Airworthiness Directives; Rolls-Royce plc RB211 Trent 875, 877, 884, 884B, 892, 892B, and 895 Series Turbofan Engines, 11585-11588 [05-4561]
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11585
Proposed Rules
Federal Register
Vol. 70, No. 45
Wednesday, March 9, 2005
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF HOMELAND
SECURITY
8 CFR Part 214
[DHS No. 2004–0033]
RIN 1615–AA82
Petitions for Aliens To Perform
Temporary Nonagricultural Services or
Labor (H–2B)
U.S. Citizenship and
Immigration Services, Department of
Homeland Security.
ACTION: Proposed rule; extension of
comment period.
AGENCY:
SUMMARY: On January 27, 2005, at 70 FR
3984, U.S. Citizenship and Immigration
Services published a proposed rule in
the Federal Register, to provide a
uniform review process governing
petitions for aliens to perform
temporary nonagricultural services or
labor. To ensure that the public has
ample opportunity to fully review and
comment on the proposed rule, DHS has
extended the comment period for this
rule for an additional 30 days. This
document informs the public that the
comment period has been extended
until April 8, 2005.
DATES: Written comments must be
submitted on or before April 8, 2005.
ADDRESSES: You may submit comments,
identified by RIN 1615–AA82 or DHS
Docket DHS–2004–0033 by one of the
following methods:
• EPA Federal Partner EDOCKET Web
site: https://www.epa.gov/feddocket.
Follow the instructions for submitting
comments on the Web site.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
• E-mail: rfs.regs@dhs.gov. When
submitting comments electronically,
please include RIN 1615–AA82 or DHS–
2004–0033 in the subject line of the
message.
• Mail/Hand-delivered/Courier:
Director, Regulatory Management
Division, Department of Homeland
Security, U.S. Citizenship and
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Immigration Services, 111
Massachusetts Avenue, NW., 3rd Floor,
Washington, DC 20529.
Instructions: All submissions received
must include the DHS–2004–0033 or
RIN 1615–AA82. All comments received
will be posted without change to
https://www.epa.gov/feddocket,
including any personal information
provided. For detailed instructions on
submitting comments and additional
information on the rulemaking process,
see the ‘‘Public Participation’’ heading
of the SUPPLEMENTARY INFORMATION
section of this document below.
Docket: For access to the docket to
read background documents or
comments received, go to https://
www.epa.gov/feddocket. You may also
access the Federal eRulemaking Portal
at https://www.regulations.gov.
Submitted comments may also be
inspected at Regulatory Management
Division, Department of Homeland
Security, U.S. Citizenship and
Immigration Services, 111
Massachusetts Avenue, NW., 2nd Floor,
Washington, DC, Monday through
Friday, except Federal holidays.
Arrangements to inspect submitted
comments should be made in advance
by calling (202) 272–8377.
FOR FURTHER INFORMATION CONTACT:
Kevin J. Cummings, Adjudications
Officer, Office of Program and
Regulation Development, U.S.
Citizenship and Immigration Services,
Department of Homeland Security, 111
Massachusetts Avenue, NW., 3rd Floor,
Washington, DC 20529, telephone (202)
353–8177.
Richard A. Sloan,
Director, Regulatory Management Division.
[FR Doc. 05–4514 Filed 3–8–05; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001–NE–17–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc RB211 Trent 875, 877, 884, 884B,
892, 892B, and 895 Series Turbofan
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to revise
an existing airworthiness directive (AD)
for Rolls-Royce plc (RR) RB211 Trent
875, 877, 884, 884B, 892, 892B, and 895
series turbofan engines with certain part
number (P/N) low pressure compressor
(LPC) fan blades installed. That AD
currently requires initial and repetitive
ultrasonic inspections of the fan blade
dovetail roots and defines a specific
terminating action to the repetitive
blade inspection requirements. This
proposed AD would require the same
actions but would clarify the
terminating action. This proposed AD
results from a request by an operator to
clarify the terminating action in the
existing AD. We are proposing this AD
to prevent multiple LPC fan blade
failures due to cracks, which could
result in uncontained engine failure and
possible damage to the airplane.
DATES: We must receive any comments
on this proposed AD by May 9, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD:
• By mail: Federal Aviation
Administration (FAA), New England
Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2001–NE–
17–AD, 12 New England Executive Park,
Burlington, MA 01803–5299.
• By fax: (781) 238–7055.
• By e-mail: 9-aneadcomment@faa.gov.
You can get the service information
identified in this proposed AD from
Rolls-Royce plc, P.O. Box 31, Derby
DE24 6BJ, UK; telephone 44 (0) 1332
242424; fax 44 (0) 1332 249936.
You may examine the AD docket, by
appointment, at the FAA, New England
Region, Office of the Regional Counsel,
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Federal Register / Vol. 70, No. 45 / Wednesday, March 9, 2005 / Proposed Rules
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:
Comments Invited
We invite you to submit any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
2001–NE–17–AD’’ in the subject line of
your comments. If you want us to
acknowledge receipt of your mailed
comments, send us a self-addressed,
stamped postcard with the docket
number written on it; we will datestamp your postcard and mail it back to
you. We specifically invite comments
on the overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. If a person contacts us
verbally, and that contact relates to a
substantive part of this proposed AD,
we will summarize the contact and
place the summary in the docket. We
will consider all comments received by
the closing date and may amend the
proposed AD in light of those
comments.
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.
Discussion
On January 3, 2005, we issued AD
2005–01–15, Amendment 39–13940 (70
FR 2336, January 13, 2005). That AD
requires initial and repetitive ultrasonic
inspections of the fan blade dovetail
roots and defines a specific terminating
action to the repetitive blade inspection
requirements. That AD results from a
report of a cracked fan blade found
before the blade reached the initial
inspection threshold of AD 2002–11–08.
That AD also resulted from the need to
reduce a repetitive inspection
compliance time due to potential
breakdown of blade coating and
lubrication on certain blades.
Actions Since AD 2005–01–15 Was
Issued
Since we issued AD 2005–01–15, we
received a comment from an operator
requesting that we clarify the
terminating action in that AD. As the
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AD is currently written, LPC fan blades
must be installed in complete sets to
comply with the terminating action. We
agree that the terminating action needs
clarification. All blades must be
replaced with blades that meet the
replacement criteria to qualify as
terminating action, but not necessarily
replaced as a complete set. We have
rewritten paragraph (h) in this proposed
AD to address the commenter’s request.
Relevant Service Information
We have reviewed and approved the
technical contents of Rolls-Royce (RR)
Alert Service Bulletin (ASB) No.
RB.211–72–AD344, Revision 7, dated
March 12, 2004, that provides
procedures to ultrasonic-inspect the
blade root on LPC fan blades. We have
also reviewed and approved the
technical contents of RR Service
Bulletin (SB) No. RB.211–72–D672,
dated February 1, 2002, that provides
procedures to rework, relubricate, and
remark the fan blades at fan blade
overhaul, and lists part numbers for new
fan blades that feature additional blade
root processing requirements. The Civil
Aviation Authority (CAA), which is the
airworthiness authority for the United
Kingdom (UK), classified these service
bulletins as mandatory and issued AD
G–2004–0008, dated April 29, 2004, in
order to ensure the airworthiness of
these RR engines in the UK.
Bilateral Agreement Information
These engine models are
manufactured in the UK and are type
certificated for operation in the United
States under the provisions of § 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 and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other products of this same
type design. Therefore, we are
proposing this AD, which would require
the following:
• Require initial and repetitive
ultrasonic-inspections of the dovetail
roots of LPC fan blades P/Ns FK30838,
FK30840, FK30842, FW12960,
FW12961, FW12962, and FW13175.
