Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series Turbofan Engines, 73576-73577 [05-23834]
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<![CDATA[
73576
Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations
Contact Rolls-Royce plc,
P.O. Box 31, Derby, England, DE248BJ;
telephone: 011–44–1332–242424; fax:
011–44–1332–245418, for the service
Maximum
Number of flights in Monte
acceptable fuel
information identified in this AD.
Carlo analysis
tank flammability
You may examine the AD docket at
(percent)
the FAA, New England Region, Office of
100,000 .............................
2.98 the Regional Counsel, 12 New England
1,000,000 ..........................
3.00 Executive Park, Burlington, MA. You
may examine the service information, at
the FAA, New England Region, Office of
Issued in Renton, Washington, on
the Regional Counsel, 12 New England
December 5, 2005.
Executive Park, Burlington, MA.
Ali Bahrami,
FOR FURTHER INFORMATION CONTACT:
Manager, Transport Airplane Directorate,
Christopher Spinney, Aerospace
Aircraft Certification Service.
Engineer, Engine Certification Office,
[FR Doc. 05–23936 Filed 12–12–05; 8:45 am]
FAA, Engine And Propeller Directorate,
BILLING CODE 4910–13–P
12 New England Executive Park;
Burlington, MA 01803–5299; telephone
(781) 238–7175; fax (781) 238–7199.
DEPARTMENT OF TRANSPORTATION
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR Part 39 with
Federal Aviation Administration
a new AD, applicable to RR models
RB211 Trent 875–17, Trent 877–17,
14 CFR Part 39
Trent 884–17, Trent 884B–17, Trent
[Docket No. 2003–NE–38–AD; Amendment
892–17, Trent 892B–17, and Trent 895–
39–14404; AD 2005–25–11]
17 turbofan engines with LP compressor
RIN 2120–AA64
fan blades, P/N FW18548 installed. We
published the proposed AD in the
Airworthiness Directives; Rolls-Royce
Federal Register on May 27, 2005 (70
plc RB211 Trent 800 Series Turbofan
FR 30653). That action proposed to
Engines
require LP compressor fan blade
replacement with new or previously
AGENCY: Federal Aviation
reworked blades, or rework of the
Administration (FAA), DOT.
existing LP compressor fan blades, at
ACTION: Final rule.
reduced compliance times from the
previous AD, for certain airplane and
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for engine rating combinations and certain
maximum gross weight limits.
Rolls-Royce plc (RR) models RB211
Trent 875–17, Trent 877–17, Trent 884– Examining the AD Docket
17, Trent 884B–17, Trent 892–17, Trent
You may examine the AD Docket
892B–17, and Trent 895–17 turbofan
(including any comments and service
engines with low pressure (LP)
information), by appointment, between
compressor fan blades, part number (P/
8 a.m. and 4:30 p.m., Monday through
N) FW18548 installed. That AD
Friday, except Federal holidays. See
currently requires LP compressor fan
ADDRESSES for the location.
blade replacement with new or
previously reworked blades, or rework
Comments
of the existing LP compressor fan
We provided the public the
blades. This ad requires the same
actions but at reduced compliance times opportunity to participate in the
development of this AD. We considered
for certain airplane and engine rating
the one comment received. The
combinations and certain maximum
commenter supports the proposal.
gross weight limits. This AD results
from a number of new production LP
Conclusion
compressor fan blades found with
We carefully reviewed the available
surfaces formed outside of design intent. data, including the comment received,
We are issuing this AD to prevent
and determined that air safety and the
possible multiple uncontained LP
public interest require adopting the AD
compressor fan blade failure, due to
as proposed.
cracking in the blade root caused by
increased stresses in the shear key slots. Costs of Compliance
DATES: This AD becomes effective
About 392 RR RB211 Trent 800 series
January 17, 2006. The Director of the
turbofan engines of the affected design
Federal Register approved the
are in the worldwide fleet. About 106
incorporation by reference of certain
engines installed on airplanes of U.S.
publications listed in the regulations as
registry will be affected by this AD. We
of January 17, 2006.
estimate about 100 work hours per
TABLE 6.—FLAMMABILITY LIMIT—
Continued
VerDate Aug<31>2005
16:47 Dec 12, 2005
Jkt 208001
ADDRESSES:
PO 00000
Frm 00024
Fmt 4700
Sfmt 4700
engine are needed to perform blade
rework, and that the average labor rate
is $65 per work hour. Based on these
figures, we estimate the total cost of the
AD to U.S. operators to be $689,000.
