Airworthiness Directives; Rolls-Royce plc RB211 Trent 700 Series Turbofan Engines, 2333-2336 [05-484]
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Federal Register / Vol. 70, No. 9 / Thursday, January 13, 2005 / Rules and Regulations
(1) Left Engine PDIU
(2) Left Engine Thrust Reverser Cont/Scav
Press
(3) Left Engine Electronic Engine Control
Altn Pwr (if installed)
(4) Left Engine Thrust Reverser PRI Cont
(5) Left Engine Thrust Reverser Sec Cont
(k) For the right engine, make sure these
circuit breakers on the P11 panel are
closed:
(1) Right Engine PDIU
(2) Right Engine Thrust Reverser Cont/Scav
Press
(3) Right Engine Electronic Engine Control
Altn Pwr (if installed)
(4) Right Engine Thrust Reverser PRI Cont
(5) Right Engine Thrust Reverser Sec Cont
(l) Supply electrical power.
(m) Remove the pressure from the left
(right) hydraulic system.
B. Do the Thrust Reverser Sync Lock Test.
(1) Move and hold the manual unlock lever
on the center actuator on both thrust
reverser sleeves to the unlock position.
(2) Make sure the thrust reverser sleeves
did not move.
(3) Move the left (right) reverser thrust
lever up and rearward to the idle detent
position.
(4) Make sure both thrust reverser sleeves
move aft (approximately 0.15 to 0.25
inch).
(5) Release the manual unlock lever on the
center actuators.
Warning: Make sure all persons and
equipment are clear of the area around the
Thrust Reverser. When you apply hydraulic
pressure the Thrust Reverser will extend and
can cause injuries to persons or damage to
equipment.
(6) Pressurize the left (right) hydraulic
system.
(7) Make sure the thrust reverser extends.
(8) Move the left (right) reverser thrust
lever to the fully forward and down
position to retract the thrust reverser.
C. Put the Airplane Back to its Usual
Condition.
(1) Remove hydraulic pressure.
(2) Close the left and right fan cowls.
(3) Close the Auto Speedbrake circuit
breaker on the P11 panel.
(4) Remove electrical power if it is not
necessary.
(5) Return the EEC Maint Power switch or
the EEC Power L and EEC Power R
switches to the Normal position.
D. Repeat the Thrust Reverser Sync Lock
Test on the other engine.’’
(k) Installation of the sync lock, as required
by paragraph (i) of this AD, constitutes
terminating action for the requirements of
paragraphs (f) through (h) of this AD.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) We approve the following for the
corresponding requirements of this AD:
AMOCs approved previously in accordance
with AD 91–20–09, amendment 39–8043; AD
94–01–10, amendment 39–8792; and AD 94–
01–10 R1, amendment 39–13247.
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Material Incorporated by Reference
(m) Except as otherwise specified in this
AD, the actions must be done in accordance
with Boeing Alert Service Bulletin 757–
78A0027, dated September 9, 1991; Boeing
Service Bulletin 757–78–0025, dated
September 9, 1991; Boeing Document
D630N002, ‘‘Boeing 757 Dispatch Deviation
Guide,’’ Revision 8, dated January 15, 1991;
and Boeing Service Bulletin 757–78–0028,
Revision 1, dated October 29, 1992, or Boeing
Service Bulletin 757–78–0028, Revision 2,
dated January 14, 1993; as applicable.
(1) The incorporation by reference of
Boeing Service Bulletin 757–78–0028,
Revision 1, dated October 29, 1992; and
Boeing Service Bulletin 757–78–0028,
Revision 2, dated January 14, 1993; was
approved previously by the Director of the
Federal Register as of March 3, 1994 (59 FR
4558, February 1, 1994).
(2) The incorporation by reference of
Boeing Alert Service Bulletin 757–78A0027,
dated September 9, 1991; Boeing Service
Bulletin 757–78–0025, dated September 9,
1991; and Boeing Document D630N002,
‘‘Boeing 757 Dispatch Deviation Guide,’’
Revision 8, dated January 15, 1991; was
approved previously by the Director of the
Federal Register as of September 16, 1991 (56
FR 46725, September 16, 1991). (The
document number of Boeing Alert Service
Bulletin 757–78A0027, dated September 9,
1991, was cited erroneously in the September
16, 1991, issue of the Federal Register as
‘‘757–78H0027.’’ The document number of
Boeing Service Bulletin 757–78–0025, dated
September 9, 1991, was also cited
erroneously in the September 16, 1991, issue
of the Federal Register as ‘‘757–0025.’’)
