[Federal Register Volume 63, Number 122 (Thursday, June 25, 1998)]
[Rules and Regulations]
[Pages 34578-34580]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-16467]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-15-AD; Amendment 39-10612; AD 98-13-21]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Limited, Aero Division-
Bristol, S.N.E.C.M.A Olympus 593 Series 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 Olympus 593 series turbojet engines. This action requires 
initial and repetitive visual inspections of the low pressure (LP) 
shaft signal system for cable wear and refurbishment of the LP shaft 
signal system at when the cable is found frayed, or at every engine 
shop visit, whichever occurs first. This amendment is prompted by 
reports of frayed rear cables in the LP shaft signal system. The 
actions specified in this AD are intended to prevent LP shaft signal 
system failure, which could result in an LP turbine overspeed, burst, 
uncontained engine failure, and damage to the aircraft in the event of 
a LP shaft failure.

DATES: Effective July 10, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 10, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before August 24, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 98-ANE-15-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be sent 
via the Internet using the following address: ``9-ad-
[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, PO Box 3, Filton, Bristol BS12 7QE, England; telephone 01-
17-979-1234, fax 01-17-979-7575. 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: Jason Yang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7747, 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 Limited (R-R), Aero Division-
Bristol, S.N.E.C.M.A. Olympus 593 Mk. 610-14-28 turbojet engines. The 
CAA advises that they have received reports of frayed rear cables in 
the low pressure (LP) shaft signal system. The LP shaft signal system 
prevents the LP turbine disk from bursting in the event of LP shaft 
failure by cutting off the fuel when excess twist is detected in the 
shaft. The rear cable activates the fuel shut-off valve. This 
condition, if not corrected, could result in LP shaft signal system 
failure, which could result in an LP turbine overspeed, burst, 
uncontained engine failure, and damage to the aircraft in the event of 
a LP shaft failure.
    There are currently no affected engines operated on aircraft of 
U.S. registry. This AD, then, is necessary to require accomplishment of 
the required actions for engines installed on aircraft currently of 
foreign registry that may someday be imported into the U.S or which may 
be operated in U.S. airspace. Accordingly, the FAA has determined that 
notice and prior opportunity for comment are unnecessary and good cause 
exists for making this amendment effective in less than 30 days.
    R-R has issued Service Bulletin (SB) No. OL.593-76-9039-71, 
Revision 2, dated July 23, 1997, that specifies procedures for visual 
inspection of the LP shaft signal system for cable wear and 
refurbishment of the LP shaft signal system. The CAA classified this SB 
as mandatory and issued AD 009-09-97 in order to assure the 
airworthiness of these engines in the UK.
    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.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other engines of the same type design registered in 
the United States, this AD requires initial and repetitive visual 
inspections of the LP shaft signal system for cable wear and 
refurbishment of the LP shaft signal system when the cable is found 
frayed, or at every engine shop visit, whichever occurs first. The 
actions would be required to be accomplished in accordance with the SB 
described previously.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not

[[Page 34579]]

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 98-ANE-15-AD.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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:

98-13-21  Rolls-Royce Limited, Aero Division-Bristol, S.N.E.C.M.A: 
Amendment 39-10612. Docket 98-ANE-15-AD.

    Applicability: Rolls-Royce Limited (R-R), Aero Division-Bristol, 
S.N.E.C.M.A. Olympus 593 Mk. 610-14-28 turbojet engines, installed 
on but not limited to British Aerospace/Aerospatiale Concorde series 
aircraft.

    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 (d) 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 prevent low pressure (LP) shaft signal system failure, which 
could result in an LP turbine overspeed, burst, uncontained engine 
failure, and damage to the aircraft in the event of a LP shaft 
failure, accomplish the following:
    (a) Perform initial and repetitive visual inspections of the LP 
shaft signal system rear cable for wear, and refurbish the LP shaft 
signal system, if necessary, in accordance with R-R Service Bulletin 
(SB) No. OL.593-76-9039-71, Revision 2, dated July 23, 1997, as 
follows:
    (1) Within 30 cycles in service after the effective date of this 
AD, perform the initial in-service inspection.
    (2) Thereafter, inspect at intervals not to exceed 800 hours 
time in service (TIS) since last inspection or refurbishment, 
whichever occurs first.
    (3) If rear cable wear is detected beyond the limits described 
in the SB, refurbish the LP shaft signal system.

    Note 2: Guidance on performing the initial in-service inspection 
can be found in the Maintenance Manual (76-21-01, 76-21-02), and 
guidance on performing a refurbishment of the LP shaft signal system 
can be found in the Overhaul Manual.

    (b) Refurbish the LP shaft signal system as follows:
    (1) Perform the initial refurbishment at the next engine shop 
visit after the effective date of this AD.
    (2) Thereafter, refurbish at intervals not to exceed each engine 
shop visit, or 200 hours TIS since last refurbishment, whichever 
occurs later.
    (c) For the purpose of this AD, an engine shop visit is defined 
as an engine entering the shop for work in accordance with the 
refurbishment or repair workscope. A maintenance related task would 
not be considered a shop visit.
    (d) 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 shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Engine Certification Office.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Engine Certification Office.

    (e) 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.
    (f) The actions required by this AD shall be performed in 
accordance with the following R-R SB:

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         Document No.            Pages   Revision           Date        
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OL.593-76-9039-71.............      1-5         2  July 23, 1997.       
    Total pages: 5.                                                     
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[[Page 34580]]

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, PO Box 3, Filton, 
Bristol BS12 7QE, England; telephone 01-17-979-1234, fax 01-17-979-
7575. 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.
    (g) This amendment becomes effective on July 10, 1998.

    Issued in Burlington, Massachusetts, on June 12, 1998.
Jay J. Pardee,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 98-16467 Filed 6-24-98; 8:45 am]
BILLING CODE 4910-13-U