[Federal Register Volume 65, Number 128 (Monday, July 3, 2000)]
[Rules and Regulations]
[Pages 40983-40985]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-16231]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-05-AD; Amendment 39-11804; AD 2000-13-05-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc. RB211 Trent 768-60, 
Trent 772-60, and Trent 772B-60 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. (RR) RB211 Trent 768-60, Trent 772-
60, and Trent 772B-60 turbofan engines. This action requires initial 
and repetitive ultrasonic inspections for cracks in fan blade dovetail 
roots, and if necessary, replacement with serviceable parts. This 
amendment is prompted by reports of fan blade failures due to dovetail 
root cracks. The actions specified in this AD are intended to prevent 
possible multiple fan blade failures, which could result in an 
uncontained engine failure and damage to the airplane.

DATES: Effective August 2, 2000. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of August 2, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before September 1, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2000-NE-05-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be sent 
via the Internet using the following address: ``<a href="/cdn-cgi/l/email-protection#95acb8f4f1b8f0fbf2fcfbf0e5e7fae5d5f3f4f4bbf2fae3"><span class="__cf_email__" data-cfemail="83baaee2e7aee6ede4eaede6f3f1ecf3c3e5e2e2ade4ecf5">[email protected]</span></a>.'' 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: 011-44-1332-
249428; fax 011-44-1332-249223. 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: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone 781-
238-7176; fax 781-238-7199.

SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is 
the airworthiness authority for the United Kingdom (U.K.), recently 
notified the FAA that an unsafe condition may exist on Rolls-Royce plc. 
(RR) RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan 
engines with fan blade part numbers (P/N's) FK22580, FK23411, FK25441, 
and FK25968 installed. The CAA received a report of multiple fan blade 
root cracks in a factory engine. A recent inspection of a set of fan 
blades from a factory fleet leader test engine has identified small 
cracks in the blade roots on the convex root flank. To date, this is 
the only engine that has exhibited the blade root cracks. This 
condition, if not corrected, could result in possible multiple fan 
blade failures, which could result in an uncontained engine failure and 
damage to the airplane.

Manufacturer's Service Information

    Rolls-Royce plc (RR) has issued service bulletin (SB) No. RB.211-
72-C878, Revision 1, dated December 10, 1999, that specifies procedures 
for ultrasonic inspections for cracks in fan blade dovetail roots. The 
CAA classified this SB as mandatory and issued airworthiness directive 
(AD) 003-11-99 in order to assure the airworthiness of these engines in 
the U.K.

Differences Between This AD and the Manufacturer's Service 
Information

    This AD applies only to those engines with fan blades having four 
specific part numbers. The manufacturer's service bulletin is not 
limited in that fashion. The FAA expects that future changes in the 
design of the affected fan blades will eliminate the need for the 
required inspections and that those newer fan blades will have 
different part numbers. The installation of the newer part number will 
therefore have the effect of removing the engine from the applicability 
of this AD.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the U.K. 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. Pursuant to 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

[[Page 40984]]

for products of this type design that are certificated for operation in 
the United States.

Requirements of This AD

    Although none of these affected engine models are used on any 
airplanes that are registered in the United States, the possibility 
exists that the engine models could be used on airplanes that are 
registered in the United States in the future. Because an unsafe 
condition has been identified that is likely to exist or develop on 
other RR RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 series 
turbofan engines of the same type design, with fan blade P/N's FK22580, 
FK23411, FK25441, and FK25968 installed, this AD requires:
    <bullet> Initial ultrasonic inspections within 200 cycles after the 
effective date of this AD, or within 200 cycles of achieving 2,800 
cycles since new, whichever is later; and
    <bullet> Repetitive ultrasonic inspection of the fan blade root 
within 340 cycles since the last inspection.
    The actions are required to be completed in accordance with the 
service bulletin described previously.

Immediate Adoption

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

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 
in triplicate 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-05-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    This proposed rule does not have federalism implications, as 
defined in Executive Order 13132, because it would 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. 
Accordingly, the FAA has not consulted with state authorities prior to 
publication of this proposed rule.
    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 Executive Order 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:

2000-13-05  Rolls-Royce plc: Amendment 39-11804. Docket 2000-NE-05-
AD.

Applicability

    This AD is applicable to Rolls-Royce plc. (RR) RB211 Trent 768-
60, Trent 772-60, and Trent 772B-60 turbofan engines with fan blade 
part numbers (P/N's) FK22580, FK23411, FK25441, and FK25968 
installed. These engines are installed on but not limited to Airbus 
A330-341 and A330-342 series airplanes.

    Note 1: This airworthiness directive (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 (b) 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

    Compliance with this AD is required as indicated below, unless 
already completed.
    To prevent possible multiple fan blade failures, which could 
result in an uncontained engine failure and damage to the airplane, 
do the following:

Ultrasonic Inspections

    (a) Ultrasonically inspect the dovetail roots of all fan blade 
P/N's FK22580, FK23411, FK25441, and FK25968 with more than 2800 
cycles since new (CSN), for cracks as follows:

Initial Inspection

    (1) Initially inspect the fan blade in accordance with paragraph 
3.A.(1) or paragraph 3.B.(1) through paragraph 3.B.(8) of RR service 
bulletin (SB) No. RB.211-72-C878, revision 1, dated December 10, 
1999, at the later of the following:
    (i) Within 200 fan blade cycles in service (CIS) after the 
effective date of this AD; or
    (ii) Within 200 fan blade CIS of achieving 2800 CSN.

Repetitive Inspections

    (2) Thereafter, inspect at intervals not to exceed 340 CIS, 
since last inspection, in accordance with paragraph 3.A.(1) or 
paragraph 3.B.(1) through paragraph 3.B.(8) of RR SB No. RB.211-72-
C878, revision 1, dated December 10, 1999.

Alternative Methods of Compliance

    (b) 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

[[Page 40985]]

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 airworthiness directive, 
if any, may be obtained from the ECO.

Special Flight Permits

    (c) 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 Material

    (d) The actions required by this AD shall be performed in 
accordance with the following service documents:

----------------------------------------------------------------------------------------------------------------
            Document No.                     Pages               Revision                     Date
----------------------------------------------------------------------------------------------------------------
RB.211-72-C878.....................  1-2.................  1..................  December 10, 1999
                                     3-4.................  Original...........  November 19, 1999
                                     Appendix............  Original...........  November 19, 1999
    Total pages: 7.................
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    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: 011-44-1332-249428; fax: 011-44-1332-
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

    (e) This amendment becomes effective on August 2, 2000.

    Issued in Burlington, Massachusetts, on June 21, 2000.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-16231 Filed 6-30-00; 8:45 am]
BILLING CODE 4910-13-U


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