[Federal Register Volume 66, Number 155 (Friday, August 10, 2001)]
[Rules and Regulations]
[Pages 42105-42107]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-19936]



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  Federal Register / Vol. 66, No. 155 / Friday, August 10, 2001 / Rules 
and Regulations  

[[Page 42105]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-05-AD; Amendment 39-12373; AD 2001-16-05]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc. RB211 Trent Turbofan 
Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) that is applicable to Rolls-Royce plc. (RR) RB211 Trent 768-60, 
Trent 772-60, and Trent 772B-60 turbofan engines. That AD currently 
requires the removal of low pressure compressor (LPC) fan blades, 
initial and repetitive ultrasonic inspections for cracks in LPC fan 
blade dovetail roots, and if necessary, replacement with serviceable 
parts. This amendment requires earlier initial and more frequent 
repetitive ultrasonic inspections of LPC fan blades, with inspection 
thresholds and intervals specified by engine model. This amendment is 
prompted by data collected by RR, that identifies the need to inspect 
LPC fan blade dovetail roots at an earlier initial threshold and at 
more frequent intervals than is required by the existing AD. The 
actions specified in this AD are intended to prevent possible multiple 
LPC fan blade failures, which could result in an uncontained engine 
failure and damage to the airplane.

DATES: Effective date October 9, 2001. The incorporation by reference 
of certain publications listed in the rule is approved by the Director 
of the Federal Register as of October 9, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before October 9, 2001.

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: ``[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: 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: 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: On June 21, 2000, the FAA issued AD 2000-13-
05, Amendment 39-11804 (65 FR 40983, July 3, 2000), to require initial 
and repetitive ultrasonic inspections for cracks in LPC fan blade 
dovetail roots, and if necessary, replacement with serviceable parts. 
That action was prompted by reports of LPC fan blade dovetail root 
cracks in a factory engine. That condition, if not corrected, could 
result in an uncontained engine failure and damage to the airplane.
    Since that AD was issued, data has been collected by RR that 
identifies the need to ultrasonically inspect LPC fan blade dovetail 
roots at earlier initial thresholds and at more frequent repetitive 
inspection intervals, than is required by the current AD. RR has also 
determined that the different Trent engine models require different 
initial and repetitive inspection interval requirements. RR has also 
instituted a procedure to allow repetitive ultrasonic inspections of 
LPC fan blade dovetail roots on blades not removed from the engine.

Manufacturer's Service Information

    Rolls-Royce plc. has issued service bulletin (SB) No. RB.211-72-
C878, Revision 4, dated January 22, 2001, that:
     Specifies procedures for removing LPC fan blades and 
performing initial and repetitive ultrasonic inspections for cracks in 
LPC fan blade dovetail roots, at earlier initial thresholds and at more 
frequent repetitive inspection intervals, than the inspections required 
by the current AD.
     Specifies that the different Trent engine models require 
different initial and repetitive inspection intervals.
     Adds a procedure that does not require blade removal from 
the engine in order to perform repetitive ultrasonic inspections for 
cracks in LPC fan blade dovetail roots.
     Requires that for the initial inspection and for at least 
every third inspection interval thereafter, the LPC fan blades be 
removed from the engine, to be ultrasonically inspected.

The Civil Aviation Authority (CAA), which is the airworthiness 
authority for the United Kingdom (UK), classified this SB as mandatory 
and issued AD 003-11-99 in order to assure 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. 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 for products of this type design that are certificated for 
operation in the United States.

FAA's Determination of an Unsafe Condition and Proposed Actions

    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. Since an unsafe 
condition has been identified that is likely to exist or develop on 
other RR RB211 Trent 768-

[[Page 42106]]

60, Trent 772-60, and Trent 772B-60 turbofan engine models of the same 
type design, this AD is being issued to prevent possible multiple LPC 
fan blade failures, which could result in an uncontained engine failure 
and damage to the airplane. This AD requires:
     Initial ultrasonic inspections of the fan blade root with 
blades removed,
     Repetitive ultrasonic inspections of the fan blade root 
with blades removed or installed, and
     Ultrasonic inspection to be done with the fan blades 
removed at least every third inspection. The actions are required to be 
accomplished in accordance with the service bulletin described 
previously.

Immediate Adoption of This AD

    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 action 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 final 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 final 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 removing Amendment 39-11804 (65 FR 
40983, July 3, 2000) and adding a new airworthiness directive, 
Amendment 39-12373, to read as follows:

2001-16-05: Rolls-Royce plc. Amendment 39-12373. Docket 2000-NE-05-
AD. Supersedes AD 2000-13-05, Amendment 39-11804.