(3) Contact Boeing Commercial Airplanes,
PO Box 3707, Seattle, Washington 98124–
2207, for copies of the service documents.
Copies may be inspected at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; 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.
Issued in Renton, Washington, on
December 29, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–536 Filed 1–12–05; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000–NE–05–AD; Amendment
39–13941; AD 2005–01–16]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc RB211 Trent 700 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 768–
60, Trent 772–60, and Trent 772B–60
turbofan engines with low pressure
compressor (LPC) fan blade part
numbers FK22580, FK23411, FK25441,
and FK25968 installed. That AD
currently requires initial ultrasonic
inspections of the fan blade root with
blades removed, repetitive ultrasonic
inspections of the fan blade root with
blades removed or installed, and
ultrasonic inspection of the fan blade
root to be done with the fan blades
removed at least every third inspection.
This AD requires the same inspections
but at lower thresholds and intervals,
and eliminates the requirement for
ultrasonic inspection with the fan
blades removed at least every third
inspection. This AD results from
analysis of flight data returned to RR,
that shows a need for consistent
inspection thresholds for all engine
models. We are issuing this AD to
prevent possible multiple LPC fan blade
failures, which could result in an
uncontained engine failure and 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. 2000–NE–
05–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
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Federal Register / Vol. 70, No. 9 / Thursday, January 13, 2005 / Rules and Regulations
plc, PO Box 31, Derby, England;
telephone: 011–44–1332–249428; fax:
011–44–1332–249223.
You may review copies at the FAA,
New England Region, Office of the
Regional Counsel, 12 New England
Executive Park, Burlington, MA; or at
the National Archives and Records
Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/
federal_register/
code_of_federal_regulations/
ibr_locations.html. You may examine
the AD docket 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 August
1, 2001, we issued AD 2001–16–05,
Amendment 39–12373 (66 FR 42105,
August 10, 2001). That AD requires
initial ultrasonic inspections of the fan
blade root with blades removed,
repetitive ultrasonic inspections of the
fan blade root with blades removed or
installed, and ultrasonic inspections to
be done with the fan blades removed at
least every third inspection. That AD
resulted from reports of fan blade
failures due to dovetail root cracks. That
condition, if not corrected, could result
in possible multiple LPC fan blade
failures, uncontained engine failure, and
damage to the airplane.
Actions Since AD 2001–16–05 Was
Issued
Since that AD was issued, analysis of
flight data returned to RR shows a need
for consistent inspection thresholds for
all engine models. The actions specified
in this AD are intended to prevent
possible multiple LPC fan blade failures,
which could result in an uncontained
engine failure and damage to the
airplane.
Special Flight Permits Paragraph
Removed
Paragraph (g) of the current AD, AD
2001–16–05, contains a paragraph
pertaining to special flight permits.
Even though this final rule does not
contain a similar paragraph, we have
made no changes with regard to the use
of special flight permits to operate the
airplane to a repair facility to do the
work required by this AD. In July 2002,
we published a new Part 39 that
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contains a general authority regarding
special flight permits and airworthiness
directives; see Docket No. FAA–2004–
8460, Amendment 39–9474 (69 FR
47998, July 22, 2002). Thus, when we
now supersede ADs we will not include
a specific paragraph on special flight
permits unless we want to limit the use
of that general authority granted in
section 39.23.
Relevant Service Information
We have reviewed and approved the
technical contents of RR Mandatory
Service Bulletin (MSB) No. RB.211–72–
C878, Revision 7, dated December 5,
2003, that:
• Removes LPC fan blades and
performs initial and repetitive
ultrasonic inspections for cracks in LPC
fan blade dovetail roots, at earlier initial
thresholds than the inspections required
by the current AD, and, at adjusted
repetitive inspection intervals from the
current AD.
• Provides a procedure that does not
require blade removal from the engine
in order to perform repetitive ultrasonic
inspections for cracks in LPC fan blade
dovetail roots.
