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

[Federal Register Volume 69, Number 35 (Monday, February 23, 2004)]
[Rules and Regulations]
[Pages 8103-8105]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-3680]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-66-AD; Amendment 39-13487; AD 2004-04-06]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain General Electric Company (GE) CT58-100-2, CT58-140-1, -140-2, 
and T58-GE-1, -3, -5, -8E, -8F, -10, -100, and -402 turboshaft engines. 
This AD requires the removal from service of certain fuel flow divider 
assemblies. This AD results from a report that a certain population of 
flow divider end caps could crack and cause large volumes of fuel 
leakage. We are issuing this AD to prevent fuel leakage from the fuel 
flow divider assembly, which could cause an engine fire, leading to an 
in-flight engine shutdown and forced landing.

DATES: This AD becomes effective March 9, 2004. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of March 9, 2004.
    We must receive any comments on this AD by April 23, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
    <bullet<ls-thn-eq> By mail: The Federal Aviation Administration 
(FAA), New England Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 2003-NE-66-AD, 12 New England Executive Park, 
Burlington, MA 01803-5299.
    <bullet<ls-thn-eq> By fax: (781) 238-7055.
    <bullet<ls-thn-eq> By e-mail: [email protected].
    You can get the service information referenced in this AD from GE 
Aircraft Engines Customer Support Center, M/D 285, 1 Neumann Way, 
Evendale, OH 45215, telephone (513) 552-3272; fax (513) 552-3329, e-
mail [email protected].
    You may examine the AD docket, by appointment, at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA. You may examine the service 
information, by appointment, 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: Mark Bouyer, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park; telephone (781) 238-7755; fax (781) 238-
7199.

SUPPLEMENTARY INFORMATION: On July 25, 2003, we were made aware that 
182 temperature control valve assemblies, located on the fuel flow 
divider assembly, are susceptible to cracking and leaking of fuel. GE 
has identified the affected temperature control valve assemblies by 
serial number (SN). An investigation by GE revealed that the end caps 
for the temperature control valve assemblies may be susceptible to 
intergranular corrosion, which can result in cracking. Even though 
there have been no reports of these end caps cracking, the FAA has 
determined that this condition represents an unsafe condition. Since 
the affected engines could accumulate as many as 120 hours time-in-
service every two weeks, we have determined that notice and opportunity 
for prior public comment is impracticable, and that this AD must be 
issued as a final rule; request for comments. This condition, if not 
corrected, could cause an engine fire, leading to an in-flight engine 
shutdown and forced landing.

Relevant Service Information

    We have reviewed and approved the technical contents of GE Alert 
Service Bulletin (ASB) CT58 S/B 73-A0081,

[[Page 8104]]

Revision 2, dated August 7, 2003, that lists the affected SNs of 
temperature control assemblies, part numbers (P/Ns) 5040T77G02 or 
5040T87G02.

FAA's Determination and Requirements of this AD

    The unsafe condition described previously is likely to exist or 
develop on other GE CT58 series turboshaft engines of the same type 
design. We are issuing this AD to prevent fuel leakage from the fuel 
flow divider assembly, which could cause an engine fire, leading to an 
in-flight engine shutdown and forced landing. This AD requires within 
120 hours time-in-service:
    <bullet<ls-thn-eq> Locating suspect fuel flow divider assemblies, 
P/Ns 4050T82G02 and 4067T04G02, and
    <bullet<ls-thn-eq> Locating affected temperature control 
assemblies, P/N 5040T77G02 and 5040T87G02, by SN, and
    <bullet<ls-thn-eq> Removing affected fuel flow divider assemblies 
from service.
    You must use the service information described previously by this 
AD to identify the affected temperature control assemblies by SN.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are impracticable, and that good 
cause exists for making this amendment effective in less than 30 days.

