The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the structural integrity and controllability of the helicopter. Therefore, the above actions are required at the specified time intervals, and this AD must be issued immediately.

Since it was found that immediate corrective action was required, notice and opportunity for prior public comment thereon were impracticable and contrary to the public interest, and good cause existed to make the AD effective immediately by individual letters issued on September 1, 2000 to
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all known U.S. owners and operators of BHTImanufactured Model OH13E, OH13H, and OH13S helicopters. These conditions still exist, and the AD is hereby published in the Federal Register as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it effective to all persons.

The FAA estimates that 300 helicopters of U.S. registry will be affected by this AD, that it will take approximately 10 work hours per helicopter to accomplish either inspection, and that the average labor rate is $60 per work hour. Required parts, if a grip needs to be replaced, will cost approximately $4,000 per grip (there are two grips on each helicopter). Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $2,580,000, assuming one inspection per helicopter and replacement of both grips on each helicopter.

Comments Invited

Although this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications should identify the Rules Docket number and be submitted in triplicate to the address specified under the caption ADDRESSES. All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed.

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 mailed comments submitted in response to this rule must submit a self addressed, stamped postcard on which the following statement is made: ``Comments to Docket No. 2000SW36AD.'' The postcard will be date stamped and returned to the commenter.

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.

The FAA has determined that this regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft, and that it is not a ``significant regulatory action'' under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed, may be obtained from the Rules Docket at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, 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 a new airworthiness directive to read as follows:
20001852 Gifton McCreay (Formerly Aerodyne Systems Engineering, LTD., Formerly Texas Helicopter Corp.), Continental Copters, Inc., Teryjon Aviation Inc., Hawkeye Rotor and Wing Flight School: Amendment 3911984. Docket No. 2000SW36AD.

Applicability: Bell Helicopter Textron, Inc. (BHTI)manufactured Model OH13E, OH13H, and OH13S helicopters, with main rotor blade grips, part number (P/N) 471201352, 471201353, 471201355,
471202521, 471202527, 4712025211, 7412025211, and 74

1201355, installed, certificated in any category.

Note 1: This AD applies to each helicopter 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 helicopters 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 (c) 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 failure of a main rotor blade grip (grip), separation of a main rotor blade, and subsequent loss of control of the helicopter, accomplish the following:
(a) Within 100 hours timeinservice (TIS) since initial installation on any helicopter or within 10 hours TIS for grips with 100 or more hours TIS, conduct a liquid penetrant or eddy current inspection of the grip threads for a crack. Thereafter, conduct the liquid penetrant or eddy current inspection at intervals not to exceed 200 hours TIS. If a crack is detected, before further flight, replace the cracked grip with an airworthy grip.
(b) On or before 1200 hours TIS, replace each grip with an airworthy grip. This AD establishes a retirement life of 1200 hours TIS for grips, P/N 471201352, 471201353, 471201355, 47120
2521, 471202527, 4712025211, 7412025211, and 741201355.
(c) 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, Rotorcraft Certification Office, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office.

Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Certification Office.
(d) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished.
(e) This amendment becomes effective on November 30, 2000, to all persons except those persons to whom it was made immediately effective by Emergency AD 20001852, issued September 1, 2000, which contained the requirements of this amendment.

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Issued in Fort Worth, Texas, on November 2, 2000. Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 0029050 Filed 111400; 8:45 am] BILLING CODE 491013U

FOR FURTHER INFORMATION CONTACT Marc Belhumeur, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, Fort Worth, Texas 761930170, telephone (817) 2225177, fax (817) 222 5783.