initial In accordance with within cycles
Engine location inspection Type action mandatory service since last
within (CSN) bulletin (MSB) inspection
(CSLI)
----------------------------------------------------------------------------------------------------------------
(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.
----------------------------------------------------------------------------------------------------------------
(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
----------------------------------------------------------------------------------------------------------------
Initial Repeat
Engine location inspection Type action In accordance with inspection
within (CSN) MSB within CSLI
----------------------------------------------------------------------------------------------------------------
(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.
----------------------------------------------------------------------------------------------------------------
[[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
----------------------------------------------------------------------------------------------------------------
Initial Repeat
Engine location inspection Type action In accordance with inspection
within (CSN) MSB within (CSLI)
----------------------------------------------------------------------------------------------------------------
(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.
----------------------------------------------------------------------------------------------------------------
(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: https://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