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• Define a terminating action to the
repetitive blade inspection requirements
in the AD, to be done at the next shop
visit when fan blades are removed, but
no later than December 31, 2009. The
terminating action would consist of
replacing LPC fan blades with reworked,
relubricated, and remarked LPC fan
blades, using Rolls-Royce SB No.
RB.211–72–D672, dated February 1,
2002, or with LPC fan blades that
feature additional blade root processing
requirements.
The proposed AD would require that
you do these actions using the service
information described previously.
Costs of Compliance
There are about 350 RR RB211 Trent
875, 877, 884, 884B, 892, 892B, and 895
series turbofan engines of the affected
design in the worldwide fleet. We
estimate that 90 engines installed on
airplanes of U.S. registry would be
affected by this proposed AD. We also
estimate that it would take about 8 work
hours per engine to perform the
proposed inspections, and about 260
work hours per engine to perform the
proposed terminating action. The
average labor rate is $65 per work hour.
Based on these figures, we estimate the
total cost of the proposed AD to U.S.
operators to be $1,567,800.
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
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD 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
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responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the 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. Would 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 proposal 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.
2001–NE–17–AD’’ in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
proposes to amend 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–13940 (70 FR
2336, January 13, 2005) and by adding
a new airworthiness directive, to read as
follows:
Rolls-Royce plc: Docket No. 2001–NE–17–
AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by May 9,
2005.
Affected ADs
(b) This AD revises AD 2005–01–15,
Amendment 39–13940.
Applicability
(c) This AD applies to Rolls-Royce plc (RR)
RB211 Trent 875, 877, 884, 884B, 892, 892B,
and 895 series turbofan engines with low
pressure compressor (LPC) fan blades, part
numbers (P/Ns) FK30838, FK30840,
FK30842, FW12960, FW12961, FW12962,
and FW13175, installed. These engines are
installed on, but not limited to, Boeing
Company 777 series airplanes.
11587
Unsafe Condition
(d) This AD results from a request by an
operator to clarify the terminating action in
AD 2005–01–15. We are issuing this AD to
prevent multiple LPC fan blade failures due
to cracks, which could result in uncontained
engine failure and possible 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) Ultrasonic-inspect and disposition the
dovetail roots of LPC fan blades, P/Ns
FK30838, FK30840, FK30842, FW12960,
FW12961, FW12962, and FW13175, that are
removed from the engine, using 3.A.(1)
through 3.A.(5) or, for blades that are not
removed from the engine, using 3.B.(1)
through 3.B.(5) of the Accomplishment
Instructions of RR Alert Service Bulletin
(ASB) No. RB.211–72–AD344, Revision 7,
dated March 12, 2004, as follows:
(1) For blades P/Ns FK30838, FK30840,
and FK30842, that have not been relubricated
during any interval exceeding 600 cyclessince-new (CSN) or 600 cycles-since-rework
(CSR) using either RR ASB No. RB.211–72AD344 or Service Bulletin (SB) No. RB.211–
72–D347, inspect as specified in paragraph (f)
of this AD and within the compliance times
specified in the following Table 1:
TABLE 1.—COMPLIANCE TIMES FOR BLADES P/NS FK30838, FK30840, AND FK30842
Boeing 777
series
Engine series
(i) –884B, –892 ................................................
–300
(ii) –884, –892, –892B, and –895 ...................
–200
(iii) –875 ...........................................................
(iv) –877 ...........................................................
–200
–200
(2) For blades P/Ns FK30838, FK30840,
and FK30842, that have been relubricated at
intervals not exceeding 600 CSN or 600 CSR
Initial
inspection
CSN
Airplane maximum gross weight
(times 1,000 pounds)
(A) 660 and 632.5 ...........................................
(B) 580 .............................................................
(A) 632.5 and 648 ...........................................
(B) 656 .............................................................
(C) 555 .............................................................
535 ...................................................................
