This amendment adopts a new AD for BHTI Model 412, 412EP, and 412CF helicopters. This AD requires inspecting and replacing any cracked cap angle, part number (P/N) 212-030-191-001, and repairing any cracked adjacent structure. This AD is prompted by a report of a fatigue crack in a tailboom attachment cap angle. This condition, if not corrected, could result in loss of the tailboom and subsequent loss of control of the helicopter. \n\n\tThe FAA has reviewed BHTI Alert Service Bulletin No. 412-00-100, and the temporary revision to the Maintenance Manual, BHT-412-MM, both dated March 24, 2000, which specify inspecting the cap angle and adjacent structure for a crack and contacting BHTI if a crack is found. \n\n\tWe have identified an unsafe condition that is likely to exist or develop on other BHTI Model 412, 412EP, and 412CF helicopters of these same type designs. This AD is being issued to prevent failure of a cap angle, loss of the tailboom, and subsequent loss of control of the helicopter. This AD requires, within 25 hours time-in-service (TIS) and thereafter at intervals not to exceed 100 hours TIS, inspecting the cap angle, P/N 212-030-191-001, for a crack. Before further flight, if a crack is found, this AD requires replacing any cracked cap angle with an airworthy cap angle and repairing any cracked adjacent structure. This AD also requires reporting any crack to the Manager, Rotorcraft Certification Office. \n\n\tThe short compliance time involved is required because the previously described critical unsafe condition can adversely affect the controllability or structural integrity of the helicopter. Therefore, inspecting the cap angle, P/N 212-030-191-001, for a crack is required within 25 hours TIS and this AD must be issued immediately. \n\n\tSince a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days. \n\n\tThe FAA estimates that 149 helicopters will be affected by this AD, that it will take approximately l/2 work hour to inspect a cap angle and approximately 15 work hours to replace and repair each part, and that the average labor rate is $60 per work hour. Required parts will cost approximately $279 per helicopter. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $180,141 assuming all cap angles are replaced. \n\nComments Invited \nAlthough 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. \n\n\tComments 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 FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket. \n\n\tCommenters 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. 2000-SW-29-AD." The postcard will be date stamped and returned to the commenter. \n\n\tThe 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. \n\n\tThe 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 otherwisewould 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 location provided under the caption "ADDRESSES." \n\nList of Subjects in 14 CFR Part 39 \nAir transportation, Aircraft, Aviation safety, Safety. \n\nAdoption of the Amendment \nAccordingly, 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: \n\nPART 39 - AIRWORTHINESS DIRECTIVES \n1. The authority citation for part 39 continues to read as follows: \n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n§ 39.13 (Amended) \n2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: