Airworthiness Directives; Rolls-Royce plc Models RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 Turbofan Engines, 11153-11156 [06-1965]
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Federal Register / Vol. 71, No. 43 / Monday, March 6, 2006 / Rules and Regulations
If electrical de-icing boots are installed, no
polyurethane protective strips are required.
Repetitive Visual Inspection of the Propeller
Blade
(i) If after the effective date of this AD, any
propeller blade erosion sheath found to be
cracked or loose during the pilot’s preflight
inspection, or 100-hour inspection, or annual
inspection, must be repaired, replaced, or
overhauled before the next flight.
Repetitive Visual Inspection of the Propeller
Blade Polyurethane Strip
(j) If after the effective date of this AD, any
propeller blade polyurethane protective strip
found to be damaged or missing during the
pilot’s preflight inspection, or 100-hour
inspection, or annual inspection, must be
replaced or installed within 10-flight hours.
If electrical de-icing boots are installed,
polyurethane protective strips are not
required.
Alternative Methods of Compliance
(k) The Manager, Boston Aircraft
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.
Special Flight Permits
(l) Special flight permits are prohibited.
Related Information
(m) MT-Propeller Entwicklung GmbH,
Service Bulletin No. 8A, dated July 4, 2003,
pertains to the subject of this AD. LBA
airworthiness directive 1994–098/2, dated
September 24, 2003, also addresses the
subject of this AD.
Issued in Burlington, Massachusetts, on
February 24, 2006.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 06–1957 Filed 3–3–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23605; Directorate
Identifier 2005–NE–48–AD; Amendment 39–
14500; AD 2006–05–03]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc Models RB211 Trent 768–60, Trent
772–60, and Trent 772B–60 Turbofan
Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
hsrobinson on PROD1PC70 with RULES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for Rolls-
VerDate Aug<31>2005
14:28 Mar 03, 2006
Jkt 208001
Royce plc (RR) models RB211 Trent
768–60, Trent 772–60, and Trent 772B–
60 turbofan engines. This AD requires
initial and repetitive borescope
inspections of the high pressureintermediate pressure (HP–IP) turbine
bearing internal oil vent tube, scavenge
tube, and tube heat shields for wear and
cracking, and removing tubes from
service if found with any cracks beyond
serviceable limits. This AD also requires
installation of a new or modified HP–IP
turbine bearings support as terminating
action for the repetitive borescope
inspections. This AD results from two
reports of RR RB211 Trent 700 series
engines found with the HP–IP internal
oil vent tube and scavenge tube fretted
by damaged heat shields on the tubes.
We are issuing this AD to prevent oil
ejecting from the HP–IP turbine bearings
chamber and igniting. Burning oil can
cause the intermediate pressure (IP)
shaft to fracture, the IP turbine to
overspeed, and possible uncontained
failure of the engine.
DATES: Effective March 27, 2006. The
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulations as of March 27, 2006.
We must receive any comments on
this AD by May 5, 2006.
ADDRESSES: Use one of the following
addresses to comment on this AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Rolls-Royce plc, PO Box 31,
Derby, England, DE248BJ; telephone:
011–44–1332–242424; fax: 011–44–
1332–245418, for the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Christopher Spinney, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803–5299; telephone
(781) 238–7175; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION: The Civil
Aviation Authority (CAA), which is the
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11153
airworthiness authority for the United
Kingdom (UK), recently notified us that
an unsafe condition might exist on RR
RB211 Trent 768–60, Trent 772–60, and
Trent 772B–60 turbofan engines. The
CAA advises that two RB211 Trent 700
series engines were removed due to high
oil consumption. Investigation revealed
that damaged heat shields caused
fretting of the HP–IP internal oil vent
tube and scavenge tube. A previous
service incident revealed that ingestion
of HP cooling air into either the
scavenge tube or the vent tube can over
pressurize the HP–IP turbine bearing
chamber. The overpressure can cause oil
to eject from the rear of the chamber. If
the ejected oil ignites, the fire can
trigger fracture of the IP shaft, overspeed
of the IP turbine, and uncontained
engine failure.