545 ...................................................................
using either RR ASB No. RB.211–72–AD344
or SB No. RB.211–72–D347, inspect as
specified in paragraph (f) of this AD and
Repetitive
inspection (cyclessince-last-inspection)
(CSLI)
600
2,000
1,200
600
2,000
2,000
2,000
80
600
100
80
600
600
600
within the compliance times specified in the
following Table 2:
TABLE 2.—COMPLIANCE TIMES FOR BLADES P/NS FK30838, FK30840, AND FK30842
Boeing 777
series
Engine series
(i) –884B, 892 ..................................................
–300
(ii) –884, –892, –892B, and –895 ...................
–200
(iii) –875 ...........................................................
(iv) –877 ...........................................................
–200
–200
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Initial
inspection
CSN
Airplane maximum gross weight
(times 1,000 pounds)
(A) 660 and 632.5 ...........................................
(B) 580 .............................................................
(A) 632.5 and 648 ...........................................
(B) 656 .............................................................
(C) 555 .............................................................
535 ...................................................................
545 ...................................................................
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600
2,400
1,200
600
2,400
2,400
2,400
Repetitive
inspection
CSLI
80
600
100
80
600
600
600
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Federal Register / Vol. 70, No. 45 / Wednesday, March 9, 2005 / Proposed Rules
(3) For blades P/Ns FW12960, FW12961,
FW12962, and FW13175, either new or
reworked to that configuration at greater than
600 CSN or since previous rework, or that
have not been relubricated during any
interval exceeding 600 CSN or 600 CSR using
either RR ASB No. RB.211–72–AD344 or SB
No. RB.211–72–D347 requirements, inspect
as specified in paragraph (f) of this AD and
within the compliance times specified in the
following Table 3:
TABLE 3.—COMPLIANCE TIMES FOR BLADES P/NS FW12960, FW12961, FW12962, AND FW13175
Boeing 777
series
Engine series
(i) –884B, –892 ................................................
–300
(ii) –884, –892, –892B and –895 ....................
–200
(iii) –875 ...........................................................
(iv) –877 ...........................................................
–200
–200
(4) For blades P/Ns FW12960, FW12961,
FW12962, and FW13175, either new or
reworked to that configuration at fewer than
600 CSN or since previous rework, and that
Initial
inspection
CSN
Airplane maximum gross weight
(times 1,000 pounds)
(A) 660 and 632.5 ...........................................
(B) 580 .............................................................
(A) 632.5 and 648 ...........................................
(B) 656 .............................................................
(C) 555 .............................................................
535 ...................................................................
545 ...................................................................
have been relubricated at intervals not
exceeding 600 CSN using either RR ASB No.
RB.211–72–AD344 or SB No. RB.211–72–
D347, inspect as specified in paragraph (f) of
Repetitive
inspection
CSLI
600
2,000
1,200
600
2,000
2,000
2,000
100
600
125
100
600
600
600
this AD and within the compliance times
specified in the following Table 4:
TABLE 4.—COMPLIANCE TIMES FOR BLADES P/NS FW12960, FW12961, FW12962, AND FW13175
Boeing 777
series
Engine series
(i) –884B, –892 ................................................
–300
(ii) –884, –892, –892B, and –895 ...................
–200
(iii) –875 ...........................................................
(iv) –877 ...........................................................
–200
–200
(g) When engines containing blades P/Ns
FK30838, FK30840, FK30842, FW12960,
FW12961, FW12962, and FW13175 are
moved from one gross weight category to
another, the inspection schedule that is
applicable to the higher gross weight category
must be used.
Terminating Action
(h) As terminating action to the repetitive
inspection requirements of this AD, at the
next shop visit when the LPC fan blades are
removed for repair or overhaul, but no later
than December 31, 2009:
(1) Replace LPC fan blades P/Ns FK30838,
FK30840, FK30842, FW12960, FW12961,
FW12962, or FW13175, with serviceable LPC
fan blades.