Bilateral Airworthiness Agreement
This engine model is manufactured in
the United Kingdom and is type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. Pursuant to this bilateral
airworthiness agreement, the Civil
Aviation Authority (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 of an Unsafe
Condition and Proposed Actions
Although none of these affected
engine models are used on any airplanes
that are registered in the United States,
the possibility exists that the engine
models could be used on airplanes that
are registered in the United States in the
future. Since an unsafe condition has
been identified that is likely to exist or
develop on other RR RB211 Trent 768–
60, Trent 772–60, and Trent 772B–60
turbofan engine models of the same type
design, this AD is being issued to
prevent possible multiple LPC fan blade
failures, which could result in an
uncontained engine failure and damage
to the airplane. This AD requires:
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• Initial ultrasonic inspections of the
fan blade root with blades removed; at
or before accumulating 1,100 cyclessince-new (CSN) on the fan blades after
the effective date of the AD; and
• For blades with more than 1,100
CSN that have not been previously
inspected, initial ultrasonic inspections
of the fan blade root with blades
removed; within 300 cycles-in-service
(CIS) from the effective date of the AD
or within 2,000 CSN, whichever occurs
first; and
• Repetitive ultrasonic inspections of
the fan blade root, with blades removed
within 300 CIS intervals, or with blades
not removed within 250 CIS intervals.
The actions are required to be done
using the service bulletin described
previously.
Immediate Adoption of This AD
Since there are currently no domestic
operators of these engine models, notice
and opportunity for prior public
comment are unnecessary. Therefore, a
situation exists that allows the
immediate adoption of this regulation.
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.
2000–NE–05–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
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.
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.
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Federal Register / Vol. 70, No. 9 / Thursday, January 13, 2005 / Rules and Regulations
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 satisfy the initial requirements of 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. 2000–NE–05–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]
the compliance times specified unless the
actions have already been done.
Initial Ultrasonic Inspection
(f) Perform an initial ultrasonic inspection
of the LPC fan blade dovetail roots using
Method A (paragraphs 3.A.(1) through
3.A.(8); blades removed from engine) of
Accomplishment Instructions of RR
Mandatory Service Bulletin (MSB) No.
RB.211–72–C878, Revision 7, dated
December 5, 2003, as follows:
(1) Inspect before accumulating 1,100
cycles-since-new (CSN) on the fan blades; or
(2) For fan blades that have accumulated
more than 800 CSN on the effective date of
this AD that have not been previously
inspected, inspect within 300 cycles-inservice (CIS) from the effective date of this
AD or within 2,000 CSN, whichever occurs
first.
I
Repetitive Ultrasonic Inspections
2005–01–16 Rolls-Royce plc: Amendment
39–13941. Docket No. 2000–NE–05–AD.
Supersedes AD 2001–16–05,
Amendment 39–12373.
(g) Perform repetitive inspections of the
LPC fan blades using Method A, or Method
B (paragraphs 3.B.(1) through 3.B.(5); blades
not removed from the engine) of the
Accomplishment Instructions of RR MSB No.
RB.211–72–C878, Revision 7, dated
December 5, 2003, as follows:
(1) Inspect within 300 CIS since-lastinspected with Method A of the SB; or
(2) Inspect within 250 CIS since-lastinspected with Method B of the SB.
2. The Federal Aviation
Administration (FAA) amends § 39.13 by
removing Amendment 39–12373 (66 FR
42105, August 10, 2001), and by adding
a new airworthiness directive (AD),
Amendment 39–13941, to read as
follows:
Effective Date
(a) This AD becomes effective January 28,
2005.
Affected ADs
(b) This AD supersedes AD 2001–16–05,
Amendment 39–12373.
Applicability
(c) This AD applies to Rolls-Royce plc (RR)
RB211 Trent 768–60, Trent 772–60, and
Trent 772B–60 turbofan engines with low
pressure compressor (LPC) fan blade part
numbers FK22580, FK23411, FK25441, and
FK25968 installed. These engines are
installed on, but not limited to, Airbus A330
series airplanes.
Unsafe Condition
(d) This AD supersedure results from
analysis of flight data returned to RR, that
shows a need for consistent inspection
thresholds for all engine models. We are
issuing this AD to prevent possible multiple
LPC fan blade failures, which could result in
an uncontained engine failure and damage to
the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
Alternative Methods of Compliance
(h) 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
(i) You must use the Rolls-Royce plc
service information specified in Table 1 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 1 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, PO 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. 2000–NE–05–
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 1 follows:
TABLE 1.—INCORPORATION BY REFERENCE
Mandatory service bulletin No.