Relevant Service Information
We have reviewed and approved the
technical contents of RR Alert Service
Bulletin RB.211–72–AE792, dated July
8, 2005, that describes procedures for
initial and repetitive borescope
inspections of the HP–IP turbine bearing
internal oil vent tube, scavenge tube,
and tube heat shields for wear and
cracking. We have also reviewed and
approved the technical contents of RR
Service Bulletin RB.211–72–E708,
Revision 2, dated September 6, 2005,
that describes procedures for installing
a new or modified HP–IP turbine
bearings support. The CAA classified
these service bulletins as mandatory and
issued AD G–2005–0016 in order to
ensure the airworthiness of these RR
RB211 Trent 768–60, Trent 772–60, and
Trent 772B–60 turbofan engines in the
UK.
Bilateral Airworthiness Agreement
These RR RB211 Trent 768–60, Trent
772–60, and Trent 772B–60 turbofan
engines are manufactured in the UK and
are 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. Under this bilateral
airworthiness agreement, the CAA kept
the FAA informed of the situation
described above. We have 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
Although no airplanes that are
registered in the United States use these
RR RB211 Trent 768–60, Trent 772–60,
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Federal Register / Vol. 71, No. 43 / Monday, March 6, 2006 / Rules and Regulations
and Trent 772B–60 turbofan engines,
the possibility exists that the engines
could be used on airplanes that are
registered in the United States in the
future. The unsafe condition described
previously is likely to exist or develop
on other RR RB211 Trent 768–60, Trent
772–60, and Trent 772B–60 turbofan
engines of the same type design. We are
issuing this AD to prevent oil ejecting
from the HP–IP turbine bearings
chamber and igniting. Burning oil can
cause the IP shaft to fracture, the IP
turbine to overspeed, and possible
uncontained failure of the engine. This
AD requires:
• Initial and repetitive borescope
inspections of the HP–IP turbine bearing
internal oil vent tube, scavenge tube,
and tube heat shields for wear and
cracking; and
• Removing tubes from service if
found with any cracks beyond
serviceable limits; and
• As terminating action to the
repetitive inspections required by the
AD, at the next IP (05) module overhaul,
but before May 31, 2010, removing the
HP–IP bearings support introduced
prior to Rolls-Royce Modification 72–
E708, and replacing with serviceable
parts.
You must use the service information
described previously to perform the
actions required by this AD.
hsrobinson on PROD1PC70 with RULES
FAA’s Determination of the Effective
Date
Since there are currently no domestic
operators of this engine model, notice
and opportunity for public comment
before issuing this AD are unnecessary.
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 send us any
written relevant data, views, or
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
FAA–2006–23605; Directorate Identifier
2005–NE–48–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the rule that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
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14:28 Mar 03, 2006
Jkt 208001
search function of the DMS Web site,
anyone can find and read the comments
in any of our dockets, including the
name of the individual who sent the
comment (or signed the comment on
behalf of an association, business, labor
union, etc.). You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
2000 (65 FR 19477–78) or you may visit
https://dms.dot.gov.
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.
Examining the AD Docket
List of Subjects in 14 CFR Part 39
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
Facility Docket Office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The Docket
Office (telephone (800) 647–5227) is
located on the plaza level of the
Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the DMS
receives them.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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;
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Adoption of the Amendment
Under the authority delegated to me
by the Administrator, the Federal
Aviation Administration 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 FAA amends § 39.13 by adding
the following new airworthiness
directive:
I
2006–05–03 Rolls-Royce plc: Amendment
39–14500. Docket No. FAA–2006–23605;
Directorate Identifier 2005–NE–48–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective March 27, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc (RR)
models RB211 Trent 768–60, Trent 772–60,
and Trent 772B–60 turbofan engines. These
engines are installed on, but not limited to,
Airbus A330–243, A330–341, A330–342, and
A330–343 airplanes.
Unsafe Condition
(d) This AD results from two reports of RR
RB211 Trent 700 series engines found with
the high pressure-intermediate pressure (HP–
IP) internal oil vent tube and scavenge tube
fretted by damaged heat shields on the tubes.
