[Federal Register Volume 66, Number 116 (Friday, June 15, 2001)]
[Rules and Regulations]
[Pages 32535-32537]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-14823]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-07-AD; Amendment 39-12262; AD 2001-12-07]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CT58 Series 
and Former Military T58 Series Turboshaft 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

[[Page 32536]]

applicable to certain General Electric Company (GE) CT58 series and 
former military T58 series turboshaft engines. This action requires the 
removal from service of certain fuel flow divider assemblies, and 
replacement with serviceable parts. This amendment is prompted by 
reports of large volumes of fuel leakage from end caps on fuel flow 
divider assemblies. The actions specified in this AD are intended to 
prevent fuel flow divider assembly fuel leakage, which could cause an 
engine fire, leading to an in-flight engine shutdown and forced 
landing.

DATES: Effective July 2, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before August 14, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2001-NE-07-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be sent 
via the Internet using the following address:``[email protected]''.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; Attention: 
CT58/T58 International Program Manager, Mail Zone: 564X9; fax: (781) 
594-1527, Internet address: ``[email protected]''. 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: Eugene Triozzi, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299 telephone: (781) 
238-7148; fax: (781) 238-7199.

SUPPLEMENTARY INFORMATION: On December 7, 2000, the FAA was made aware 
of three incidents of fuel leaking from the temperature control valve 
assembly, located on the fuel flow divider assembly. An investigation 
by GE revealed that the vendor of the temperature control valve 
assembly end caps did not accomplish the required manufacturing process 
steps following heat treatment. This has caused the end caps to be 
susceptible to intergranular corrosion which can result in cracking. 
This condition, if not corrected, could cause an engine fire, leading 
to an in-flight engine shutdown and forced landing.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of GE 
Company Alert Service Bulletin (ASB) CT58 73-A0080, dated February 13, 
2001, that describes procedures for locating suspect fuel flow divider 
assemblies, part numbers (P/N's) 4050T82G02 or 4067T04G02, then 
locating temperature control assemblies P/N's 5040T77G02 or 5040T87G02 
by affected serial number prefix, and then replacing fuel flow divider 
assemblies with serviceable parts.

FAA's Determination of an Unsafe Condition and Proposed Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other GE CT58 series turboshaft engines of the same 
type design, this AD is being issued to prevent fuel flow divider 
assembly fuel leakage, which could cause an engine fire, leading to an 
in-flight engine shutdown and forced landing. This AD requires locating 
suspect fuel flow divider assemblies by part number, then locating 
affected temperature control assemblies by part number and serial 
number prefix, and then replacing fuel flow divider assemblies with 
serviceable parts.

Immediate Adoption of This AD

    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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NE-07-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it would not have a substantial 
direct effect 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    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, 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:

[[Page 32537]]

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:

2001-12-07  General Electric Company: Amendment 39-12262. Docket No. 
2001-NE-07-AD.

Applicability

    This airworthiness directive (AD) is applicable to General 
Electric Company (GE) CT58-140-1, -140-2, and former military T58-
GE-5, -8F, -10, -100, and -402 turboshaft engines, with fuel flow 
divider assemblies part numbers (P/N's) 4050T82G02, or 5040T77G02 
having temperature control assemblies with serial numbers (SN's) 
with the first two digits of 95, 96, 97, 98, or 99 installed. These 
engines are installed on, but not limited to Agusta S.p.A. AS-6N, 
Boeing Vertol 107-11, Sikorsky S-61 Series and S-62 Series, and the 
following surplus military helicopters that have been certified in 
accordance with sections 21.25 or 21.27 of the Federal Aviation 
Regulations (14 CFR 21.25 or 21.27): Carson S-61L, Firefly UH-1F, 
Glacier CH-3E, Quentin HH52A, Robinson Air Crane CH-3C, CH-3E, HH-
3C, and HH-3E, Sikorsky S-61A, S-61D, S-61E, S-61V, and S-61V-1, and 
Siller Helicopters CH-3A, and SH-3A.

    Note 1: This 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 
done.
    To prevent fuel flow divider assembly fuel leakage, which could 
cause an engine fire, leading to an in-flight engine shutdown and 
forced landing, do the following within 120 hours time-in-service 
after the effective date of this AD:
    (a) Locate the temperature control assembly, which is mounted on 
the fuel flow divider assembly and do the following:
    (1) Read the temperature control assembly SN, located on the 
temperature control assembly end cap. The end cap can be identified 
by a one-inch hex flange and by being threaded into the fuel flow 
divider body.
    (2) If the first two digits of the SN are 95, 96, 97, 98, or 99, 
or if the SN cannot be determined, replace the entire fuel flow 
divider assembly. Further information regarding SN location on the 
temperature control assembly may be found in GE Alert Service 
Bulletin CT58 73-A0080, dated February 13, 2001.
    (b) After the effective date of this AD, do not install any fuel 
flow divider assembly P/N 4050T82G02 or 5040T77G02, that has the 
first two digits of the temperature control assembly SN of 95, 96, 
97, 98, or 99.

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. 
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.

Special Flight Permits

    (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.

Effective Date of this AD

    (e) This amendment becomes effective on July 2, 2001.

    Issued in Burlington, Massachusetts, on June 5, 2001.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 01-14823 Filed 6-14-01; 8:45 am]
BILLING CODE 4910-13-P