[Federal Register Volume 62, Number 235 (Monday, December 8, 1997)]
[Rules and Regulations]
[Pages 64513-64514]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-31862]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-ANE-21-AD; Amendment 39-10232; AD 97-25-08]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CJ610 Series
Turbojet and CF700 Series Turbofan 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 General Electric Company (GE) CJ610 series turbojet
and CF700 series turbofan engines. This action requires removal from
service of possibly defective turbine torque rings and compressor drive
shafts which may have been manufactured from contaminated material; and
replacement with serviceable parts. This amendment is prompted by a
report of a cooling plate removed from a GE CT58 series engine that was
found to have an iron-rich inclusion that came from a contaminated heat
lot. Parts on GE CJ610 series and CF700 series engines which were
manufactured from the same and similar heat lots may also be
contaminated. The actions specified in this AD are intended to prevent
turbine torque ring or compressor drive shaft failure due to a
manufacturing defect, which could result in an uncontained engine
failure.
DATES: Effective January 2, 1998. The incorporation by reference of
certain publications listed in the regulations is approved by the
Director of the Federal Register as of January 2, 1998.
Comments for inclusion in the Rules Docket must be received on or
before February 6, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 97-ANE-21-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.
The service information referenced in this AD may be obtained from
GE Aircraft Engines, 1000 Western Ave., Lynn, MA 01910; telephone (781)
594-3140, fax (781) 594-4805. This information may be examined at the
FAA, New England Region, Office of the Assistant Chief 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: Barbara Caufield, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7146, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The Federal Aviation Administration received
a report that certain turbine torque rings and compressor drive shafts
installed on General Electric Company (GE) CJ610 series turbojet and
CF700 series turbofan engines were forged with a contaminated alloy
that could reduce the life of the part. The FAA has determined that
certain heat lots of A286 material were produced with iron-rich
inclusions during the vendor's normal Vacuum Induction Melt (VIM)
process. The manufacturer discovered a cooling plate removed from a GE
CT58 series turboprop engine had been manufactured from this heat lot
and was found with an inclusion. This heat lot was also used to
manufacture turbine torque rings and compressor drive shafts on GE
CJ610 series turbojet and CF700 series turbofan engines. This
condition, if not corrected, could result in turbine torque ring or
compressor drive shaft failure due to a manufacturing defect, which
could result in an uncontained engine failure.
The FAA has reviewed and approved the technical contents of GE
CF700 Service Bulletin (SB) No. A72-155, dated May 22, 1997, and GE
CJ610 SB No. A72-147, dated May 22, 1997, that describes procedures for
removing affected turbine torque rings and compressor drive shafts from
service, and replacing with serviceable parts.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of the same type design, this AD is
being issued to prevent an uncontained engine failure and damage to the
aircraft. This AD requires removing affected turbine torque rings and
compressor drive shafts from service, and replacing with serviceable
parts. The actions are 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
[[Page 64514]]
Docket Number 97-ANE-21-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:
97-25-08 General Electric Company: Amendment 39-10232. Docket 97-
ANE-21-AD.
Applicability: General Electric Company (GE) CJ610 series
turbojet and CF700 series turbofan engines, with turbine torque
rings and compressor drive shafts identified in GE CF700 Service
Bulletin (SB) No. A72-155, dated May 22, 1997, and GE CJ610 SB No.
A72-147, dated May 22, 1997. These engines are installed on but not
limited to the following aircraft: Learjet 20 series, Israel
Aircraft Industries Westwind series, Hansa Jet, Aero Commander Jet
Commander, Dassault Falcon 20 series, Sabreliner 265 series.
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 turbine torque ring or compressor drive shaft failure
due to a manufacturing defect, which could result in an uncontained
engine failure, accomplish the following:
(a) For GE CF700 series turbofan engines, accomplish the
following in accordance with GE CF700 SB No. A72-155, dated May 22,
1997:
(1) Remove from service affected turbine torque rings, listed by
serial number (S/N) in paragraph 1. A.(3a) of GE CF700 SB No. A72-
155, dated May 22, 1997, and replace with serviceable parts, within
50 hours time in service (TIS), or 60 days after the effective date
of this AD, whichever occurs first.
(2) Remove from service affected turbine torque rings and
compressor drive shafts, listed by S/N in GE paragraph 1.A.(3b) of
GE CF700 SB No. A72-155, dated May 22, 1997, and replace with
serviceable parts, within 300 hours TIS, or 12 months after the
effective date of this AD, whichever occurs first.
(b) For GE CJ610 series turbojet engines, accomplish the
following in accordance with GE CJ610 SB No. A72-147, dated May 22,
1997:
(1) Remove from service affected turbine torque rings, listed by
S/N in paragraph 1.A.(3a) of GE CJ610 SB No. A72-147, dated May 22,
1997, and replace with serviceable parts, within 50 hours TIS, or 60
days after the effective date of this AD, whichever occurs first.
(2) Remove from service affected turbine torque rings and
compressor drive shafts, listed by S/N in paragraph 1.A.(3b) of GE
CJ610 SB No. A72-147, dated May 22, 1997, and replace with
serviceable parts, within 300 hours TIS, or 12 months after the
effective date of this AD, whichever occurs first.
(c) After the effective date of this AD, installation of
uninstalled affected parts identified by S/N in the SBs referenced
in paragraphs (a) and (b) of this AD is prohibited.
(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 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.
(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 done in accordance
with the following GE service documents:
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Document No. Pages Date
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CF700 SB No. A72-155.................... 1-9 May 22, 1997.
Total Pages: 9........................
CJ610 SB No. A72-147.................... 1-9 May 22, 1997.
Total Pages: 9........................
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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 GE Aircraft Engines, 1000 Western Ave.,
Lynn, MA 01910; telephone (781) 594-3140, fax (781) 594-4805. Copies
may be inspected at the FAA, New England Region, Office of the
Assistant Chief 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 January 2, 1998.
Issued in Burlington, Massachusetts, on November 26, 1997.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 97-31862 Filed 12-5-97; 8:45 am]
BILLING CODE 4910-13-U