Burning oil can cause the intermediate
pressure (IP) shaft to fracture, the IP turbine
to overspeed, and possible uncontained
failure of the engine. We are issuing this AD
to prevent oil ejecting from the HP–IP turbine
bearings chamber and igniting.
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.
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Federal Register / Vol. 71, No. 43 / Monday, March 6, 2006 / Rules and Regulations
Initial Borescope Inspection
(f) Perform an initial borescope inspection
of the HP–IP turbine bearing internal oil vent
and scavenge tubes and tube heat shields
before the thresholds listed in Table 1 of this
AD, or within 4 months after the effective
date of this AD, whichever occurs later. To
do the inspections, use either the on-wing or
the in-shop inspection procedures in the
Accomplishment Instructions of RR Alert
Service Bulletin (ASB) RB.211–72–AE792,
dated July 8, 2005.
TABLE 1.—INSPECTION CRITERIA
Action
Inspection threshold
(1) Initial inspection ..................................................................................
10,000 hours time-since-new (TSN) or time-since-overhaul (TSO), or
2,500 cycles-since-new (CSN) or cycles-since-overhaul (CSO),
whichever occurs first.
10,000 hours time-since-last-inspection (TSLI), or 2,500 cycles-sincelast-inspection (CSLI), whichever occurs first.
6,400 hours TSLI or 1,600 CSLI, whichever occurs first.
(2) Repetitive inspection interval for tubes with no visible damage to
outer heat shields on the tubes.
(3) Repetitive inspection interval for tubes with cracking up to 90 degrees around tube circumference or 10 millimeters along the length
of either outer heat shield.
(4) Repetitive inspection interval for tubes with cracking greater than
(3) above, but less than 360 degrees around the tube circumference.
Repetitive Borescope Inspections
(g) Repeat the borescope inspections of the
HP–IP turbine bearing internal oil vent and
scavenge tubes within the applicable
intervals listed in Table 1 of this AD. To do
the inspections, use either the on-wing or the
in-shop inspection procedures in the
Accomplishment Instructions of RR ASB
RB.211–72–AE792, dated July 8, 2005.
Removal of Damaged Tubes
(h) Within 10 CSLI, remove tubes with
cracking around the complete circumference
of either outer heat shield, or if any material
is missing from either outer heat shield, or
if either tube is fretted by loose heat shield
material.
Terminating Action
(i) As terminating action to the repetitive
inspections required by paragraph (g) of this
AD, at the next IP (05) module overhaul, but
before May 31, 2010, remove the HP–IP
bearings supports introduced prior to RollsRoyce Modification 72–E708 and replace
1,600 hours TSLI or 400 CSLI, whichever occurs first.
with serviceable parts. Information on RollsRoyce Modification 72–E708 can be found in
RR Service Bulletin RB.211–72–E708,
Revision 2, dated September 6, 2005.
Material Incorporated by Reference
(m) You must use the service information
specified in Table 2 of this AD to perform the
inspections and installations required by this
AD. The Director of the Federal Register
approved the incorporation by reference of
the documents listed in Table 2 of this AD
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact Rolls-Royce plc, PO Box 31,
Derby, England, DE248BJ; telephone: 011–
44–1332–242424; fax: 011–44–1332–245418,
for a copy of this service information. You
may review copies at the Docket Management
Facility; U.S. Department of Transportation,
400 Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–0001,
on the Internet at https://dms.dot.gov; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Definition
(j) For the purposes of this AD, serviceable
parts are new or reworked bearings supports
which reduce the adverse effects of HP3
cooling air turbulence on the HP–IP turbine
bearing internal oil vent and scavenge tubes
and tube heat shields, as described in RollsRoyce Modification 72–E708.
Alternative Methods of Compliance
(k) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(l) Civil Aviation Authority airworthiness
directive G–2005–0016, dated July 6, 2005,
also addresses the subject of this AD.
