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

[Federal Register Volume 65, Number 240 (Wednesday, December 13, 2000)]
[Rules and Regulations]
[Pages 77776-77778]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-31113]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-37-AD; Amendment 39-12031; AD 2000-24-24]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Rolls-Royce plc RB211 Trent 768-60, Trent 772-60, and 
Trent 772B-60 series turbofan engines having common nozzle assembly 
part number (P/N) FK16544 or FK16558. This action requires initial and 
repetitive visual inspections of the inner and outer skins of the 
common nozzle assembly and specifies allowable limits for cracks, loose 
rivets, and missing rivets. This action also requires repair if the 
common nozzle assembly damage exceeds allowable limits. This amendment 
is prompted by two reports of in-flight inner skin detachment. The 
actions specified in this AD are intended to detect cracks, loose 
rivets, and missing rivets, which could result in inner skin 
detachment, release of common nozzle assembly debris from the engine, 
and possible damage to the airplane control surfaces.

DATES: Effective January 12, 2001. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of January 12, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before February 12, 2001.

ADDRESSES: Submit comments to the Federal Aviation Administration 
(FAA), New England Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 2000-NE-37-AD, 12 New England Executive Park, 
Burlington, MA 01803-5299. Comments may also be sent via the Internet 
using the following address: ``[email protected]''. Comments sent 
via the Internet must contain the docket number in the subject line.
    The service information referenced in this AD may be obtained from 
Rolls-Royce plc, PO Box 31, Derby, England; telephone: International 
Access Code 011, Country Code 44, 1332-249428, fax International Access 
Code 011, Country Code 44, 1332-249223. This information may be 
examined at the FAA, New England Region, Office of the Regional 
Counsel, 12 New England Executive Park, Burlington, MA; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Keith Mead, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone: 781-238-
7744; fax: 781-238-7199.

SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is 
the airworthiness authority for the United Kingdom (UK), recently 
notified the Federal Aviation Administration (FAA) that an unsafe 
condition may exist on Rolls-Royce plc (RR) RB211 Trent 768-60, Trent 
772-60, and Trent 772B-60 series turbofan engines having common nozzle 
assembly P/N FK16544 or FK16558. The CAA received reports of cracking 
and rivet loss on the outer and inner skin of the common nozzle 
assembly, with two reports of inner skin detachment. Rolls-Royce has 
determined that cracks and detachment of inner skin, and cracks of 
outer skin occurred due to a combination of missing rivets, loose 
rivets, and high stress levels on common nozzle assemblies with a high 
number of flight cycles. This condition, if not corrected, could result 
in inner skin detachment, release of common nozzle assembly debris from 
the engine, and possible damage to the airplane control surfaces. The 
compliance times specified in this AD are based on Rolls-Royce service 
bulletin criteria and CAA recommendations.

Manufacturer's Service Information

    RR has issued Mandatory Service Bulletin (MSB) No. RB.211-78-C931, 
Revision 1, dated June 13, 2000, that specifies procedures for initial 
visual inspections of inner and outer skin, including allowable limits, 
for cracks, missing rivets, and loose rivets. The MSB also specifies 
repair for common nozzle assemblies that are out of limits. The MSB 
also specifies on common nozzle assemblies with more than 1,500 cycles-
since-new, initial visual inspections for cracks in inner and outer 
skins, missing rivets, loose rivets not later than 500 flight hours 
after release of AD, and repetitive inspections within 500 flight hours 
since the last inspection. The CAA classified this MSB as mandatory and 
issued airworthiness directive (AD) 005-06-

[[Page 77777]]

2000 in order to ensure the airworthiness of these engines in the UK.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the UK 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. As required by 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 engines of this type design that could be used on 
airplanes certificated for operation in the United States.

Required Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other engines of the same type design that could be 
used on airplanes registered in the United States, this AD requires 
initial and repetitive in-service visual inspections of the common 
nozzle assembly to detect cracks, missing rivets, and loose rivets, 
including allowable acceptance limits. This AD also requires repair for 
common nozzle assemblies that are out of limits. The actions must be 
done in accordance with the MSB described previously.

Immediate Adoption

    A situation exists that allows the immediate adoption of this 
regulation. Since there are currently no domestic operators of this 
engine model, notice and opportunity for prior public comment are 
unnecessary.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NE-37-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    This proposal does not have federalism implications, as defined in 
Executive Order (EO) 13132, because it would not have 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this proposal.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under EO 12866. It has been determined further that this action 
involves an emergency regulation under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979). If it is determined that 
this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket. A copy of it, if filed, may 
be obtained from the Rules Docket at the location provided under the 
caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to 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

    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]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2000-24-24  Rolls-Royce plc: Amendment 39-12031. Docket 2000-NE-37-
AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Rolls-Royce plc (RR) RB211 Trent 768-60, Trent 772-60, and Trent 
772B-60 series turbofan engines having common nozzle assembly part 
number (P/N) FK16544 or FK16558 installed. These engines are 
installed on but not limited to Airbus A330-341 and A330-342 series 
airplanes.

    Note 1: This AD applies to each engine identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For engines that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (c) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

Compliance

    Required as indicated, unless accomplished previously.
    To detect cracking, loose rivets, and missing rivets on common 
nozzle assembly P/N FK16544 or FK16558, which could result in inner 
skin detachment, release of exit nozzle debris from the engine, and 
possible damage to the airplane control surfaces, do the following:

Initial Inspection

    (a) Visually inspect all common nozzle assemblies for cracks, 
missing rivets, and loose rivets, within 500 flight hours after the 
effective date of this AD, and disposition in accordance with 
Accomplishment Instructions, Paragraph 3A of RR Mandatory Service 
Bulletin (MSB) No. RB.211-78-C931, Revision 1, dated June 13, 2000.

Repetitive Inspections

    (b) Thereafter, on common nozzle assemblies that have greater 
than 1,500 cycles-since-new, do repetitive visual inspection for 
cracks, loose rivets, and missing rivets, within 500 flight hours 
since the last inspection, and disposition in accordance with 
Accomplishment Instructions, Paragraph 3A of RR MSB No. RB.211-78-
C931, Revision 1, dated June 13, 2000.

[[Page 77778]]

Alternative Methods of Compliance

    (c) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office (ECO). 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the ECO.

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (e) The actions required by this AD must be performed in 
accordance with the Accomplishment Instructions of RR MSB No. 
RB.211-78-C931, Revision 1, dated June 13, 2000. This incorporation 
by reference was approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
obtained from Rolls-Royce plc, PO Box 31, Derby, England; telephone: 
International Access Code 011, Country Code 44, 1332-249428, fax: 
International Access Code 011, Country Code 44, 1332-249223. Copies 
may be inspected at the FAA, New England Region, Office of the 
Regional Counsel, 12 New England Executive Park, Burlington, MA; or 
at the Office of the Federal Register, 800 North Capitol Street, NW, 
suite 700, Washington, DC.

Effective Date of This AD

    (f) This amendment becomes effective on January 12, 2001.

    Issued in Burlington, Massachusetts, on November 28, 2000.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-31113 Filed 12-12-00; 8:45 am]
BILLING CODE 4910-13-U

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