(2) For the purposes of this AD, serviceable
LPC fan blades are blades that feature
additional blade root processing
requirements found in RR SB No. RB.211–
72–D672, dated February 1, 2002; or are LPC
fan blades that feature a full form root profile.
Information on full form root profile blades
can be found in RR SB No. RB.211–72–D390,
RR SB No. RB.211–72–E044, and RR SB No.
RB.211–72–E382.
(A) 660 and 632.5 ...........................................
(B) 580 .............................................................
(A) 632.5 and 648 ...........................................
(B) 656 .............................................................
(C) 555 .............................................................
535 ...................................................................
545 ...................................................................
March 12, 2004, before the effective date of
this AD.
Alternative Methods of Compliance
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Repetitive
inspection
CSLI
600
2,400
2,400
600
2,400
2,400
2,400
100
1,200
125
100
1,200
1,200
600
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
(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.
14 CFR Part 39
Related Information
Airworthiness Directives; Kelly
Aerospace Power Systems Part
Number (P/N) 14D11, A14D11, B14D11,
C14D11, 23D04, A23D04, B23D04,
C23D04, or P23D04 Fuel Regulator
Shutoff Valves (formerly owned by
ElectroSystems, JanAero Devices,
Janitrol, C&D Airmotive Products, FL
Aerospace, and Midland-Ross
Corporation)
(k) Civil Aviation Authority (CAA)
airworthiness directive G–2004–0008, dated
April 29, 2004, also addresses the subject of
this AD.
Issued in Burlington, Massachusetts, on
March 2, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 05–4561 Filed 3–8–05; 8:45 am]
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[Docket No. FAA–2004–19693; Directorate
Identifier 2004–CE–40–AD]
RIN 2120–AA64
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to revise
Airworthiness Directive (AD) 2004–25–
16, which applies to aircraft equipped
with a fuel regulator shutoff valve part
number (P/N) 14D11, A14D11, B14D11,
C14D11, 23D04, A23D04, B23D04,
C23D04, or P23D04 used with B1500,
Previous Credit
(i) Previous credit is allowed for initial
inspections of fan blades that were done
using RR ASB No. RB.211–72–AD344,
Revision 4, dated March 15, 2002, Revision
5, dated June 20, 2003, Revision 6, dated
February 27, 2004, or Revision 7, dated
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inspection
CSN
Airplane maximum gross weight
(times 1,000 pounds)
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]]>Agencies
[Federal Register Volume 70, Number 45 (Wednesday, March 9, 2005)]
[Proposed Rules]
[Pages 11585-11588]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-4561]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NE-17-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Trent 875, 877,
884, 884B, 892, 892B, and 895 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to revise an existing airworthiness directive
(AD) for Rolls-Royce plc (RR) RB211 Trent 875, 877, 884, 884B, 892,
892B, and 895 series turbofan engines with certain part number (P/N)
low pressure compressor (LPC) fan blades installed. That AD currently
requires initial and repetitive ultrasonic inspections of the fan blade
dovetail roots and defines a specific terminating action to the
repetitive blade inspection requirements. This proposed AD would
require the same actions but would clarify the terminating action. This
proposed AD results from a request by an operator to clarify the
terminating action in the existing AD. We are proposing this AD to
prevent multiple LPC fan blade failures due to cracks, which could
result in uncontained engine failure and possible damage to the
airplane.
DATES: We must receive any comments on this proposed AD by May 9, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2001-NE-17-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
You can get the service information identified in this proposed AD
from Rolls-Royce plc, P.O. Box 31, Derby DE24 6BJ, UK; telephone 44 (0)
1332 242424; fax 44 (0) 1332 249936.
