[Federal Register: February 23, 2004 (Volume 69, Number 35)]
[Rules and Regulations]
[Page 8103-8105]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23fe04-5]
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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:
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.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
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 GEAE.csc@ae.ge.com.
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:
Locating suspect fuel flow divider assemblies,
P/Ns 4050T82G02 and 4067T04G02, and
Locating affected temperature control
assemblies, P/N 5040T77G02 and 5040T87G02, by SN, and
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 GEAE.csc@ae.ge.com. 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