Page
RB.211–72–C878 ...................................................................................
Total Pages: 9
RB.211–72–C878, Appendix 1 ...............................................................
Total Pages: 4
RB.211–72–C878, Appendix 2 ...............................................................
All ...................................................
7
December 5, 2003.
All ...................................................
7
December 5, 2003.
All ...................................................
7
December 5, 2003.
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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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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
E:\FR\FM\13JAR1.SGM
13JAR1
]]>Agencies
[Federal Register Volume 70, Number 9 (Thursday, January 13, 2005)]
[Rules and Regulations]
[Pages 2333-2336]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-484]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-NE-05-AD; Amendment 39-13941; AD 2005-01-16]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Trent 700 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 768-60, Trent 772-60, and
Trent 772B-60 turbofan engines with low pressure compressor (LPC) fan
blade part numbers FK22580, FK23411, FK25441, and FK25968 installed.
That AD currently requires initial ultrasonic inspections of the fan
blade root with blades removed, repetitive ultrasonic inspections of
the fan blade root with blades removed or installed, and ultrasonic
inspection of the fan blade root to be done with the fan blades removed
at least every third inspection. This AD requires the same inspections
but at lower thresholds and intervals, and eliminates the requirement
for ultrasonic inspection with the fan blades removed at least every
third inspection. This AD results from analysis of flight data returned
to RR, that shows a need for consistent inspection thresholds for all
engine models. We are issuing this AD to prevent possible multiple LPC
fan blade failures, which could result in an uncontained engine failure
and 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. 2000-NE-05-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
[[Page 2334]]
plc, PO Box 31, Derby, England; telephone: 011-44-1332-249428; fax:
011-44-1332-249223.
You may review copies at the FAA, New England Region, Office of the
Regional Counsel, 12 New England Executive Park, Burlington, MA; or at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-741-
6030, or go to: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html. You may examine the AD docket
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 August 1, 2001, we issued AD 2001-16-05,
Amendment 39-12373 (66 FR 42105, August 10, 2001). That AD requires
initial ultrasonic inspections of the fan blade root with blades
removed, repetitive ultrasonic inspections of the fan blade root with
blades removed or installed, and ultrasonic inspections to be done with
the fan blades removed at least every third inspection. That AD
resulted from reports of fan blade failures due to dovetail root
cracks. That condition, if not corrected, could result in possible
multiple LPC fan blade failures, uncontained engine failure, and damage
to the airplane.
Actions Since AD 2001-16-05 Was Issued
Since that AD was issued, analysis of flight data returned to RR
shows a need for consistent inspection thresholds for all engine
models. The actions specified in this AD are intended to prevent
possible multiple LPC fan blade failures, which could result in an
uncontained engine failure and damage to the airplane.
Special Flight Permits Paragraph Removed
Paragraph (g) of the current AD, AD 2001-16-05, contains a
paragraph pertaining to special flight permits. Even though this final
rule does not contain a similar paragraph, we have made no changes with
regard to the use of special flight permits to operate the airplane to
a repair facility to do the work required by this AD. In July 2002, we
published a new Part 39 that contains a general authority regarding
special flight permits and airworthiness directives; see Docket No.
FAA-2004-8460, Amendment 39-9474 (69 FR 47998, July 22, 2002). Thus,
when we now supersede ADs we will not include a specific paragraph on
special flight permits unless we want to limit the use of that general
authority granted in section 39.23.
Relevant Service Information
We have reviewed and approved the technical contents of RR
Mandatory Service Bulletin (MSB) No. RB.211-72-C878, Revision 7, dated
December 5, 2003, that:
Removes LPC fan blades and performs initial and repetitive
ultrasonic inspections for cracks in LPC fan blade dovetail roots, at
earlier initial thresholds than the inspections required by the current
AD, and, at adjusted repetitive inspection intervals from the current
AD.
Provides a procedure that does not require blade removal
from the engine in order to perform repetitive ultrasonic inspections
for cracks in LPC fan blade dovetail roots.