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 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 by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘AD Docket No. 2003–NE–38–
AD’’ in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
I
E:\FR\FM\13DER1.SGM
13DER1
73577
Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations
Effective Date
(a) This AD becomes effective January 17,
2006.
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
Affected ADs
(b) This AD supersedes AD 2004–15–02,
Amendment 39–13736.
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–13736 (69 FR
44925, August 12, 2004) and by adding
a new airworthiness directive,
Amendment 39–14404, to read as
follows:
I
2005–25–11 Rolls-Royce plc: Amendment
39–14404. Docket No. 2003–NE–38–AD.
Applicability
(c) This AD applies to Rolls-Royce plc (RR)
models RB211 Trent 875–17, Trent 877–17,
Trent 884–17, Trent 884B–17, Trent 892–17,
Trent 892B–17, and Trent 895–17 turbofan
engines, with low pressure (LP) compressor
fan blades, part number FW18548 installed.
These engines are installed on, but not
limited to, Boeing 777 series airplanes.
Unsafe Condition
(d) This AD results from a number of new
production LP compressor blades found with
surfaces formed outside of design intent. We
are issuing this AD to prevent possible
multiple uncontained LP compressor fan
blade failure, due to cracking in the blade
root caused by increased stresses in the shear
key slots.
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.
Actions Required for LP Compressor Fan
Blades
(f) Replace LP compressor fan blades with
new or previously reworked LP compressor
blades before accumulating the specified
cycles-since-new (CSN) in the following
Table 1, or rework the existing blades as
specified in paragraph (g) of this AD.
TABLE 1.—LP COMPRESSOR FAN BLADE REPLACEMENT OR REWORK SCHEDULE
Airplane
maximum gross
weight
(times 1,000
pounds)
Boeing 777 Series:
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
(g) Rework LP compressor fan blades at or
before accumulating the specified CSN in
Table 1 of this AD. Follow paragraphs 3.B.(1)
through 3.B.(22) of Accomplishment
Instructions of RR service bulletin (SB) No.
RB.211–72–E044, Revision 2, dated October
8, 2004, to do the blade rework.
(h) For engines moved between
configurations, calculate the cycles
remaining using either of the following:
(1) Subtract the total CSN from the most
limiting configuration’s limit from Table 1 of
this AD; or
(2) Calculate the cycles remaining using
the following equation:
X X
X
X r = Lc 1 − 1 + 2 + 3 + .....
L1 L 2 L3
Where:
Xr = Cycles remaining in current
configuration.
Lc = Cyclic limit of current configuration
from Table 1 of this AD.
Xn = Cycles accumulated in configuration n.
Ln = Cyclic limit in configuration n from
Table 1 of this AD.
(i) Information on the source life of the
cycle limits in Table 1 of this AD can be
found in RR Alert SB No. RB.211–72–AE055,
Revision 3, dated May 28, 2004.
VerDate Aug<31>2005
16:47 Dec 12, 2005
Jkt 208001
660, 632.5
656
648
632.5
632.5
555
545
535
506
–884, –892, –884B
–892, –895
–892, –892B
–892B
–892
–884
–877
–875
–875
Replace or
rework LP
compressor fan
blades before
accumulating:
2,400
2,400
3,200
3,200
4,100
4,100
4,100
4,100
4,100
CSN.
CSN.
CSN.
CSN.
CSN.
CSN.
CSN.
CSN.
CSN.
Alternative Methods of Compliance
(j) 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.
Issued in Burlington, Massachusetts, on
December 5, 2005.
