[Federal Register Volume 63, Number 122 (Thursday, June 25, 1998)]
[Rules and Regulations]
[Pages 34567-34569]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-16270]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-12-AD; Amendment 39-10609; AD 98-13-20]
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 
a radiological inspection of the combustion chamber No. 2 outer cooling 
ring scoop circumferential and axial weld for weld quality, and reweld 
and reinspection, if necessary; and an inspection of the combustion 
chamber No. 2 inner and outer cooling ring web length, marking 
acceptable components with the letter ``T'' adjacent to the part 
number, and replacement of unacceptable components with serviceable 
parts. This amendment is prompted by reports of circumferential cracks 
at the No. 2 outer and inner rings of the combustor chamber, resulting 
in a section of the combustion chamber detaching and causing 
significant ignitor and low pressure turbine damage. The actions 
specified in this AD are intended to prevent combustion chamber 
detachment, which could result in an inflight engine shutdown or an 
engine fire.

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-12-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#6e57430f0a43640b000907000b1e1c011e2e080f0f400a011a40090118">9-ad-
<span class="__cf_email__" data-cfemail="076269606e696277756877476166662963687329606871">[email protected]</span></a>''. Comments sent via the Internet must contain 
the docket number in the subject line.

[[Page 34568]]

    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 circumferential cracks 
at the No. 2 outer and inner rings of the combustor chamber, resulting 
in a section of the combustion chamber detaching and causing 
significant ignitor and low pressure turbine damage. The investigation 
revealed that the length of the web is under minimum drawing dimension, 
resulting in inadequate weld penetration, causing cracks to initiate 
and propagate along the weld joint. 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 US or aircraft that are currently operated in the 
U.S. 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. This condition, 
if not corrected, could result in combustion chamber detachment, which 
could result in an inflight engine shutdown or an engine fire.
    R-R has issued Service Bulletin (SB) No. OL.593-72-9038-417, dated 
June 26, 1996, that specifies procedures for a radiological inspection 
of the combustion chamber No. 2 outer cooling ring scoop 
circumferential and axial weld for weld quality, and reweld and 
reinspection, if necessary; and SB No. OL.593-72-9048-424, dated April 
25, 1997, that specifies procedures for an inspection of the combustion 
chamber No. 2 inner and outer cooling ring web length, marking 
acceptable components with the letter ``T'' adjacent to the part 
number, and replacement of unacceptable components with serviceable 
parts. The CAA classified these SBs as mandatory and issued ADs 008-06-
96 and 004-04-97 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, at the next combustor exposure 
after the effective date of this AD, a radiological inspection of the 
combustion chamber No. 2 outer cooling ring scoop circumferential and 
axial weld for weld quality, and reweld and reinspection, if necessary; 
and an inspection of the combustion chamber No. 2 inner and outer 
cooling ring web length, marking acceptable components with the letter 
``T'' adjacent to the part number, and replacement of unacceptable 
components with serviceable parts. The actions would be required to be 
accomplished in accordance with the SBs 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 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-12-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.

[[Page 34569]]

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:

98-13-20  Rolls-Royce Limited, Aero Division-Bristol, N.E.C.M.A.: 
Amendment 39-10609. Docket 98-ANE-12-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 (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 prevent combustion chamber detachment, which could result in 
an inflight engine shutdown or an engine fire, accomplish the 
following:
    (a) At the next combustor exposure after the effective date of 
this AD, accomplish the following in accordance with the 
Accomplishment Instructions of R-R Service Bulletin (SB) No. OL.593-
72-9038-417, dated June 26, 1996:
    (1) Perform a radiological inspection of the combustion chamber 
No. 2 outer cooling ring scoop circumferential and axial weld for 
weld quality.
    (2) If the weld quality does not meet the standards described in 
the SB, reweld and then perform an additional radiological 
inspection for weld quality prior to return to service.
    (b) At the next combustor exposure after the effective date of 
this AD, accomplish the following in accordance with the 
Accomplishment Instructions of R-R SB No. OL.593-72-9048-424, dated 
April 25, 1997:
    (1) Perform an inspection of the combustion chamber No. 2 inner 
and outer cooling ring for web length.
    (2) If the web length is acceptable within the limits described 
in the SB, mark the letter ``T'' adjacent to the part number.
    (3) If the web length is not acceptable within the limits 
described in the SB, remove the combustion chamber from service and 
replace affected components with serviceable parts prior to return 
to service.
    (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 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 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Engine Certification Office.

    (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 aircraft to a location where 
the inspection requirements of this AD can be accomplished.
    (e) The actions required by this AD shall be performed in 
accordance with the following R-R SBs:

------------------------------------------------------------------------
           Document No.              Pages               Date           
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OL.593-72-9038-417................      1-3  June 26, 1996.             
Total pages: 3.                                                         
OL.593-72-9048-424................      1-4  April 25, 1997.            
Total pages: 4.                                                         
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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, 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.
    (f) This amendment becomes effective on July 10, 1998.

    Issued in Burlington, Massachusetts, on June 11, 1998.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 98-16270 Filed 6-24-98; 8:45 am]
BILLING CODE 4910-13-U


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