Airworthiness Directives; Rolls-Royce plc RB211 Trent 875, 877, 884, 884B, 892, 892B, and 895 Series Turbofan Engines, 2336-2339 [05-485]
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Federal Register / Vol. 70, No. 9 / Thursday, January 13, 2005 / Rules and Regulations
TABLE 1.—INCORPORATION BY REFERENCE—Continued
Mandatory service bulletin No.
Page
Revision
Date
Total Pages: 5
Related Information
(j) United Kingdom Civil Aviation
Authority airworthiness directive 003–11–99
also addresses the subject of this AD.
Issued in Burlington, Massachusetts, on
January 4, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–484 Filed 1–12–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001–NE–17–AD; Amendment
39–13940; AD 2005–01–15]
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: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
Rolls-Royce plc (RR) RB211 Trent 875,
877, 884, 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. This AD requires the
same actions except at reduced
compliance times for certain blades,
defines a specific terminating action to
the repetitive blade inspection
requirements, and adds the 884B series
to the applicability. This AD results
from a report of a cracked fan blade
found before the blade reached the
initial inspection threshold of AD 2002–
11–08. This AD also results from the
need to reduce a repetitive inspection
compliance time due to potential
breakdown of blade coating and
lubrication on certain blades. 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.
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14:42 Jan 12, 2005
Jkt 205001
Effective January 28, 2005. The
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulations as of January 28, 2005.
We must receive any comments on
this AD by March 14, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
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
referenced in this 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,
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: On May
27, 2002, the FAA issued AD 2002–11–
08, Amendment 39–12769 (67 FR
38852, June 6, 2002). That AD requires
initial and repetitive ultrasonic
inspections of the fan blade dovetail
roots. That AD was the result of the loss
of an LPC fan blade during takeoff. That
condition, if not corrected, could result
in multiple LPC fan blade failures due
to cracks, which could result in
uncontained engine failure and possible
damage to the airplane.
DATES:
Actions Since AD 2002–11–08 Was
Issued
Since that AD was issued, the Civil
Aviation Authority (CAA), which is the
airworthiness authority for the United
Kingdom (UK), notified us that an
unsafe condition may exist on RR
RB211 Trent 875, 877, 884, 884B, 892,
892B, and 895 series turbofan engines.
The CAA advises that a cracked fan
blade was found before the blade
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reached the initial inspection threshold
specified in AD 2002–11–08. The CAA
also advises that potential breakdown of
blade coating and lubrication on certain
blades might occur, leading to blade
cracking.
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 CAA
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 Airworthiness Agreement
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 This AD
The unsafe condition described
previously is likely to exist or develop
on other RR RB211 Trent 875, 877, 884,
884B, 892, 892B, and 895 series
turbofan engines of the same type
design. 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. This AD:
• Requires initial and repetitive
ultrasonic-inspections of the dovetail
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Federal Register / Vol. 70, No. 9 / Thursday, January 13, 2005 / Rules and Regulations
roots of LPC fan blades P/Ns FK30838,
FK30840, FK30842, FW12960,
FW12961, FW12962, and FW13175.
• Reduces the initial inspection
threshold for fan blades, P/Ns FK30838,
FK30840, and FK30842 in Table 1 for
Airplane Maximum Gross Weight of
632,500 pounds and 648,000 pounds,
from 2,400 cycles-since-new (CSN) to
1,200 CSN.
• Reduces the repetitive inspection
threshold for fan blades, P/Ns FW12960,
FW12961, FW12962, and FW13175 in
Table 4 for Airplane Maximum Gross
Weight of 545,000 pounds from 1,200
CSN to 600 CSN.
• Defines 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 consists of replacing
LPC fan blades with a complete set of
reworked, relubricated, and remarked
LPC fan blades, using Rolls-Royce SB
No. RB.211–72–D672, dated February 1,
2002, or with a complete set of new LPC
fan blades that feature additional blade
root processing requirements.
• Adds the 884B series engine to the
applicability.
You must use the service information
described previously to perform the
actions required by this AD.
FAA’s Determination of the Effective
Date
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we have found that notice and
opportunity for public comment before
issuing this AD are impracticable, and
that good cause exists for making this
amendment effective in less than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
written relevant data, views, or
arguments regarding this AD. 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 rule that might suggest a need to
modify it. If a person contacts us
verbally, and that contact relates to a
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14:42 Jan 12, 2005
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substantive part of this 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 AD in
light of those comments.
We are reviewing the writing style we
currently use in regulatory documents.