Carlos Pestana,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–23834 Filed 12–12–05; 8:45 am]
Material Incorporated by Reference
(k) You must use Rolls-Royce plc Service
Bulletin No. RB.211–72–E044, Revision 2,
dated October 8, 2004, to perform the blade
rework 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. You can get a copy from
Rolls-Royce plc, PO Box 31, Derby, England,
DE248BJ; telephone: 011–44–1332–242424;
fax: 011–44–1332–245418. You can review a
copy at the FAA, New England Region, Office
of the Regional Counsel, 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.
BILLING CODE 4910–13–P
Related Information
(l) CAA airworthiness directive G–2004–
030, dated December 23, 2004, and RR Alert
SB No. RB.211–72–AE055, Revision 4, dated
December 9, 2004, pertain to the subject of
this AD.
PO 00000
Frm 00025
Fmt 4700
Sfmt 4700
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22560; Directorate
Identifier 2005–NM–061–AD; Amendment
39–14408; AD 2005–25–15]
RIN 2120–AA64
Airworthiness Directives; Dassault
Model Falcon 2000 Airplanes Equipped
With CFE Company CFE738–1–1B
Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
E:\FR\FM\13DER1.SGM
13DER1
ER13DE05.008</GPH>
–300
–200
–200
–200
–200
–200
–200
–200
–200
RB211 Trent Engine
Model
]]>Agencies
[Federal Register Volume 70, Number 238 (Tuesday, December 13, 2005)]
[Rules and Regulations]
[Pages 73576-73577]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23834]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NE-38-AD; Amendment 39-14404; AD 2005-25-11]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Rolls-Royce plc (RR) models RB211 Trent 875-17, Trent 877-17,
Trent 884-17, Trent 884B-17, Trent 892-17, Trent 892B-17, and Trent
895-17 turbofan engines with low pressure (LP) compressor fan blades,
part number (P/N) FW18548 installed. That AD currently requires LP
compressor fan blade replacement with new or previously reworked
blades, or rework of the existing LP compressor fan blades. This ad
requires the same actions but at reduced compliance times for certain
airplane and engine rating combinations and certain maximum gross
weight limits. This AD results from a number of new production LP
compressor fan blades found with surfaces formed outside of design
intent. We are issuing this AD to prevent possible multiple uncontained
LP compressor fan blade failure, due to cracking in the blade root
caused by increased stresses in the shear key slots.
DATES: This AD becomes effective January 17, 2006. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of January 17, 2006.
ADDRESSES: Contact Rolls-Royce plc, P.O. Box 31, Derby, England,
DE248BJ; telephone: 011-44-1332-242424; fax: 011-44-1332-245418, for
the service information identified in this AD.
You may examine the AD docket at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA. You may examine the service information, at the FAA,
New England Region, Office of the Regional Counsel, 12 New England
Executive Park, Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine And Propeller
Directorate, 12 New England Executive Park; Burlington, MA 01803-5299;
telephone (781) 238-7175; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39
with a new AD, applicable to RR models RB211 Trent 875-17, Trent 877-
17, Trent 884-17, Trent 884B-17, Trent 892-17, Trent 892B-17, and Trent
895-17 turbofan engines with LP compressor fan blades, P/N FW18548
installed. We published the proposed AD in the Federal Register on May
27, 2005 (70 FR 30653). That action proposed to require LP compressor
fan blade replacement with new or previously reworked blades, or rework
of the existing LP compressor fan blades, at reduced compliance times
from the previous AD, for certain airplane and engine rating
combinations and certain maximum gross weight limits.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Comments
We provided the public the opportunity to participate in the
development of this AD. We considered the one comment received. The
commenter supports the proposal.
Conclusion
We carefully reviewed the available data, including the comment
received, and determined that air safety and the public interest
require adopting the AD as proposed.
Costs of Compliance
About 392 RR RB211 Trent 800 series turbofan engines of the
affected design are in the worldwide fleet. About 106 engines installed
on airplanes of U.S. registry will be affected by this AD. We estimate
about 100 work hours per engine are needed to perform blade rework, and
that the average labor rate is $65 per work hour. Based on these
figures, we estimate the total cost of the AD to U.S. operators to be
$689,000.
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 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 by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2003-NE-38-AD'' in your request.