You may examine the AD docket, by appointment, at the FAA, New
England Region, Office of the Regional Counsel,
[[Page 11586]]
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:
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2001-NE-17-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it; we will date-stamp your postcard and
mail it back to you. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. If a person contacts us verbally, and that contact relates to a
substantive part of this proposed AD, we will summarize the contact and
place the summary in the docket. We will consider all comments received
by the closing date and may amend the proposed AD in light of those
comments.
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.
Discussion
On January 3, 2005, we issued AD 2005-01-15, Amendment 39-13940 (70
FR 2336, January 13, 2005). That AD requires initial and repetitive
ultrasonic inspections of the fan blade dovetail roots and defines a
specific terminating action to the repetitive blade inspection
requirements. That AD results from a report of a cracked fan blade
found before the blade reached the initial inspection threshold of AD
2002-11-08. That AD also resulted from the need to reduce a repetitive
inspection compliance time due to potential breakdown of blade coating
and lubrication on certain blades.
Actions Since AD 2005-01-15 Was Issued
Since we issued AD 2005-01-15, we received a comment from an
operator requesting that we clarify the terminating action in that AD.
As the AD is currently written, LPC fan blades must be installed in
complete sets to comply with the terminating action. We agree that the
terminating action needs clarification. All blades must be replaced
with blades that meet the replacement criteria to qualify as
terminating action, but not necessarily replaced as a complete set. We
have rewritten paragraph (h) in this proposed AD to address the
commenter's request.
Relevant Service Information
We have reviewed and approved the technical contents of Rolls-Royce
(RR) Alert Service Bulletin (ASB) No. RB.211-72-AD344, Revision 7,
dated March 12, 2004, that provides procedures to ultrasonic-inspect
the blade root on LPC fan blades. We have also reviewed and approved
the technical contents of RR Service Bulletin (SB) No. RB.211-72-D672,
dated February 1, 2002, that provides procedures to rework,
relubricate, and remark the fan blades at fan blade overhaul, and lists
part numbers for new fan blades that feature additional blade root
processing requirements. The Civil Aviation Authority (CAA), which is
the airworthiness authority for the United Kingdom (UK), classified
these service bulletins as mandatory and issued AD G-2004-0008, dated
April 29, 2004, in order to ensure the airworthiness of these RR
engines in the UK.
Bilateral Agreement Information
These engine models are manufactured in the UK and are type
certificated for operation in the United States under the provisions of
Sec. 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 and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. Therefore, we are proposing this AD, which
would require the following:
Require initial and repetitive ultrasonic-inspections of
the dovetail roots of LPC fan blades P/Ns FK30838, FK30840, FK30842,
FW12960, FW12961, FW12962, and FW13175.
Define a terminating action to the repetitive blade
inspection requirements in the AD, to be done at the next shop visit
when fan blades are removed, but no later than December 31, 2009. The
terminating action would consist of replacing LPC fan blades with
reworked, relubricated, and remarked LPC fan blades, using Rolls-Royce
SB No. RB.211-72-D672, dated February 1, 2002, or with LPC fan blades
that feature additional blade root processing requirements.
The proposed AD would require that you do these actions using the
service information described previously.
Costs of Compliance
There are about 350 RR RB211 Trent 875, 877, 884, 884B, 892, 892B,
and 895 series turbofan engines of the affected design in the worldwide
fleet. We estimate that 90 engines installed on airplanes of U.S.
registry would be affected by this proposed AD. We also estimate that
it would take about 8 work hours per engine to perform the proposed
inspections, and about 260 work hours per engine to perform the
proposed terminating action. The average labor rate is $65 per work
hour. Based on these figures, we estimate the total cost of the
proposed AD to U.S. operators to be $1,567,800.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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
[[Page 11587]]
responsibilities among the various levels of government.
For the reasons discussed above, I certify that the 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. Would 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 proposal 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. 2001-NE-17-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 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. The FAA amends Sec. 39.13 by removing Amendment 39-13940 (70 FR
2336, January 13, 2005) and by adding a new airworthiness directive, to
read as follows:
Rolls-Royce plc: Docket No. 2001-NE-17-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by May 9, 2005.