    Applicability: This airworthiness directive (AD) is applicable 
to Rolls-Royce plc. (RR) RB211 Trent 768-60, Trent 772-60, and Trent 
772B-60 turbofan engine models with Low Pressure Compressor (LPC) 
fan blade part numbers (P/N's) FK22580, FK23411, FK25441, and 
FK25968 installed. These engines are installed on, but not limited 
to Airbus Industrie 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 (f) 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.
    To prevent possible multiple LPC fan blade failures, which could 
result in an uncontained engine failure and damage to the airplane, 
do the following:

Initial Ultrasonic Inspection

    (a) For fan blades P/N's FK22580, FK23411, FK25411, and FK25968, 
do an initial ultrasonic inspection of the dovetail roots in 
accordance with Accomplishment Instructions, Section 3.A. (Method A, 
blades removed from engine) of Rolls-Royce (RR) Service bulletin 
(SB) RB.211-72-C878, Revision 4, dated January 22, 2001, at or 
before the cycles-since-new (CSN) requirements of Table 1 of this 
AD:

[[Page 42107]]



                       Table 1.--Initial and Repetitive Ultrasonic Inspection Requirements
----------------------------------------------------------------------------------------------------------------
                                  Cycles-since-new                           Repetitive           Repetitive
                                    (CSN) on the           Initial           inspection           inspection
          Engine model            effective date of      inspection        interval using       interval using
                                       this AD                              3.A method A.       3.B. method B.
----------------------------------------------------------------------------------------------------------------
(1) 768-60 and 772-60..........  (i) Fewer than      Before              340 cycles-since-   280 CSLI.
                                  2,000 CSN.          accumulating        last-inspection
                                                      2,000 CSN.          (CSLI).
                                 (ii) 2,000 CSN or   Within 100 cycles-  340 cycles-since-   280 CSLI.
                                  more.               in-service (CIS)    last-inspection
                                                      after the           (CSLI).
                                                      effective date of
                                                      this AD.
(2) 772B-60....................  (i) Fewer than      Before              250 CSLI..........  200 CSLI.
                                  1,000 CSN.          accumulating
                                                      1,000 CSN.
 
r                                (ii) 1,000 CSN or   Within 100 CIS      250 CSLI..........  200 CSLI.
                                  more.               after the
                                                      effective date of
                                                      this AD.
----------------------------------------------------------------------------------------------------------------

Credit for Previous Inspections

    (b) Previous inspections performed using RR SB RB.211-72-C878, 
Revision 1, dated December 10, 1999; RR SB RB.211-72-C878, Revision 
2, dated November 13, 2000; RR SB RB.211-72-C878, Revision 3, dated 
January 3, 2001, comply with the initial inspection requirements of 
paragraph (a) of this AD.

Repetitive Ultrasonic Inspections

    (c) Inspect LPC fan blades in accordance with either 
Accomplishment Instructions, Section 3.A. (Method A, blades removed 
from engine), or Section 3.B. (Method B, blades installed in 
engine), of RR SB RB.211-72-C878, Revision 4, dated January 22, 
2001, at or before CSLI interval requirements in Table 1 of this AD.

Removed Blades for Every Third Ultrasonic Inspection Interval

    (d) For at least every third ultrasonic inspection interval, 
inspect LPC fan blades in accordance with Accomplishment 
Instructions, Section 3.A. (Method A, blades removed from engine) of 
RR SB RB.211-72-C878, Revision 4, dated January 22, 2001.

LPC Fan Blade Disposition

    (e) Before further flight, remove from service cracked or 
suspect cracked fan blades which do not meet the acceptance criteria 
of Appendix 1, Section 4, paragraph B, or Appendix 2, Section 4, 
paragraphs B and C, of RR SB RB.211-72-C878, Revision 4, dated 
January 22, 2001.

Alternative Methods of Compliance

    (f) 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 must 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

    (g) 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 aircraft to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (h) The actions required by this AD must be performed in 
accordance with Rolls-Royce plc. Service Bulletin No. RB.211-72-
C878, Revision 4, dated January 22, 2001. 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

    (i) This amendment becomes effective on October 9, 2001.

    Issued in Burlington, Massachusetts, on August 1, 2001.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 01-19936 Filed 8-9-01; 8:45 am]
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