TABLE 2.—INCORPORATION BY REFERENCE
Page
Revision
RB.211–72–AE792 ..................................................................................
Total Pages: 22
Appendix A of RB.211–72–AE792 ..........................................................
Total Pages: 3
hsrobinson on PROD1PC70 with RULES
Service Bulletin No.
All ..............................
Original ......................
July 8, 2005.
All ..............................
Original ......................
July 8, 2005.
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11156
Federal Register / Vol. 71, No. 43 / Monday, March 6, 2006 / Rules and Regulations
Issued in Burlington, Massachusetts, on
February 24, 2006.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 06–1965 Filed 3–3–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001–NM–213–AD; Amendment
39–14479; AD 2006–03–15]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747SP, 747SR, 747–100, –100B,
–100B SUD, –200B, –200C, –200F, and
–300 Series Airplanes
Federal Aviation
Administration, DOT.
ACTION: Final rule.
hsrobinson on PROD1PC70 with RULES
AGENCY:
SUMMARY: This amendment adopts a
new airworthiness directive (AD),
applicable to all Boeing Model 747SP,
747SR, 747–100, –100B, –100B SUD,
–200B, –200C, –200F, and –300 series
airplanes, that requires modification of
the escape slide/raft pack assembly and
cable release sliders, as applicable. The
actions specified by this AD are
intended to prevent improper
deployment of the escape slide/raft or
blockage of the passenger/crew doors in
the event of an emergency evacuation,
which could result in injury to
passengers or crewmembers. This action
is intended to address the identified
unsafe condition.
DATES: Effective April 10, 2006.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of April 10,
2006.
ADDRESSES: The service information
referenced in this AD may be obtained
from Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington
98124–2207. This information may be
examined at the Federal Aviation
Administration (FAA), Transport
Airplane Directorate, Rules Docket,
1601 Lind Avenue, SW., Renton,
Washington.
FOR FURTHER INFORMATION CONTACT:
Keith Ladderud, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6435; fax (425) 917–6590.
VerDate Aug<31>2005
14:28 Mar 03, 2006
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A
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an airworthiness directive (AD)
that is applicable to all Boeing Model
747SP, 747SR, 747–100, –100B, –100B
SUD, –200B, –200C, –200F, and –300
series airplanes, was published as a
supplemental notice of proposed
rulemaking (NPRM) in the Federal
Register on August 23, 2005 (70 FR
49207). That action proposed to require
modification of the escape slide/raft
pack assembly and cable release sliders,
as applicable.
SUPPLEMENTARY INFORMATION:
Comments
Interested persons have been afforded
an opportunity to participate in the
making of this amendment. Due
consideration has been given to the
comments received.
Request To Change Paragraph (a)(1)
One commenter, the manufacturer,
disagrees with the language specified in
paragraph (a)(1) of the supplemental
NPRM as written. The commenter
reiterates that paragraph and states that
it disagrees with the content. The
commenter states that, if Boeing Service
Bulletin 747–25–2666, Revision 2, dated
April 24, 2003; and Goodrich Service
Bulletin 25–238, Revision 1, dated
January 31, 2003; have been
incorporated, the Door 3 ramp slide
pack (two-piece slide) will have been
replaced with a one-piece slide pack,
which does not have the cable
assemblies addressed by Boeing Service
Bulletin 747–25–3274, Revision 3, dated
December 16, 2004 (referenced in the
supplemental NPRM for accomplishing
certain actions). The one-piece slides
installed by Goodrich Service Bulletin
25–238 are specified in that service
bulletin.
We agree with the commenter and
have revised paragraph (a)(1) (reidentified as paragraph (a)(2) of the final
rule) as follows: ‘‘For airplanes on
which the modification of Door 3, as
specified in Boeing Special Attention
Service Bulletin 747–25–2666, Revision
2; and Goodrich Service Bulletin 25–
238, Revision 1; has been accomplished:
No further action is required for Door 3
only.’’
