[Federal Register Volume 69, Number 3 (Tuesday, January 6, 2004)]
[Rules and Regulations]
[Pages 494-495]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-144]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-26-AD; Amendment 39-13409; AD 2003-26-11]
RIN 2120-AA64


Airworthiness Directives; General Electric Company (GE) CF6-
80E1A2 and -80E1A4 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 and -80E1A4 turbofan engines 
with left vertical link bolts part number (P/N) 1304M26P02 installed, 
and pylon attachment bolts originally torqued to 450-500 lb ft. This AD 
requires reducing the torque of pylon attachment bolts, and replacing 
left vertical link bolts with life-limited serialized bolts. This AD 
results from revised analyses by the airframe manufacturer of loads on 
the forward engine mount. We are issuing this AD to prevent engine 
separation that could result from a reduction of engine mount 
structural integrity due to failure of pylon attachment bolts or 
vertical link bolts.

DATES: Effective February 5, 2004. The Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulations as of February 5, 2004.
    We must receive any comments on this AD by March 8, 2004.

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-26-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
    [sbull] By fax: (781) 238-7055.
    [sbull] By e-mail: [email protected].
    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. 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: 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.
    Airbus Industrie has revised their analyses of Airbus A330-200 and 
A330-300 airplane forward engine mount loads. The revised analyses 
predict higher loads than the loads used in the original certification 
of the engine. The increased loads, in combination with the originally 
specified pylon attachment bolt torque, result in a reduced low-cycle-
fatigue (LCF) life capability for the pylon attachment bolts. The 
increased load also results in a reduced LCF life capability for the 
left vertical link bolts. This AD requires reducing the torque of pylon 
attachment bolts, and replacing left vertical link bolts with life-
limited serialized bolts. These actions restore the forward engine 
mount structural integrity.

Relevant Service Information

    We have reviewed and approved the technical contents of GE Alert 
Service Bulletin No. CF6-80E1 S/B 72-A0184, Revision 1, dated February 
26, 2002, that describes procedures for reducing the torque on CF6-
80E1A2 and -80E1A4 turbofan engine pylon attachment bolts.

FAA's Determination and Requirements of This AD

    Although no airplanes that are registered in the United States use 
these GE CF6-80E1A2 and -80E1A4 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 and -
80E1A4 turbofan engines of the same type design. We are issuing this AD 
to prevent engine separation that could result from a reduction of 
engine mount structural integrity due to failure of pylon attachment 
bolts or vertical link bolts. This AD requires reducing the torque of 
pylon attachment bolts, and replacing left vertical link bolts with 
life-limited serialized bolts. You must use the service information 
described previously to perform the bolt torque reduction required by 
this AD.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of GE CF6-80E1A2 
and -80E1A4 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-26-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

[[Page 495]]

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 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-26-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:

2003-26-11 General Electric Company: Amendment 39-13409. Docket No. 
2003-NE-26-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
5, 2004.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-80E1A2 
and -80E1A4 turbofan engines with left vertical link bolts part 
number (P/N) 1304M26P02 installed, and pylon attachment bolts 
originally torqued to 450-500 lb ft. These engines are installed on, 
but not limited to Airbus Industrie A330-200 and A330-300 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 a reduction of 
engine mount structural integrity due to failure of pylon attachment 
bolts or vertical link bolts.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance cycles and times specified unless 
the actions have already been done.

Torque Reduction of Pylon Attachment Bolts

    (f) For CF6-80E1A2 engines, reduce the pylon attachment bolt 
torque on each of the five bolts to 400-450 lb ft, before exceeding 
7,160 cycles-since-new (CSN) or before exceeding 5,120 cycles-since-
last-installation (CSLI), whichever is later. Use paragraph 3. of 
Accomplishment Instructions of Alert Service Bulletin (ASB) No. CF6-
80E1 S/B 72-A0184, Revision 1, dated February 26, 2002, to reduce 
the torque.
    (g) For CF6-80E1A4 engines, reduce the pylon attachment bolt 
torque on each of the five bolts to 400-450 lb ft, before exceeding 
6,520 CSN or before exceeding 4,480 CSLI, whichever is later. Use 
paragraph 3. of Accomplishment Instructions of ASB No. CF6-80E1 S/B 
72-A0184, Revision 1, dated February 26, 2002, to reduce the torque.

Replacement of Left Vertical Link Bolts

    (h) For CF6-80E1A2 and -80E1A4 turbofan engines, remove the 
three left vertical link bolts, P/N 1304M26P02, and replace with 
three left vertical link bolts, P/N 1304M26P05, at next shop visit. 
Bolts P/N 1304M26P05 are serialized and have a calculated life limit 
published in the Life Limits section of Chapter 5 of the engine 
manual.

Definitions

    (i) For the purpose of this AD, CSLI is defined as cycles since 
the engine was last installed on the pylon.
    (j) For the purpose of this AD, next shop visit is defined as 
induction of the engine into a shop for any reason.

Alternative Methods of Compliance

    (k) 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

    (l) You must use GE Alert Service Bulletin No. CF6-80E1 S/B 72-
A0184, Revision 1, dated February 26, 2002, for reducing the bolt 
torque required by this AD. 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 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 can review a copy 
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.

Related Information

    (m) The Direction Generale de L'Aviation Civile, which is the 
airworthiness authority for France, issued AD 2001-556(B), which 
pertains to the subject of this AD.

    Issued in Burlington, Massachusetts, on December 23, 2003.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 04-144 Filed 1-5-04; 8:45 am]
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