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,
[[Page 73577]]
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:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-13736 (69 FR
44925, August 12, 2004) and by adding a new airworthiness directive,
Amendment 39-14404, to read as follows:
2005-25-11 Rolls-Royce plc: Amendment 39-14404. Docket No. 2003-NE-
38-AD.
Effective Date
(a) This AD becomes effective January 17, 2006.
Affected ADs
(b) This AD supersedes AD 2004-15-02, Amendment 39-13736.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) models RB211 Trent
875-17, Trent 877-17, Trent 884-17, Trent 884B-17, Trent 892-17,
Trent 892B-17, and Trent 895-17 turbofan engines, with low pressure
(LP) compressor fan blades, part number FW18548 installed. These
engines are installed on, but not limited to, Boeing 777 series
airplanes.
Unsafe Condition
(d) This AD results from a number of new production LP
compressor blades found with surfaces formed outside of design
intent. We are issuing this AD to prevent possible multiple
uncontained LP compressor fan blade failure, due to cracking in the
blade root caused by increased stresses in the shear key slots.
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.
Actions Required for LP Compressor Fan Blades
(f) Replace LP compressor fan blades with new or previously
reworked LP compressor blades before accumulating the specified
cycles-since-new (CSN) in the following Table 1, or rework the
existing blades as specified in paragraph (g) of this AD.
Table 1.--LP Compressor Fan Blade Replacement or Rework Schedule
----------------------------------------------------------------------------------------------------------------
Airplane maximum Replace or rework LP
Boeing 777 Series: gross weight (times RB211 Trent Engine Model compressor fan blades
1,000 pounds) before accumulating:
----------------------------------------------------------------------------------------------------------------
-300.......................... 660, 632.5 -884, -892, -884B 2,400 CSN.
-200.......................... 656 -892, -895 2,400 CSN.
-200.......................... 648 -892, -892B 3,200 CSN.
-200.......................... 632.5 -892B 3,200 CSN.
-200.......................... 632.5 -892 4,100 CSN.
-200.......................... 555 -884 4,100 CSN.
-200.......................... 545 -877 4,100 CSN.
-200.......................... 535 -875 4,100 CSN.
-200.......................... 506 -875 4,100 CSN.
----------------------------------------------------------------------------------------------------------------
(g) Rework LP compressor fan blades at or before accumulating
the specified CSN in Table 1 of this AD. Follow paragraphs 3.B.(1)
through 3.B.(22) of Accomplishment Instructions of RR service
bulletin (SB) No. RB.211-72-E044, Revision 2, dated October 8, 2004,
to do the blade rework.
(h) For engines moved between configurations, calculate the
cycles remaining using either of the following:
(1) Subtract the total CSN from the most limiting
configuration's limit from Table 1 of this AD; or
(2) Calculate the cycles remaining using the following equation:
[GRAPHIC] [TIFF OMITTED] TR13DE05.008
Where:
Xr = Cycles remaining in current configuration.
Lc = Cyclic limit of current configuration from Table 1 of this AD.
Xn = Cycles accumulated in configuration n.
Ln = Cyclic limit in configuration n from Table 1 of this AD.
(i) Information on the source life of the cycle limits in Table
1 of this AD can be found in RR Alert SB No. RB.211-72-AE055,
Revision 3, dated May 28, 2004.
Alternative Methods of Compliance
(j) 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.
Material Incorporated by Reference
(k) You must use Rolls-Royce plc Service Bulletin No. RB.211-72-
E044, Revision 2, dated October 8, 2004, to perform the blade rework
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. You can get a
copy from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ;
telephone: 011-44-1332-242424; fax: 011-44-1332-245418. You can
review a copy at the FAA, New England Region, Office of the Regional
Counsel, 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.
Related Information
(l) CAA airworthiness directive G-2004-030, dated December 23,
2004, and RR Alert SB No. RB.211-72-AE055, Revision 4, dated
December 9, 2004, pertain to the subject of this AD.
Issued in Burlington, Massachusetts, on December 5, 2005.
Carlos Pestana,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-23834 Filed 12-12-05; 8:45 am]
BILLING CODE 4910-13-P