Request To Exclude Certain Airplanes
From the Applicability
One commenter asks that we change
the applicability section specified in the
supplemental NPRM. The commenter
states that not all the airplanes listed in
the applicability section are equipped
with the affected escape slide/raft pack
assembly components. The commenter
notes that it operates several Model
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747–100 series airplanes that do not
have the affected equipment installed.
The commenter adds that those
airplanes were originally designed and
manufactured with the cool gas
generator escape slide inflation system,
which does not include the affected
escape slide/raft pack assembly
components. Additionally, Boeing
Special Attention Service Bulletin 747–
25–3274 does not include those
airplanes in the effectivity, nor does it
include procedures for those airplanes.
The commenter asks that the
applicability section be changed to be
similar to that in AD 2004–03–17,
amendment 39–13461 (69 FR 6536,
February 11, 2004), which includes both
the affected airplane models and those
equipped with affected components.
We agree with the commenter and
have changed the applicability section
in this AD to exclude those airplanes
that do not have the affected equipment
installed, as follows: ‘‘Model 747SP,
747SR, 747–100, –100B, –100B SUD,
–200B, –200C, –200F, and –300 series
airplanes; certificated in any category;
equipped with an escape slide/raft pack
assembly; as identified in Boeing
Special Attention Service Bulletin 747–
25–3274, Revision 3, dated December
16, 2004.’’
Another commenter asks that the final
rule include a statement to the effect
that Model 747 airplanes converted to
the all-cargo configuration by any FAAapproved modification are excluded
from accomplishing the modification of
the slide required by the AD on any
main door that has had the slide
removed. The commenter suggests that
this would reduce the number of
requests submitted to the FAA for
alternative methods of compliance
(AMOC), thus reducing the use of FAA
resources. The commenter also states
that airplanes on which the escape
slides for the upper deck crew door
have been removed, in accordance with
Supplemental Type Certificate (STC)
ST01539SE, should be excluded from
the applicability section of the AD.
We agree with the commenter that
airplanes with an FAA-approved
modification of the main doors that
have the slides removed are not affected
by the unsafe condition and should not
be subject to this AD. Therefore, we
have changed the applicability section
in this AD to specify airplanes
‘‘equipped with an escape slide raft/
pack assembly’; which, in turn,
excludes airplanes on which the escape
slides for the upper deck crew door
have been removed in accordance with
STC ST01539SE.
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]]>Agencies
[Federal Register Volume 71, Number 43 (Monday, March 6, 2006)]
[Rules and Regulations]
[Pages 11153-11156]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-1965]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23605; Directorate Identifier 2005-NE-48-AD;
Amendment 39-14500; AD 2006-05-03]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc Models RB211 Trent 768-
60, Trent 772-60, and Trent 772B-60 Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Rolls-Royce plc (RR) models RB211 Trent 768-60, Trent 772-60, and Trent
772B-60 turbofan engines. This AD requires initial and repetitive
borescope inspections of the high pressure-intermediate pressure (HP-
IP) turbine bearing internal oil vent tube, scavenge tube, and tube
heat shields for wear and cracking, and removing tubes from service if
found with any cracks beyond serviceable limits. This AD also requires
installation of a new or modified HP-IP turbine bearings support as
terminating action for the repetitive borescope inspections. This AD
results from two reports of RR RB211 Trent 700 series engines found
with the HP-IP internal oil vent tube and scavenge tube fretted by
damaged heat shields on the tubes. We are issuing this AD to prevent
oil ejecting from the HP-IP turbine bearings chamber and igniting.
Burning oil can cause the intermediate pressure (IP) shaft to fracture,
the IP turbine to overspeed, and possible uncontained failure of the
engine.
DATES: Effective March 27, 2006. The Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulations as of March 27, 2006.
We must receive any comments on this AD by May 5, 2006.