We are interested in your comments on
whether the style of this document is
clear, and your suggestions to improve
the clarity of our communications with
you. You may get more information
about plain language at https://
www.faa.gov/language and https://
www.plainlanguage.gov.
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.
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 the 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. Will not have a significant
economic impact, positive or negative,
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2337
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. 2001–NE–17–
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,
the FAA amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
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 Federal Aviation
Administration (FAA) amends § 39.13 by
removing Amendment 39–12769 (67 FR
38852; June 6, 2002), and by adding a
new airworthiness directive (AD),
Amendment 39–13940, to read as
follows:
I
2005–01–15 Rolls-Royce plc: Amendment
39–13940. Docket No. 2001–NE–17–AD.
Supersedes AD 2002–11–08,
Amendment 39–12769.
Effective Date
(a) This AD becomes effective January 28,
2005.
Affected ADs
(b) This AD supersedes AD 2002–11–08,
Amendment 39–12769.
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 report of a
cracked fan blade found before the blade
reached the initial inspection threshold of
AD 2002–11–08. This AD also results from
the need to reduce a repetitive inspection
compliance time due to potential breakdown
of blade coating and lubrication on certain
blades. We are issuing this AD to prevent
multiple LPC fan blade failures due to cracks,
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13JAR1
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Federal Register / Vol. 70, No. 9 / Thursday, January 13, 2005 / Rules and Regulations
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 cycles-since-rework
(CSR) using either RR ASB No. RB.211–72–
AD344 or 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
Airplane maximum gross weight
(times 1,000 pounds)
(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 CSR
(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 RB.211–72–D347, inspect as specified
in paragraph (f) of this AD and within the
Initial
inspection
CSN
Repetitive
inspection
(cycles-sincelast-inspection) (CSLI)
600
2,000
1,200
600
2,000
2,000
2,000
80
600
100
80
600
600
600
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
Airplane maximum gross weight
(times 1,000 pounds)
(i) –884B, 892 ....................................................
–300
(ii) 884, –892, –892B, and –895 ........................
–200
(iii) –875; ............................................................
(iv) –877 .............................................................
–200
–200
(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
(A) 660 and 632.5 .............................................
(B) 580 ...............................................................
(A) 632.5 and 648 .............................................
(B) 656 ...............................................................
(C) 555 ..............................................................
535 .....................................................................
545 .....................................................................
have not been relubricated during any
interval exceeding 600 CSN or CSR using
either RR ASB No. RB.211–72–AD344 or
RB.211–72–D347 requirements, inspect as
Initial
inspection
CSN
Repetitive
inspection
CSLI
600
2,400
1,200
600
2,400
2,400
2,400
80
600
100
80
600
600
600
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
Airplane maximum gross weight
(times 1,000 pounds)
(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
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Jkt 205001
(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
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Fmt 4700
Sfmt 4700
Initial
inspection
CSN
Repetitive
inspection
CSLI
600
2,000
1,200
600
2,000
2,000
2,000
this AD and within the compliance times
specified in the following Table 4:
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100
600
125
100
600
600
600
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Federal Register / Vol. 70, No. 9 / Thursday, January 13, 2005 / Rules and Regulations
TABLE 4.—COMPLIANCE TIMES FOR BLADES P/NS FW12960, FW12961, FW12962, AND FW13175
Boeing 777
series
Engine series
Airplane maximum gross weight
(times 1,000 pounds)
(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 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 a complete set
of LPC fan blades that have been reworked,
relubricated, and remarked using RR SB No.
RB.211–72–D672, dated February 1, 2002; or;
(2) Replace LPC fan blades P/Ns FK30838,
FK30840, FK30842, FW12960, FW12961,
FW12962, or FW13175 with a complete set
of new LPC fan blades that feature additional
Initial
inspection
CSN
(A) 660 and 632.5 .............................................
(B) 580 ...............................................................
(A) 632.5 and 648 .............................................
(B) 656 ...............................................................
(C) 535 ..............................................................
535 .....................................................................
545 .....................................................................
blade root processing requirements found in
RR SB No. RB.211–72–D672, dated February
1, 2002.
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.
Material Incorporated by Reference
(k) You must use the Rolls-Royce plc
service information specified in Table 5 of
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
this AD to perform the blade inspections and
replacements required by this AD. The
Director of the Federal Register approved the
incorporation by reference of the documents
listed in Table 5 of this AD in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. You
can get a copy from Rolls-Royce plc, P.O. Box
31, Derby DE24 6BJ, UK; telephone 44 (0)
1332 242424; fax 44 (0) 1332 249936. You
may review copies at the FAA, New England
Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2001–NE–17–
AD, 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/
code_of_federal_regulations/
ibr_locations.html. Table 5 follows:
TABLE 5.—INCORPORATION BY REFERENCE
Service Bulletin No.