Bilateral Airworthiness Agreement
This engine model is manufactured in the United Kingdom and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the Civil Aviation Authority (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 of an Unsafe Condition and Proposed Actions
Although none of these affected engine models are used on any
airplanes that are registered in the United States, the possibility
exists that the engine models could be used on airplanes that are
registered in the United States in the future. Since an unsafe
condition has been identified that is likely to exist or develop on
other RR RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan
engine models of the same type design, this AD is being issued to
prevent possible multiple LPC fan blade failures, which could result in
an uncontained engine failure and damage to the airplane. This AD
requires:
Initial ultrasonic inspections of the fan blade root with
blades removed; at or before accumulating 1,100 cycles-since-new (CSN)
on the fan blades after the effective date of the AD; and
For blades with more than 1,100 CSN that have not been
previously inspected, initial ultrasonic inspections of the fan blade
root with blades removed; within 300 cycles-in-service (CIS) from the
effective date of the AD or within 2,000 CSN, whichever occurs first;
and
Repetitive ultrasonic inspections of the fan blade root,
with blades removed within 300 CIS intervals, or with blades not
removed within 250 CIS intervals.
The actions are required to be done using the service bulletin
described previously.
Immediate Adoption of This AD
Since there are currently no domestic operators of these engine
models, notice and opportunity for prior public comment are
unnecessary. Therefore, a situation exists that allows the immediate
adoption of this regulation.
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. 2000-NE-05-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.
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.
[[Page 2335]]
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 satisfy the initial
requirements of 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. 2000-NE-05-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 39-12373 (66 FR 42105, August 10, 2001), and by
adding a new airworthiness directive (AD), Amendment 39-13941, to read
as follows:
2005-01-16 Rolls-Royce plc: Amendment 39-13941. Docket No. 2000-NE-
05-AD. Supersedes AD 2001-16-05, Amendment 39-12373.
Effective Date
(a) This AD becomes effective January 28, 2005.
Affected ADs
(b) This AD supersedes AD 2001-16-05, Amendment 39-12373.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 768-60,
Trent 772-60, and Trent 772B-60 turbofan engines with low pressure
compressor (LPC) fan blade part numbers FK22580, FK23411, FK25441,
and FK25968 installed. These engines are installed on, but not
limited to, Airbus A330 series airplanes.
Unsafe Condition
(d) This AD supersedure results from analysis of flight data
returned to RR, that shows a need for consistent inspection
thresholds for all engine models. We are issuing this AD to prevent
possible multiple LPC fan blade failures, which could result in an
uncontained engine failure and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Initial Ultrasonic Inspection
(f) Perform an initial ultrasonic inspection of the LPC fan
blade dovetail roots using Method A (paragraphs 3.A.(1) through
3.A.(8); blades removed from engine) of Accomplishment Instructions
of RR Mandatory Service Bulletin (MSB) No. RB.211-72-C878, Revision
7, dated December 5, 2003, as follows:
(1) Inspect before accumulating 1,100 cycles-since-new (CSN) on
the fan blades; or
(2) For fan blades that have accumulated more than 800 CSN on
the effective date of this AD that have not been previously
inspected, inspect within 300 cycles-in-service (CIS) from the
effective date of this AD or within 2,000 CSN, whichever occurs
first.
Repetitive Ultrasonic Inspections
(g) Perform repetitive inspections of the LPC fan blades using
Method A, or Method B (paragraphs 3.B.(1) through 3.B.(5); blades
not removed from the engine) of the Accomplishment Instructions of
RR MSB No. RB.211-72-C878, Revision 7, dated December 5, 2003, as
follows:
(1) Inspect within 300 CIS since-last-inspected with Method A of
the SB; or
(2) Inspect within 250 CIS since-last-inspected with Method B of
the SB.
Alternative Methods of Compliance
(h) 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
(i) You must use the Rolls-Royce plc service information
specified in Table 1 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 1 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, PO 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. 2000-NE-05-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 1 follows:
Table 1.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Mandatory service bulletin No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
RB.211-72-C878........................ All..................... 7 December 5, 2003.
Total Pages: 9
RB.211-72-C878, Appendix 1............ All..................... 7 December 5, 2003.
Total Pages: 4
RB.211-72-C878, Appendix 2............ All..................... 7 December 5, 2003.
[[Page 2336]]
Total Pages: 5
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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