ADDRESSES: Use one of the following addresses to comment on this AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ;
telephone: 011-44-1332-242424; fax: 011-44-1332-245418, for the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (781) 238-7175; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is
the airworthiness authority for the United Kingdom (UK), recently
notified us that an unsafe condition might exist on RR RB211 Trent 768-
60, Trent 772-60, and Trent 772B-60 turbofan engines. The CAA advises
that two RB211 Trent 700 series engines were removed due to high oil
consumption. Investigation revealed that damaged heat shields caused
fretting of the HP-IP internal oil vent tube and scavenge tube. A
previous service incident revealed that ingestion of HP cooling air
into either the scavenge tube or the vent tube can over pressurize the
HP-IP turbine bearing chamber. The overpressure can cause oil to eject
from the rear of the chamber. If the ejected oil ignites, the fire can
trigger fracture of the IP shaft, overspeed of the IP turbine, and
uncontained engine failure.
Relevant Service Information
We have reviewed and approved the technical contents of RR Alert
Service Bulletin RB.211-72-AE792, dated July 8, 2005, that describes
procedures for initial and repetitive borescope inspections of the HP-
IP turbine bearing internal oil vent tube, scavenge tube, and tube heat
shields for wear and cracking. We have also reviewed and approved the
technical contents of RR Service Bulletin RB.211-72-E708, Revision 2,
dated September 6, 2005, that describes procedures for installing a new
or modified HP-IP turbine bearings support. The CAA classified these
service bulletins as mandatory and issued AD G-2005-0016 in order to
ensure the airworthiness of these RR RB211 Trent 768-60, Trent 772-60,
and Trent 772B-60 turbofan engines in the UK.
Bilateral Airworthiness Agreement
These RR RB211 Trent 768-60, Trent 772-60, and Trent 772B-60
turbofan engines are manufactured in the UK and are 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. Under this bilateral
airworthiness agreement, the CAA kept the FAA informed of the situation
described above. We have 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
Although no airplanes that are registered in the United States use
these RR RB211 Trent 768-60, Trent 772-60,
[[Page 11154]]
and Trent 772B-60 turbofan engines, the possibility exists that the
engines could be used on airplanes that are registered in the United
States in the future. The unsafe condition described previously is
likely to exist or develop on other RR RB211 Trent 768-60, Trent 772-
60, and Trent 772B-60 turbofan engines of the same type design. We are
issuing this AD to prevent oil ejecting from the HP-IP turbine bearings
chamber and igniting. Burning oil can cause the IP shaft to fracture,
the IP turbine to overspeed, and possible uncontained failure of the
engine. This AD requires:
Initial and repetitive borescope inspections of the HP-IP
turbine bearing internal oil vent tube, scavenge tube, and tube heat
shields for wear and cracking; and
Removing tubes from service if found with any cracks
beyond serviceable limits; and
As terminating action to the repetitive inspections
required by the AD, at the next IP (05) module overhaul, but before May
31, 2010, removing the HP-IP bearings support introduced prior to
Rolls-Royce Modification 72-E708, and replacing with serviceable parts.
You must use the service information described previously to
perform the actions required by this AD.
FAA's Determination of the Effective Date
Since there are currently no domestic operators of this engine
model, notice and opportunity for public comment before issuing this AD
are unnecessary. 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 send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. FAA-2006-23605;
Directorate Identifier 2005-NE-48-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of the DMS Web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78) or you may visit
https://dms.dot.gov.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Under the authority delegated to me by the Administrator, the Federal
Aviation Administration 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 FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2006-05-03 Rolls-Royce plc: Amendment 39-14500. Docket No. FAA-2006-
23605; Directorate Identifier 2005-NE-48-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective March
27, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) models RB211 Trent
768-60, Trent 772-60, and Trent 772B-60 turbofan engines. These
engines are installed on, but not limited to, Airbus A330-243, A330-
341, A330-342, and A330-343 airplanes.
Unsafe Condition
(d) This AD results from two reports of RR RB211 Trent 700
series engines found with the high pressure-intermediate pressure
(HP-IP) internal oil vent tube and scavenge tube fretted by damaged
heat shields on the tubes. Burning oil can cause the intermediate
pressure (IP) shaft to fracture, the IP turbine to overspeed, and
possible uncontained failure of the engine. We are issuing this AD
to prevent oil ejecting from the HP-IP turbine bearings chamber and
igniting.
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.