Page
Revision
RB.211–72–AD344 ...............................................................
Total Pages: 11
RB.211–72–AD344, Appendices 1 through 5 ......................
Total Pages: 18
RB.211–72–D672 .................................................................
Total Pages: 24
ALL ........................................
7 ............................................
March 12, 2004.
ALL ........................................
7 ............................................
March 12, 2004.
ALL ........................................
Original ..................................
February 1, 2002.
Related Information
DEPARTMENT OF TRANSPORTATION
(l) 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
January 3, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–485 Filed 1–12–05; 8:45 am]
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20010; Directorate
Identifier 2003–NM–224–AD; Amendment
39–13938; AD 2005–01–13]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767–300 Series Airplanes
BILLING CODE 4910–13–P
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 767–300 series airplanes.
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Date
This AD requires repetitive functional
tests and repetitive replacements of the
auxiliary power unit (APU) and engine
fire shutoff switches. This proposal also
provides an optional terminating action
for the repetitive functional tests and
replacements. This AD is prompted by
a report of the failure of the engine fire
shutoff switch in the engine fire control
module. We are issuing this AD to
prevent mineral build-up on the APU
and engine fire shutoff switches, which
could lead to the switches failing to
discharge fire suppressant to the
affected fire zone and result in an
uncontrolled engine or APU fire and
consequent loss of the airplane.
Effective January 28, 2005. The
incorporation by reference of a certain
publication listed in the AD is approved
DATES:
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]]>Agencies
[Federal Register Volume 70, Number 9 (Thursday, January 13, 2005)]
[Rules and Regulations]
[Pages 2336-2339]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-485]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NE-17-AD; Amendment 39-13940; AD 2005-01-15]
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: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Rolls-Royce plc (RR) RB211 Trent 875, 877, 884, 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. This AD requires the same actions except at reduced compliance
times for certain blades, defines a specific terminating action to the
repetitive blade inspection requirements, and adds the 884B series to
the applicability. This AD results from a report of a cracked fan blade
found before the blade reached the initial inspection threshold of AD
2002-11-08. This AD also results from the need to reduce a repetitive
inspection compliance time due to potential breakdown of blade coating
and lubrication on certain blades. 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.
DATES: Effective January 28, 2005. The Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulations as of January 28, 2005.
We must receive any comments on this AD by March 14, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this 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 referenced in this 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, 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: On May 27, 2002, the FAA issued AD 2002-11-
08, Amendment 39-12769 (67 FR 38852, June 6, 2002). That AD requires
initial and repetitive ultrasonic inspections of the fan blade dovetail
roots. That AD was the result of the loss of an LPC fan blade during
takeoff. That condition, if not corrected, could result in multiple LPC
fan blade failures due to cracks, which could result in uncontained
engine failure and possible damage to the airplane.
Actions Since AD 2002-11-08 Was Issued
Since that AD was issued, the Civil Aviation Authority (CAA), which
is the airworthiness authority for the United Kingdom (UK), notified us
that an unsafe condition may exist on RR RB211 Trent 875, 877, 884,
884B, 892, 892B, and 895 series turbofan engines. The CAA advises that
a cracked fan blade was found before the blade reached the initial
inspection threshold specified in AD 2002-11-08. The CAA also advises
that potential breakdown of blade coating and lubrication on certain
blades might occur, leading to blade cracking.
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 CAA 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 Airworthiness Agreement
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 This AD
The unsafe condition described previously is likely to exist or
develop on other RR RB211 Trent 875, 877, 884, 884B, 892, 892B, and 895
series turbofan engines of the same type design. 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. This AD:
Requires initial and repetitive ultrasonic-inspections of
the dovetail
[[Page 2337]]
roots of LPC fan blades P/Ns FK30838, FK30840, FK30842, FW12960,
FW12961, FW12962, and FW13175.
Reduces the initial inspection threshold for fan blades,
P/Ns FK30838, FK30840, and FK30842 in Table 1 for Airplane Maximum
Gross Weight of 632,500 pounds and 648,000 pounds, from 2,400 cycles-
since-new (CSN) to 1,200 CSN.
Reduces the repetitive inspection threshold for fan
blades, P/Ns FW12960, FW12961, FW12962, and FW13175 in Table 4 for
Airplane Maximum Gross Weight of 545,000 pounds from 1,200 CSN to 600
CSN.
