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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
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:
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PART 39–AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13 [Amended]
2. The FAA amends § 39.13 by adding the following new airworthiness directive:
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AIRWORTHINESS DIRECTIVE
Aircraft Certification Service
Washington, DC
U.S. Department
of Transportation
Federal Aviation
Administration
We post ADs on the internet at "www.faa.gov"
The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Title 14 of the Code of Federal Regulations (14 CFR) part 39,
applies to an aircraft model of which our records indicate you may be the registered owner. Airworthiness Directives affect aviation safety and are regulations which require immediate
attention. You are cautioned that no person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of the Airworthiness
Directive (reference 14 CFR part 39, subpart 39.3).
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 cyclessince-
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.
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(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
　
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