AD 2001-18-06

[Federal Register Volume 66, Number 178 (Thursday, September 13, 2001)]
[Rules and Regulations]
[Pages 47575-47576]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-22312]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-13-AD; Amendment 39-12432; AD 2001-18-06]
RIN 2120-AA64


Airworthiness Directives; General Electric Company T58 and CT58 
Series Turboshaft Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment surpersedes two existing airworthiness 
directives (AD's), applicable to General Electric Company (GE) T58 and 
CT58 series turboshaft engines. The current AD's revised the counting 
method for hours in repetitive heavy-lift (RHL) service and reduced the 
life limit for rotating components. Life-limited rotating components 
must be removed from service in accordance with the multiplying factors 
and retirement lives contained in General Electric Alert Service 
Bulletin (ASB) CT58 A72-162 (CEB-258), dated July 9, 1979. This 
amendment requires applying an additional multiplying factor to life-
limited rotating parts when the engine is used in heavy lifting 
operations. This amendment is prompted by a review of the current AD's, 
AD-69-23-02 and AD-79-23-04, and a determination that the requirements 
of those AD's may conflict. This amendment will prevent RHL and utility 
service multiplier factors from being applied incorrectly. The actions 
specified in this AD are intended to prevent low-cycle fatigue failure 
of rotating parts that could result in uncontained engine failure and 
damage to the rotorcraft.

DATES: Effective October 18, 2001. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of October 18, 2001.

ADDRESSES: The service information referenced in this AD may be 
obtained from from GE Aircraft Engines, General Electric Company, 1000 
Western Avenue, Lynn, MA 01910. This information may be examined at the 
FAA, New England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Kevin Donovan, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7743, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 69-23-02, 
Amendment 39-1086 (34 FR 18296, November 15, 1969); and AD 79-23-04, 
Amendment 39-3610 (44 FR 72103, December 13, 1979) that are applicable 
to General Electric Company CT58 turboshaft engines was published in 
the Federal Register on April 3, 2000 (64 FR 17471). That action 
proposed to require that the life limits of certain life-limited 
rotating parts be revised based on multiplying factors specified in 
GEAE Alert Service Bulletin (ASB) (CT58) 72-162 CEB 258, dated July 9, 
1979, for RHL operations.

Comments

    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. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.

Differences Between the NPRM and the Amendment

    Since the publication of the NPRM, the FAA has been informed that 
there are restricted category aircraft involved in RHL operations. As a 
result, the T58 models have been added to the Applicability of this 
amendment.

Economic Impact

    There are approximately 380 engines of the affected design in the 
worldwide fleet. The FAA estimates that 130 engines installed on 
aircraft of U.S. registry would be affected by this proposed AD, that 
it would take approximately 0.25 work hour per engine to accomplish the 
proposed calculations, and that the average labor rate is $60 per work 
hour. Based on these figures, the total cost impact of the proposed AD 
on U.S. operators is estimated to be $1,950.

Regulatory Impact

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it does not have a substantial direct 
effect on

[[Page 47576]]

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. Accordingly, the FAA has not consulted 
with state authorities prior to publication of this rule.
    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 removing Amendment 39-1086 (34 FR 
18296, October 15, 1970) and Amendment 39-3610 (44 FR 72103, December 
13, 1979), and by adding a new airworthiness directive (AD) to read as 
follows:

AD 2001-18-06  GE Aircraft Engines: Amendment 39-12432. Docket No. 
99-NE-13-AD. Supersedes AD 69-23-02, Amendment 39-1086 and AD 79-23-
04, Amendment 39-3610.

    Applicability: GE Aircraft Engines T58 and CT58 series 
turboshaft engine installed on, but not limited to Boeing--Vertol V-
107 series, Kaman H-2, Bell UH-1F series; and Sikorsky CH/HH-3 
series, S-61 A/H-3/CH124/CH-3/HH-3L/N/R series, and S-62 series 
rotorcraft.

    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

    Compliance with this AD is required as indicated, unless already 
accomplished.
    To prevent low-cycle fatigue failure of rotating parts that 
could result in uncontained engine failure and damage to the 
rotorcraft, accomplish the following:

Calculating New Life Limits for Rotating Parts

    (a) Within 50 hours time-in-service after the effective date of 
this AD, calculate the new cycles-since-new for life-limited 
rotating parts in accordance with the Accomplishment Instructions, 
2.A. through 2.G. of GEAE Service Bulletin (CT58) 72-162 CEB-258, 
revision 9, dated October 6, 1998.
    (b) Remove any part from service that exceeds the new calculated 
life limit and replace it with a serviceable part.

Alternative Methods of Compliance

    (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 (ECO). 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the ECO.

    (d) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the rotorcraft to a location where the 
requirements of this AD can be accomplished.

Documents That Have Been Incorporated By Reference

    (e) The calculation shall be done in accordance with the 
Accomplishment Instructions, 2.A. through 2.G. of GEAE Service 
Bulletin (CT58) 72-162 CEB-258, revision 9, dated October 6, 1998 as 
follows:

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             Document No.                        Pages                  Revision                   Date
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(CT58) 72-162 CEB-258.................  1-4....................  9.....................  October 6, 1998.
(CT58) 72-162 CEB-258.................  5......................  5.....................  May 12, 1994.
(CT58) 72-162 CEB-258.................  6......................  7.....................  April 25, 1997.
(CT58) 72-162 CEB-258.................  7-8....................  5.....................  May 12, 1994.
(CT58) 72-162 CEB-258.................  9-11...................  7.....................  April 25, 1997.
(CT58) 72-162 CEB-258.................  12-16..................  5.....................  May 12, 1994.
(CT58) 72-162 CEB-258.................  17.....................  7.....................  April 25, 1997.
(CT58) 72-162 CEB-258.................  18.....................  9.....................  October 6, 1998.
(CT58) 72-162 CEB-258.................  19-20..................  5.....................  May 12, 1994.
(CT58) 72-162 CEB-258.................  21.....................  8.....................  June 16, 1997.
(CT58) 72-162 CEB-258.................  22-24..................  5.....................  May 12, 1994.
(CT58) 72-162 CEB-258.................  25-26..................  9.....................  October 6, 1998.
(CT58) 72-162 CEB-258.................  27.....................  5.....................  May 12, 1994.
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 Total pages: 27.

    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, General 
Electric Company, 1000 Western Avenue, Lynn, MA 01910. 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 October 18, 2001.

    Issued in Burlington, Massachusetts, on August 24, 2001.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 01-22312 Filed 9-12-01; 8:45 am]
BILLING CODE 4910-13-U