Affected ADs
(b) This AD revises AD 2005-01-15, Amendment 39-13940.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 875,
877, 884, 884B, 892, 892B, and 895 series turbofan engines with low
pressure compressor (LPC) fan blades, part numbers (P/Ns) FK30838,
FK30840, FK30842, FW12960, FW12961, FW12962, and FW13175, installed.
These engines are installed on, but not limited to, Boeing Company
777 series airplanes.
Unsafe Condition
(d) This AD results from a request by an operator to clarify the
terminating action in AD 2005-01-15. We are issuing this AD to
prevent multiple LPC fan blade failures due to cracks, which could
result in uncontained engine failure and possible 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) Ultrasonic-inspect and disposition the dovetail roots of LPC
fan blades, P/Ns FK30838, FK30840, FK30842, FW12960, FW12961,
FW12962, and FW13175, that are removed from the engine, using
3.A.(1) through 3.A.(5) or, for blades that are not removed from the
engine, using 3.B.(1) through 3.B.(5) of the Accomplishment
Instructions of RR Alert Service Bulletin (ASB) No. RB.211-72-AD344,
Revision 7, dated March 12, 2004, as follows:
(1) For blades P/Ns FK30838, FK30840, and FK30842, that have not
been relubricated during any interval exceeding 600 cycles-since-new
(CSN) or 600 cycles-since-rework (CSR) using either RR ASB No.
RB.211-72-AD344 or Service Bulletin (SB) No. RB.211-72-D347, inspect
as specified in paragraph (f) of this AD and within the compliance
times specified in the following Table 1:
Table 1.--Compliance Times for Blades P/Ns FK30838, FK30840, and FK30842
----------------------------------------------------------------------------------------------------------------
Repetitive
Airplane maximum gross Initial inspection
Engine series Boeing 777 weight (times 1,000 inspection (cycles-since-
series pounds) CSN last-inspection)
(CSLI)
----------------------------------------------------------------------------------------------------------------
(i) -884B, -892........................ -300 (A) 660 and 632.5......... 600 80
(B) 580................... 2,000 600
(ii) -884, -892, -892B, and -895....... -200 (A) 632.5 and 648......... 1,200 100
........... (B) 656................... 600 80
(C) 555................... 2,000 600
(iii) -875............................. -200 535....................... 2,000 600
(iv) -877.............................. -200 545....................... 2,000 600
----------------------------------------------------------------------------------------------------------------
(2) For blades P/Ns FK30838, FK30840, and FK30842, that have
been relubricated at intervals not exceeding 600 CSN or 600 CSR
using either RR ASB No. RB.211-72-AD344 or SB No. RB.211-72-D347,
inspect as specified in paragraph (f) of this AD and within the
compliance times specified in the following Table 2:
Table 2.--Compliance Times for Blades P/Ns FK30838, FK30840, and FK30842
----------------------------------------------------------------------------------------------------------------
Airplane maximum gross Initial
Engine series Boeing 777 weight (times 1,000 inspection Repetitive
series pounds) CSN inspection CSLI
----------------------------------------------------------------------------------------------------------------
(i) -884B, 892......................... -300 (A) 660 and 632.5......... 600 80
(B) 580................... 2,400 600
(ii) -884, -892, -892B, and -895....... -200 (A) 632.5 and 648......... 1,200 100
........... (B) 656................... 600 80
(C) 555................... 2,400 600
(iii) -875............................. -200 535....................... 2,400 600
(iv) -877.............................. -200 545....................... 2,400 600
----------------------------------------------------------------------------------------------------------------
[[Page 11588]]
(3) For blades P/Ns FW12960, FW12961, FW12962, and FW13175,
either new or reworked to that configuration at greater than 600 CSN
or since previous rework, or that have not been relubricated during
any interval exceeding 600 CSN or 600 CSR using either RR ASB No.
