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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 lifelimited
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.
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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 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
　
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