[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