Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report that summarizes each FAApublic contact concerned with the substance of this AD will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this rule must submit a selfaddressed, stamped postcard on which the following statement is made: ``Comments to Docket Number 2000NM136AD.'' The postcard will be date stamped and returned to the commenter.

Regulatory Impact

The regulations adopted herein 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132.

For the reasons discussed above, I certify that this action (1) is not a ``significant regulatory action'' under Executive Order 12866; (2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment

Accordingly, pursuant to 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 39AIRWORTHINESS DIRECTIVES

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]

2. Section 39.13 is amended by adding the following new airworthiness directive:

20002215 Boeing: Amendment 3911962. Docket 2000NM136AD.

Applicability: Model 747100, 200B, 200C, 200F, and 300 series airplanes; certificated in any category; equipped with Pratt & Whitney Model JT9D3 or 7 series engines, General Electric Model CF645 or 50 series engines, or RollsRoyce Model RB211524B, C, or D series engines; delivered in or modified into the stretched upper deck (SUD) configuration; and having angle assemblies with Boeing part numbers 015U045463 and 015U045464 installed at body station 970.

Note 1: Model 747100 SUD series airplanes on which paragraph (g) of AD 20000530 has been accomplished are not required to comply with this AD.

Note 2: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent chafing and failure of engine thrust control cables, which could result in a severe asymmetric thrust condition during landing, and consequent reduced controllability of the airplane, accomplish the following:
[[Page 66609]]
Inspection/Modification/Replacement
(a) Within 18 months after the effective date of this AD, perform a detailed visual inspection and measure the clearance between the engine thrust control cables and the cable penetration holes, in accordance with the Cable Chafing Inspection of the Accomplishment Instructions of Boeing Service Bulletin 747532327, Revision 2, dated September 24, 1998. If insufficient clearance exists, as specified in the service bulletin, prior to further flight, accomplish paragraphs (a)(1) and (a)(2) of this AD. (1) Modify the cable penetration holes or replace the plate, as applicable, in accordance with Figure 7 of the service bulletin. (2) Perform a detailed visual inspection of the engine thrust control cables in the area of the plate to detect wear and broken wires in accordance with Appendix 1 (including Figure 1) of this AD. If any wear is within the criteria contained in Appendix 1 (including Figure 1) of this AD, no further action is required by this paragraph. If any wear outside the criteria contained in Appendix 1 (including Figure 1) of this AD is found, prior to further flight, replace the cable with a new cable, in accordance with the procedures described in the Boeing 747 Maintenance Manual.

Note 3: For the purposes of this AD, a detailed visual inspection is defined as: ``An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.''
Alternative Methods of Compliance
(b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO.

Note 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.
Special Flight Permits
(c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.
Incorporation by Reference
(d) Except as provided by paragraph (a)(2) of this AD, the actions shall be done in accordance with Boeing Service Bulletin 747532327, Revision 2, dated September 24, 1998. This
incorporation by reference was approved previously by the Director of the Federal Register as of April 24, 2000 (65 FR 14838, March 20, 2000). Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 981242207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Effective Date
(e) This amendment becomes effective on November 22, 2000. APPENDIX 1THRUST CONTROL CABLE INSPECTION PROCEDURE
1. Detailed Visual Inspection To Detect Wear
A. Perform a detailed visual inspection of the engine thrust control cables in the area of the plate to detect wear.
B. Replace the cable assembly if any of the following criteria are met:
(1) One cable strand had worn wires where one wire cross section is decreased by more than 40 percent (see Figure 1).
(2) A kink is found.
(3) Corrosion is found.
2. Inspection To Detect Broken Wires
A. To check for broken wires, rub a cloth along the length of the cable. The cloth catches on broken wires.
B. Replace the cable assembly if any of the following criteria are met.
(1) Replace the 7x7 cable assembly if there are two or more broken wires in 12 continuous inches of cable or there are three or more broken wires anywhere in the total cable assembly.
(2) Replace the 7x19 cable assembly if there are four or more broken wires in 12 continuous inches of cable or there are six or more broken wires anywhere in the total cable assembly.
BILLING CODE 491013P
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[GRAPHIC] [TIFF OMITTED] TR07NO00.027

[[Page 66611]]

Issued in Renton, Washington, on October 30, 2000. Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 0028233 Filed 11600; 8:45 am] BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Dionne Krebs, Aerospace Engineer, Propulsion Branch, ANM140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 980554056; telephone (425) 2272250; fax (425) 2271181.