[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: ``engineprop@faa.dot.gov''. 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:
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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
