Airworthiness Directives; Rolls-Royce plc Models RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 Turbofan Engines

[Federal Register Volume 71, Number 43 (Monday, March 6, 2006)]
[Rules and Regulations]
[Pages 11153-11156]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-1965]


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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.

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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:
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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:
    <bullet> 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
    <bullet> Removing tubes from service if found with any cracks 
beyond serviceable limits; and
    <bullet> 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 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 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 http://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: 
http://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
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[[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

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