RB.211-72-AD344 or SB No. RB.211-72-D347 requirements, inspect as
specified in paragraph (f) of this AD and within the compliance
times specified in the following Table 3:
Table 3.--Compliance Times for Blades P/Ns FW12960, FW12961, FW12962, and FW13175
----------------------------------------------------------------------------------------------------------------
Airplane maximum gross Initial
Engine series Boeing 777 weight (times 1,000 inspection Repetitive
series pounds) CSN inspection CSLI
----------------------------------------------------------------------------------------------------------------
(i) -884B, -892........................ -300 (A) 660 and 632.5......... 600 100
(B) 580................... 2,000 600
(ii) -884, -892, -892B and -895........ -200 (A) 632.5 and 648......... 1,200 125
........... (B) 656................... 600 100
(C) 555................... 2,000 600
(iii) -875............................. -200 535....................... 2,000 600
(iv) -877.............................. -200 545....................... 2,000 600
----------------------------------------------------------------------------------------------------------------
(4) For blades P/Ns FW12960, FW12961, FW12962, and FW13175,
either new or reworked to that configuration at fewer than 600 CSN
or since previous rework, and that have been relubricated at
intervals not exceeding 600 CSN using either RR ASB No. RB.211-72-
AD344 or SB No. RB.211-72-D347, inspect as specified in paragraph
(f) of this AD and within the compliance times specified in the
following Table 4:
Table 4.--Compliance Times for Blades P/Ns FW12960, FW12961, FW12962, and FW13175
----------------------------------------------------------------------------------------------------------------
Airplane maximum gross Initial
Engine series Boeing 777 weight (times 1,000 inspection Repetitive
series pounds) CSN inspection CSLI
----------------------------------------------------------------------------------------------------------------
(i) -884B, -892........................ -300 (A) 660 and 632.5........ 600 100
(B) 580................... 2,400 1,200
(ii) -884, -892, -892B, and -895....... -200 (A) 632.5 and 648......... 2,400 125
........... (B) 656................... 600 100
(C) 555................... 2,400 1,200
(iii) -875............................. -200 535....................... 2,400 1,200
(iv) -877.............................. -200 545....................... 2,400 600
----------------------------------------------------------------------------------------------------------------
(g) When engines containing blades P/Ns FK30838, FK30840,
FK30842, FW12960, FW12961, FW12962, and FW13175 are moved from one
gross weight category to another, the inspection schedule that is
applicable to the higher gross weight category must be used.
Terminating Action
(h) As terminating action to the repetitive inspection
requirements of this AD, at the next shop visit when the LPC fan
blades are removed for repair or overhaul, but no later than
December 31, 2009:
(1) Replace LPC fan blades P/Ns FK30838, FK30840, FK30842,
FW12960, FW12961, FW12962, or FW13175, with serviceable LPC fan
blades.
(2) For the purposes of this AD, serviceable LPC fan blades are
blades that feature additional blade root processing requirements
found in RR SB No. RB.211-72-D672, dated February 1, 2002; or are
LPC fan blades that feature a full form root profile. Information on
full form root profile blades can be found in RR SB No. RB.211-72-
D390, RR SB No. RB.211-72-E044, and RR SB No. RB.211-72-E382.
Previous Credit
(i) Previous credit is allowed for initial inspections of fan
blades that were done using RR ASB No. RB.211-72-AD344, Revision 4,
dated March 15, 2002, Revision 5, dated June 20, 2003, Revision 6,
dated February 27, 2004, or Revision 7, dated March 12, 2004, before
the effective date of this AD.
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.
Related Information
(k) Civil Aviation Authority (CAA) airworthiness directive G-
2004-0008, dated April 29, 2004, also addresses the subject of this
AD.
Issued in Burlington, Massachusetts, on March 2, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 05-4561 Filed 3-8-05; 8:45 am]
BILLING CODE 4910-13-P
