[Federal Register Volume 68, Number 1 (Thursday, January 2, 2003)]
[Rules and Regulations]
[Pages 25-26]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-32888]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-28-AD; Amendment 39-12956; AD 2002-23-12]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Limited, Aero Division-
Bristol, S.N.E.C.M.A. Olympus 593 Mk. 610-14-28 Turbojet 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 Limited, Aero Division-Bristol, 
S.N.E.C.M.A (RR) Olympus 593 Mk. 610-14-28 turbojet engines. This 
action requires a one-time fluorescent penetrant inspection (FPI) of 
certain rebroached stage 5 high pressure compressor (HPC) disks, 
inspecting for cracks, and if necessary, removing cracked disks from 
service. This amendment is prompted by a manufacturer's analysis that 
concluded that the rebroaching process failed to achieve the 
anticipated life before being rejected for cracks and that the original 
cracks are not being removed. The actions specified in this AD are 
intended to prevent failure of the HPC stage 5 disk which could result 
in an uncontained engine failure and damage to the airplane.

DATES: Effective January 17, 2003. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of January 17, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before March 3, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2002-NE-28-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8:00 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. 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 Defence (Europe) Technical Publications Department, P.O. 
Box 3, Filton, Bristol BS34 7QE, England; telephone 011 7979 6060; Fax 
011 7979 7234. This information may be examined, by appointment, 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: Glorianne Niebuhr, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7132; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is 
the airworthiness authority for the United Kingdom (UK), notified the 
FAA that an unsafe condition may exist on Bae/SNIAS Concorde Type 1 
airplanes with RR Olympus 593 Mk. 610-14-28 turbojet engines. The CAA 
advises that if the disks were not rebroached correctly, certain HPC 
stage 5 disks may fail to achieve their anticipated cyclic life limit 
before cracking. Service experience with HPC stage 6 disks that were 
rebroached using a similar process demonstrated that the disks failed 
to achieve the anticipated life limit before being rejected for cracks. 
Further investigation revealed that original cracks were not being 
removed by the rebroaching. Therefore, a review of the HPC stage 5 
disks was done. The analysis indicated that certain HPC stage 5 disks 
needed to be inspected between specific cyclic intervals to ensure that 
they have no cracks and that they can then achieve their previously 
anticipated life. At the time the CAA AD was originally written, there 
were a number of uninspected disks. Currently, there are only two HPC 
stage 5 disks that have not been inspected.

Manufacturer's Service Information

    RR has issued Olympus 593 MSB No. OL.593-72-8951-364, Revision 7, 
dated November 23, 2001, that specifies the inspection requirements for 
certain HPC stage 5 disks. The CAA classified this service bulletin as 
mandatory and issued AD 006-07-98 in order to ensure the airworthiness 
of these RR engines in the UK.

Differences Between the Manufacturers Service Information and This AD

    RR has issued Olympus 593 MSB No. OL.593-72-9051-428, Revision 1, 
dated November 16, 2001, that requires disk P/N B510911, SN J14CA, to 
be inspected within 200 to 958 cycles-in-service (CIS) after 
rebroaching and disk P/N B510909, SN JZJ66, to be inspected within 200 
to 931 CIS after rebroaching. However, since none of these engines are 
installed on airplanes of the U.S. registry, the FAA requires that they 
be inspected before further flight.

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 Required 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 Olympus 593 Mk. 610-14-28 turbojet engines of the same type 
design, this AD is being issued to prevent failure of the HPC stage 5 
disk, which could result in an uncontained engine failure and damage to 
the airplane. This AD requires a one-time fluorescent penetrant 
inspection (FPI) of certain rebroached HPC stage 5 disks, inspecting 
for cracks, and if necessary, removing cracked disks from service. The 
actions must be done 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.

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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 2002-NE-28-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    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 adding the following new 
airworthiness directive:

2002-23-12 Rolls-Royce Limited Aero Division-Bristol, S.N.E.C.M.A.: 
Amendment 39-12956. Docket No. 2002-NE-28-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Rolls-Royce Limited, Aero Division-Bristol, S.N.E.C.M.A. (RR) 
Olympus 593 Mk. 610-14-28 turbojet engines with high pressure 
compressor (HPC) stage 5 disk part number (P/N) B510911, serial 
number (SN) J14CA and P/N B510909, SN JZJ66. These engines are 
installed on, but not limited to, BAe/SNIAS Concorde Type 1 
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: Compliance with this AD is required before further 
flight after the effective date of this AD, unless already done.
    To prevent failure of the HPC stage 5 disk due to cracking, 
which could result in an uncontained engine failure and damage to 
the airplane, do the following:
    (a) Before further flight, inspect HPC stage 5 disks P/N 
B510911, SN J14CA and P/N B510909, SN JZJ66, in accordance with 
Accomplishment Instructions 2.A.(1) through 2.A.(2) of Rolls-Royce 
(RR) Olympus 593 Mandatory Service Bulletin (MSB) OL.593-72-8951-
364, Revision 7, dated November 23, 2001.
    (b) If the stage 5 HPC disk is found cracked, it must be removed 
and replaced with a serviceable part.

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. 
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

    (d) Special flight permits may be issued in accordance with 
Sec. Sec.  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 done.

Documents That Have Been Incorporated by Reference

    (e) The inspection must be done in accordance with Rolls-Royce 
Olympus 593 Mandatory Service Bulletin (MSB) OL.593-72-8951-364, 
Revision 7, dated November 23, 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 Defence (Europe) Technical Publications Department, P.O. 
Box 3, Filton, Bristol BS34 7QE, England; telephone 011 7979 6060; 
Fax 011 7979 7234. Copies may be inspected, by appointment, 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.

    Note 3: The subject of this AD is addressed in CAA airworthiness 
directive 006-07-98.

Effective Date

    (f) This amendment becomes effective on January 17, 2003.

    Issued in Burlington, Massachusetts, on November 15, 2002.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-32888 Filed 12-31-02; 8:45 am]
BILLING CODE 4910-13-P