Changes to 14 CFR Part 39--Effect on the AD

    On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 
47998, July 22, 2002), which governs our AD system. This regulation now 
includes material that relates to special flight permits, alternative 
methods of compliance, and altered products. This material previously 
was included in each individual AD. Since this material is included in 
14 CFR part 39, we will not include it in future AD actions.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2003-NE-66-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the rule 
that might suggest a need to modify it. If a person contacts us 
verbally, and that contact relates to a substantive part of this AD, we 
will summarize the contact and place the summary in the docket. We will 
consider all comments received by the closing date and may amend the AD 
in light of those comments.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications with you. You can get more information about plain 
language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the AD Docket

    You may examine the AD Docket (including any comments and service 
information), by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. See ADDRESSES for the 
location.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will 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.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2003-NE-66-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under 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

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2004-04-06 General Electric Company: Amendment 39-13487. Docket No. 
2003-NE-66-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 9, 
2004.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CT58-100-2, 
CT58-140-1, -140-2, and T58-GE-1, -3, -5, -8E, -8F, -10, -100, and -
402 turboshaft engines, with fuel flow divider assemblies part 
number (P/N) 4050T82G02 or 4067T04G02, having temperature control 
assemblies, P/N 5040T77G02 or 5040T87G02, with serial numbers (SNs) 
listed in 1.A.(3) of GE Alert Service Bulletin (ASB) No. CT58 S/B 
73-A0081, Revision 2, dated August 7, 2003, installed. These engines 
are installed on, but not limited to, Agusta S.p.A. AS-61N, AS-61N1, 
Boeing Vertol 107-II, and Sikorsky S-61L, S-61N, S-61R, S-61NM, S-
62A helicopters, and the following surplus military helicopters that 
have been certified in accordance with Sec.  21.25 or 21.27 of the 
Federal Aviation Regulations (14 CFR 21.25 or 21.27): CA Department 
of Forestry UH-1F, Carson S-61L, Firefly UH-1F, Garlick Helicopters 
UH-1F, UH-1P, and TH-1F, Glacier CH-3E, Robinson Air Crane CH-3C, 
CH-3E, HH-3C, HH-3E, UH-1F, UH-1P, and TH-1F, Sikorsky S-61A, S-61D, 
and S-61V, Tamarack UH-1F, and Siller Helicopters CH-3A, and SH-3A 
helicopters.

Unsafe Condition

    (d) This AD results from a report that a certain population of 
flow divider end caps could crack and cause large volumes of fuel 
leakage. We are issuing this AD to prevent fuel leakage from the 
fuel flow divider assembly, which could cause an engine fire, 
leading to an in-flight engine shutdown and forced landing.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within 120 hours time-in-service after the effective 
date of this AD:

[[Page 8105]]

Required Actions

    (f) Locate the temperature control assembly, which is mounted on 
the fuel flow divider assembly and do the following:
    (1) Read the SN of the temperature control assembly. The SN is 
located on the end cap of the temperature control assembly. The end 
cap has a one-inch hex flange and is threaded into the fuel flow 
divider body.
    (2) If the SN is listed in 1.A.(3) of GE ASB No. CT58 S/B 73-
A0081, Revision 2, dated August 7, 2003, or if the SN cannot be 
determined, remove the fuel flow divider assembly from service.
    (g) After the effective date of this AD, do not install any fuel 
flow divider assembly P/N 4050T82G02 or 4067T04G02, that has a 
temperature control assembly with a SN listed in 1.A.(3) of GE ASB 
No. CT58 S/B 73-A0081, Revision 2, dated August 7, 2003.

Alternative Methods of Compliance

    (h) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (i) You must use GE ASB No. CT58 S/B 73-A0081, Revision 2, dated 
August 7, 2003 to identify by SN the affected temperature control 
assemblies. The Director of the Federal Register approved the 
incorporation by reference of this service bulletin in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy from GE 
Aircraft Engines Customer Support Center, M/D 285, 1 Neumann Way, 
Evendale, OH 45215, telephone (513) 552-3272; fax (513) 552-3329, e-
mail [email protected]. You may review copies at the Federal 
Aviation Administration (FAA), New England Region, Office of the 
Regional Counsel, 12 New England Executive Park, Burlington, MA 
01803-5299, or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

Related Information

    (j) None.


    Issued in Burlington, Massachusetts, on February 13, 2004.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 04-3680 Filed 2-20-04; 8:45 am]
BILLING CODE 4910-13-P

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