[Federal Register: November 14, 2006 (Volume 71, Number 219)]
[Rules and Regulations]
[Page 66229-66231]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14no06-1]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
[[Page 66229]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26052; Directorate Identifier 2006-NE-30-AD;
Amendment 39-14823; AD 2006-23-11]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce, plc RB211 Trent 768-60,
772-60, and 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) RB211 Trent 768-60, 772-60, and 772B-60 turbofan
engines. This AD requires initial and repetitive on-wing or in-shop
inspections of the high pressure (HP)/intermediate pressure (IP)
turbine bearing oil feed tube heat shield. This AD results from a
report that a damaged outer heat shield caused fretting of the oil feed
tubes. We are issuing this AD to prevent an uncontained failure of the
HP turbine disc and damage to the airplane.
DATES: Effective December 19, 2006. The Director of the Federal
Register approved the incorporation by reference of certain
publications listed in the regulations as of December 19, 2006.
We must receive any comments on this AD by January 16, 2007.
ADDRESSES: Use one of the following addresses to comment on this AD:
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://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.
FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803;
telephone (781) 238-7175; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The European Aviation Safety Agency (EASA)
which is the airworthiness authority for the European Union, recently
notified us that an unsafe condition may exist on RR RB211 Trent 768-
60, 772-60 and 772B-60 turbofan engine. EASA advises that a Trent 700
engine was removed due to oil loss and low-oil pressure. Investigation
established that a damaged outer heat shield caused fretting of the HP/
IP turbine bearing oil feed tubes. Oil leakage from the oil feed tube
at the outer heat shield position traveled forward to the cavity in
front of the HP/IP turbine support structure and ignited. The fire
caused localized heat damage to the rear of the HPT disc. This incident
illustrated the possibility for overheating and failure of the HPT disc
resulting from deterioration of the oil feed tube heat shield.
Relevant Service Information
We have reviewed and approved the technical contents of RR Alert
Service Bulletin (ASB) No. RB.211-72-AF045, Revision 2, dated July 27,
2006. That ASB describes procedures for initial and repetitive on-wing
or in-shop inspections for cracks in the HP/IPT oil feed tube outer
heat shield. The CAA issued AD No. 2006-0073, dated April 3, 2006, in
order to ensure the airworthiness of these RR engines in the United
Kingdom.
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. 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 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, 772-60, and 772B-60 turbofan engines of
the same type design. We are issuing this AD to prevent uncontained
failure of the HPT disc and damage to the airplane. This AD requires:
An initial on-wing inspection of the oil feed tube heat
shield within 10,000 hours or 2,500 cycles on the 05 module since new
or overhaul or within 30 days after the effective date of this AD,
whichever is later, or
An initial in-shop inspection of the heat shield of oil
feed tube during a shop visit of the module 05 where the module 05 is
not scheduled for overhaul or within 30 days after the effective date
of this AD, whichever is later.
Thereafter, a repetitive inspection of the heat shield of
oil feed tube at an interval determined by the condition of the heat
shield.
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
[[Page 66230]]
arguments regarding this AD. Send your comments to an address listed
under ADDRESSES. Include ``AD Docket No. FAA-2006-26052; Directorate
Identifier 2006-NE-30-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 http://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
http://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 Offices 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. You may get a copy of this summary at the
address listed under ADDRESSES.
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:
2006-23-11 Rolls-Royce plc: Amendment 39-14823. Docket No. FAA-2006-
26052; Directorate Identifier 2006-NE-30-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
19, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 768-60,
772-60, and 772B-60 turbofan engines that do not incorporate RR
Service Bulletin RB.211-71-F117 or RB.211-72-048. These engines are
installed on, but not limited to, Airbus A330 series airplanes.
Unsafe Condition
(d) This AD results from a report that a damaged outer heat
shield fretted the oil feed tubes. We are issuing this AD to prevent
an uncontained failure of the high pressure (HP) turbine disc 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 Inspection
(f) Initially inspect the HP/IP turbine oil feed tube outer heat
shield for cracks. Use either 3.A.(1) through 3.A.(3) on-wing
procedures or 3.B.(1)(a) through 3.B.(1)(e) in-shop procedures of RR
ASB RB.211-72-AF045, Revision 2, dated July 27, 2006, at one of the
following compliance times:
(1) At the next shop visit of the 05 Module regardless of the
reason for the visit, or
(2) Before one of the following intervals whichever occurs
latest:
(i) 30 days from the effective date of this AD, or
(ii) 10,000 hours or 2,500 cycles since new, whichever occurs
first, or
(iii) 2,500 cycles since overhaul of the 05 Module.
Repetitive Inspection
(g) Re-inspect the HP/IP turbine oil feed tube outer heat shield
for cracks as specified in the applicable criteria of paragraphs
C.(1)(b)(i) through C(1)(b)(vi) or C(2)(b)(i) through C(2)(b)(ii) of
RR ASB RB.211-72-AF045, Revision 2, dated July 27, 2006. Use either
3.A.(1) through 3.A.(3) on-wing procedures or 3.B.(1)(a) through
3.B.(1)(e) in-shop procedures of RR ASB RB.211-72-AF045, Revision 2,
dated July 27, 2006.
Remove HP/IP Turbine Oil Feed Tube Outer Heat Shields From Service
(h) Remove from service HP/IP turbine oil feed tube outer heat
shields according to the applicable criteria in paragraphs
C(1)(b)(vii) through C(1)(b)(vii) or C(2)(b)(iii) of RR ASB RB.211-
72-AF045, Revision 2, dated July 27, 2006.
Alternative Methods of Compliance
(i) 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
(j) EASA airworthiness directive 2006-0073, dated April 3, 2006,
also addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use Rolls-Royce Alert Service Bulletin No. RB.211-
72-AF045, Revision 2, dated July 27, 2006, to perform the
inspections required by this AD. The Director of the Federal
Register approved the incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Rolls-Royce plc P.O. Box 31, Derby, DE24 8BJ, United
Kingdom; telephone 44 (0) 1332 242424; Fax 44 (0) 1332 249936 for a
copy of this service
[[Page 66231]]
information. 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: http://www.archives.gov/
federal-register/cfr/ ibr-locations.html.
Issued in Burlington, Massachusetts, on November 3, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E6-18964 Filed 11-13-06; 8:45 am]
BILLING CODE 4910-13-P