[Federal Register: October 3, 2003 (Volume 68, Number 192)]
[Rules and Regulations]
[Page 57346-57347]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03oc03-8]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NE-27-AD; Amendment 39-13325; AD 2003-20-07]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF6-
80E1A2 Turbofan 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
General Electric Company (GE) CF6-80E1A2 turbofan engines with forward
engine mount platforms part numbers (P/Ns) 1520M53G04 and 1846M24G15
installed. This AD requires initial and repetitive fluorescent
penetrant inspections of cast material forward engine mount platforms.
This AD is prompted by the airframe manufacturer's revised analyses of
loads on the forward engine mount. We are issuing this AD to prevent
engine separation that could result from cracking of the forward engine
mount platform.
DATES: Effective November 3, 2003.
We must receive any comments on this AD by December 2, 2003.
ADDRESSES: Use one of the following addresses to submit comments on
this AD:
[sbull] By mail: The Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2003-NE-27-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
[sbull] By fax: (781) 238-7055. [sbull] By e-mail: 9-ane-adcomment@faa.gov.
You can get the service information referenced in this AD from
General Electric Company via Lockheed Martin Technology Services, 10525
Chester Road, suite C, Cincinnati, Ohio 45215, telephone (513) 672-
8400; fax (513) 672-8422.
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.
FOR FURTHER INFORMATION CONTACT: Karen Curtis, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7192; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: GE has notified the FAA that an unsafe
condition may exist on GE CF6-80E1A2 turbofan engines. GE advises that
Airbus Industrie has revised their analyses of Airbus A330 airplane
engine mount loads. The revised analyses predict a reduction in
calculated low-cycle-fatigue (LCF) life capability for forward mount
platforms made from cast material. Airbus Industrie has updated the
airplane maintenance manual with revised inspection thresholds and
intervals for the affected engine mount components. These revised
inspection thresholds and intervals are published in Chapter 5 of the
engine manual. This AD is necessary to make those inspection thresholds
and intervals mandatory for all operators.
FAA's Determination and Requirements of This AD
Although no airplanes that are registered in the United States use
these GE CF6-80E1A2 turbofan engines, the possibility exists that the
engines could be used on airplanes that are registered in the United
States in the future. The unsafe condition described previously is
likely to exist or develop on other GE CF6-80E1A2 turbofan engines of
the same type design. We are issuing this AD to prevent engine
separation that could result from cracking of the forward engine mount
platform. This AD requires initial and repetitive fluorescent penetrant
inspections of cast material forward engine mount platforms, P/Ns
1520M53G04 and 1846M24G15. The thresholds and intervals were
established to be consistent with inspections required by the airframe
manufacturer.
FAA's Determination of the Effective Date
Sine there are currently no domestic operators of GE CF6-80E1A2
turbofan engines, notice and opportunity for public comment before
issuing this AD are unnecessary. Therefore, a situation exists that
allows the immediate adoption of this regulation.
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
47997, 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-27-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 may 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
[[Page 57347]]
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-27-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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:
2003-20-07 General Electric Company: Amendment 39-13325. Docket No.
2003-NE-27-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November
3, 2003.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-80E1A2
turbofan engines with forward engine mount platforms part numbers
(P/Ns) 1520M53G04 and 1846M24G15 installed. These engines are
installed on, but not limited to Airbus Industrie A330 airplanes.
Unsafe Condition
(d) This AD is prompted by revised analyses of forward engine
mount loads by the airframe manufacturer. We are issuing this AD to
prevent engine separation that could result from cracking of the
forward engine mount platform.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Platforms Previously Inspected
(f) For platforms that were inspected using a fluorescent
penetrant inspection (FPI) before the effective date of this AD,
repeat the FPI within 4,000 cycles-in-service-since last inspection
(CSLI).
Platforms Not Previously Inspected
(g) For platforms that were not inspected using an FPI before
the effective date of this AD, inspect the platform using an FPI at
the next exposure, or before exceeding 6,360 cycles-since-new (CSN),
whichever occurs first.
Platform Repetitive Inspections
(h) Repeat the FPI within every 4,000 CSLI.
Alternative Methods of Compliance
(i) 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
(j) None.
Related Information
(k) GE Aircraft Engines Alert Service Bulletin No. CF6-80E1 S/B
72-A0195 pertains to the subject of this AD. Information on
performing FPI can be found in the CF6 component maintenance manual,
GEK 99410, section 71-21-02.
Issued in Burlington, Massachusetts, on September 25, 2003.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 03-25000 Filed 10-2-03; 8:45 am]
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