[Federal Register Volume 62, Number 202 (Monday, October 20, 1997)]
[Rules and Regulations]
[Pages 54373-54374]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-27351]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-ANE-18-AD; Amendment 39-10161; AD 97-21-08]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CT58 Series
Turboshaft Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to General Electric Company CT58 series turboshaft engines,
that requires removal from service of certain stage 1 and 2 forward
cooling plates, and stage 2 aft cooling plates, and replacement with
serviceable parts. This amendment is prompted by reports of certain
cooling plates forged with contaminated alloy that could reduce the
lives of the parts. The actions specified by this AD are intended to
prevent cooling plate fracture, which could result in a contained
engine failure, and an inflight engine shutdown.
DATES: Effective December 19, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 19, 1997.
ADDRESSES: The service information referenced in this AD may be
obtained from General Electric Company (GE), 1000 Western Ave., Lynn,
MA 01909; telephone (781) 594-9894, fax (781) 594-1527. This
information may be examined at the Federal Aviation Administration
(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: Diane Cook, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7133, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to General Electric Company (GE)
Models CT58-110-1, -110-2, -140-1, -140-2, and T58-GE-3/-5/-8F/-10/-100
turboshaft engines was published in the Federal Register on June 9,
1997 (62 FR 31370). That action proposed to require removal from
service of certain stage 1 and 2 forward cooling plates, and stage 2
aft cooling plates, and replacement with serviceable parts.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public.
Since publication of the proposed rule, GE Aircraft Engines has
issued GE Aircraft Engines CT58 Service Bulletin (SB) No. 72-188 (CEB-
293), Revision 1, dated July 15, 1997. This final rule references this
current revision.
The FAA has determined that air safety and the public interest
require the adoption of the rule with the changes described previously.
[[Page 54374]]
There are approximately 400 engines of the affected design in the
worldwide fleet. The FAA estimates that 126 engines installed on
aircraft of U.S. registry will be affected by this AD, that it will not
take any additional work hours per engine to accomplish the required
actions at next part exposure. Required parts will cost approximately
$2,730 per engine. Based on these figures, the total cost impact of the
AD on U.S. operators is estimated to be $343,980. The manufacturer,
however, has advised the FAA of a program to prorate the cost of
required parts downward by a factor equal to the quotient of the
difference between the original life limit of 4,000 hours time in
service and the total cycles of life consumed at time of removal,
divided by the original life limit. Therefore, the actual cost to
operators may be less than the FAA's estimate.
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.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the rules docket. A copy of it 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:
97-21-08 General Electric Company: Amendment 39-10161. Docket 97-
ANE-18-AD.
Applicability: General Electric Company (GE) Models CT58-110-1,
-110-2, -140-1, and -140-2, and T58-GE-3/-5/-8F/-10/-100 series
turboshaft engines, with stage 1 forward cooling plate, Part Number
(P/N) 37C300055P101, stage 2 forward cooling plate, P/N 3000T88P02,
and stage 2 aft cooling plate, P/N 3002T27P01, installed. These
engines are installed on but not limited to Boeing Vertol 107
series, and Sikorsky S61 and S62 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 cooling plate fracture, which could result in a
contained engine failure and an inflight engine shutdown, accomplish
the following:
(a) Remove from service affected cooling plates, listed by
serial number in GE Aircraft Engines CT58 Service Bulletin (SB) No.
72-188 (CEB-293), Revision 1, dated July 15, 1997, and replace with
serviceable parts, at the next part exposure, or next light
overhaul, whichever occurs first, but not to exceed 1,000 hours time
in service (TIS) for engines installed on aircraft that have engaged
in Repetitive Heavy Lift (RHL) operations, or 2,000 hours TIS for
engines installed on aircraft that have never engaged in RHL
operations, in accordance with that SB.
(b) For the purpose of this AD, the following definitions apply:
(1) RHL operation is defined as performing more than 10 lift-
carry-drop cycles per hour TIS without landing, or more than 10
takeoffs and landings per hour TIS.
(2) Light overhaul is defined as scheduled engine maintenance
that allows the engine to continue in service until scheduled major
overhaul time is reached.
(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. The
request shall be forwarded 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 requirements of this AD can be accomplished.
(e) The actions required by this AD shall be done in accordance
with the following GE Aircraft Engines SB:
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Document No Pages Revision Date
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72-188 (CEB-293)............... 1-7 1 July 15, 1997
Total Pages: 7.
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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 General Electric Company (GE),
1000 Western Ave., Lynn, MA 01909; telephone (781) 594-9894, fax
(781) 594-1527. 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.
(f) This amendment becomes effective on December 19, 1997.
Issued in Burlington, Massachusetts, on October 8, 1997.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 97-27351 Filed 10-17-97; 8:45 am]
BILLING CODE 4910-13-U
