[Federal Register: January 13, 2005 (Volume 70, Number 9)]
[Rules and Regulations]
[Page 2336-2339]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13ja05-5]
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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.
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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 http://www.faa.gov/language and http://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
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Repetitive
inspection
Boeing 777 Airplane maximum gross Initial (cycles-
Engine series series weight (times 1,000 pounds) inspection since-last-
CSN inspection)
(CSLI)
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(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
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(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
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Initial Repetitive
Engine series Boeing 777 Airplane maximum gross inspection inspection
series weight (times 1,000 pounds) CSN CSLI
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(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
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(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
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Initial Repetitive
Engine series Boeing 777 Airplane maximum gross inspection inspection
series weight (times 1,000 pounds) CSN CSLI
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(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
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(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
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Initial Repetitive
Engine series Boeing 777 Airplane maximum gross inspection inspection
series weight (times 1,000 pounds) CSN CSLI
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(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
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(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:
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Table 5 follows:
Table 5.--Incorporation by Reference
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Service Bulletin No. Page Revision Date
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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
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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]
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