[[Page 11155]]
Initial Borescope Inspection
(f) Perform an initial borescope inspection of the HP-IP turbine
bearing internal oil vent and scavenge tubes and tube heat shields
before the thresholds listed in Table 1 of this AD, or within 4
months after the effective date of this AD, whichever occurs later.
To do the inspections, use either the on-wing or the in-shop
inspection procedures in the Accomplishment Instructions of RR Alert
Service Bulletin (ASB) RB.211-72-AE792, dated July 8, 2005.
Table 1.--Inspection Criteria
------------------------------------------------------------------------
Action Inspection threshold
------------------------------------------------------------------------
(1) Initial inspection................. 10,000 hours time-since-new
(TSN) or time-since-overhaul
(TSO), or 2,500 cycles-since-
new (CSN) or cycles-since-
overhaul (CSO), whichever
occurs first.
(2) Repetitive inspection interval for 10,000 hours time-since-last-
tubes with no visible damage to outer inspection (TSLI), or 2,500
heat shields on the tubes. cycles-since-last-inspection
(CSLI), whichever occurs
first.
(3) Repetitive inspection interval for 6,400 hours TSLI or 1,600 CSLI,
tubes with cracking up to 90 degrees whichever occurs first.
around tube circumference or 10
millimeters along the length of either
outer heat shield.
(4) Repetitive inspection interval for 1,600 hours TSLI or 400 CSLI,
tubes with cracking greater than (3) whichever occurs first.
above, but less than 360 degrees
around the tube circumference.
------------------------------------------------------------------------
Repetitive Borescope Inspections
(g) Repeat the borescope inspections of the HP-IP turbine
bearing internal oil vent and scavenge tubes within the applicable
intervals listed in Table 1 of this AD. To do the inspections, use
either the on-wing or the in-shop inspection procedures in the
Accomplishment Instructions of RR ASB RB.211-72-AE792, dated July 8,
2005.
Removal of Damaged Tubes
(h) Within 10 CSLI, remove tubes with cracking around the
complete circumference of either outer heat shield, or if any
material is missing from either outer heat shield, or if either tube
is fretted by loose heat shield material.
Terminating Action
(i) As terminating action to the repetitive inspections required
by paragraph (g) of this AD, at the next IP (05) module overhaul,
but before May 31, 2010, remove the HP-IP bearings supports
introduced prior to Rolls-Royce Modification 72-E708 and replace
with serviceable parts. Information on Rolls-Royce Modification 72-
E708 can be found in RR Service Bulletin RB.211-72-E708, Revision 2,
dated September 6, 2005.
Definition
(j) For the purposes of this AD, serviceable parts are new or
reworked bearings supports which reduce the adverse effects of HP3
cooling air turbulence on the HP-IP turbine bearing internal oil
vent and scavenge tubes and tube heat shields, as described in
Rolls-Royce Modification 72-E708.
Alternative Methods of Compliance
(k) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Related Information
(l) Civil Aviation Authority airworthiness directive G-2005-
0016, dated July 6, 2005, also addresses the subject of this AD.
Material Incorporated by Reference
(m) You must use the service information specified in Table 2 of
this AD to perform the inspections and installations required by
this AD. The Director of the Federal Register approved the
incorporation by reference of the documents listed in Table 2 of
this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ;
telephone: 011-44-1332-242424; fax: 011-44-1332-245418, for a copy
of this service information. You may review copies at the Docket
Management Facility; U.S. Department of Transportation, 400 Seventh
Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-
0001, on the Internet at https://dms.dot.gov; or at the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call 202-741-6030, or go to:
https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Table 2.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Service Bulletin No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
RB.211-72-AE792............. All....................... Original.................. July 8, 2005.
Total Pages: 22
Appendix A of RB.211-72- All....................... Original.................. July 8, 2005.
AE792.
Total Pages: 3
----------------------------------------------------------------------------------------------------------------
[[Page 11156]]
Issued in Burlington, Massachusetts, on February 24, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 06-1965 Filed 3-3-06; 8:45 am]
BILLING CODE 4910-13-P