Defines 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 consists of replacing LPC fan blades with a complete
set of reworked, relubricated, and remarked LPC fan blades, using
Rolls-Royce SB No. RB.211-72-D672, dated February 1, 2002, or with a
complete set of new LPC fan blades that feature additional blade root
processing requirements.
Adds the 884B series engine to the applicability.
You must use the service information described previously to perform
the actions required by this AD.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause exists for making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to submit any written relevant data,
views, or arguments regarding this AD. 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 rule
that might suggest a need to modify it. If a person contacts us
verbally, and that contact relates to a substantive part of this 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 AD
in light of those comments.
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications with you. You may get more information about plain
language at https://www.faa.gov/language and https://
www.plainlanguage.gov.
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.
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 the 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. 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. 2001-NE-17-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,
the FAA amends part 39 of the Federal Aviation Regulations (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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing Amendment 39-12769 (67 FR 38852; June 6, 2002), and by adding
a new airworthiness directive (AD), Amendment 39-13940, to read as
follows:
2005-01-15 Rolls-Royce plc: Amendment 39-13940. Docket No. 2001-NE-
17-AD. Supersedes AD 2002-11-08, Amendment 39-12769.
Effective Date
(a) This AD becomes effective January 28, 2005.
Affected ADs
(b) This AD supersedes AD 2002-11-08, Amendment 39-12769.
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 report of a cracked fan blade found
before the blade reached the initial inspection threshold of AD
2002-11-08. This AD also results from the need to reduce a
repetitive inspection compliance time due to potential breakdown of
blade coating and lubrication on certain blades. We are issuing this
AD to prevent multiple LPC fan blade failures due to cracks,
[[Page 2338]]
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 cycles-since-rework (CSR) using either RR ASB No. RB.211-
72-AD344 or 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
inspection
Boeing 777 Airplane maximum gross Initial (cycles-
Engine series series weight (times 1,000 pounds) inspection since-last-
CSN 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 CSR using
either RR ASB No. RB.211-72-AD344 or SB 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
----------------------------------------------------------------------------------------------------------------
Initial Repetitive
Engine series Boeing 777 Airplane maximum gross inspection inspection
series weight (times 1,000 pounds) CSN 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
----------------------------------------------------------------------------------------------------------------
(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 CSR using either RR ASB No.
RB.211-72-AD344 or 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
----------------------------------------------------------------------------------------------------------------
Initial Repetitive
Engine series Boeing 777 Airplane maximum gross inspection inspection
series weight (times 1,000 pounds) CSN 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:
[[Page 2339]]
Table 4.--Compliance Times for Blades P/Ns FW12960, FW12961, FW12962, and FW13175
----------------------------------------------------------------------------------------------------------------
Initial Repetitive
Engine series Boeing 777 Airplane maximum gross inspection inspection
series weight (times 1,000 pounds) CSN 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) 535.................... 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 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 a complete set of LPC fan
blades that have been reworked, relubricated, and remarked using RR
SB No. RB.211-72-D672, dated February 1, 2002; or;
(2) Replace LPC fan blades P/Ns FK30838, FK30840, FK30842,
FW12960, FW12961, FW12962, or FW13175 with a complete set of new LPC
fan blades that feature additional blade root processing
requirements found in RR SB No. RB.211-72-D672, dated February 1,
2002.
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.
Material Incorporated by Reference
(k) You must use the Rolls-Royce plc service information
specified in Table 5 of this AD to perform the blade inspections and
replacements required by this AD. The Director of the Federal
Register approved the incorporation by reference of the documents
listed in Table 5 of this AD in accordance with 5 U.S.C. 552(a) and
1 CFR part 51. You can get a copy from Rolls-Royce plc, P.O. Box 31,
Derby DE24 6BJ, UK; telephone 44 (0) 1332 242424; fax 44 (0) 1332
249936. You may review copies at the FAA, New England Region, Office
of the Regional Counsel, Attention: Rules Docket No. 2001-NE-17-AD,
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/code_of_federal_
regulations/ibr_locations.html. Table 5 follows:
Table 5.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Service Bulletin No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
RB.211-72-AD344................... ALL.................. 7.................... March 12, 2004.
Total Pages: 11
RB.211-72-AD344, Appendices 1 ALL.................. 7.................... March 12, 2004.
through 5.
Total Pages: 18
RB.211-72-D672.................... ALL.................. Original............. February 1, 2002.
Total Pages: 24
----------------------------------------------------------------------------------------------------------------
Related Information
(l) 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 January 3, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-485 Filed 1-12-05; 8:45 am]
BILLING CODE 4910-13-P
