Transport Canada, which is the airworthiness authority for Canada, notified the FAA that an unsafe condition may exist on BHTC Model 222, 222B, 222U, and 230 helicopters. Transport Canada advises that an investigation into the crash of a BHTC Model 222 helicopter revealed that one of the two drive pins, part number (P/N) 222-010-455-003, had failed due to an insufficient interference fit between the pin and the ring.
BHTC has issued Service Bulletins 230-99-16, 222U-99-55, and 222-99-84, all dated February 15, 1999. These service bulletins describe procedures for inspecting each drive pin, P/N 222-010-455-003, for damage or looseness; conducting an initial torque test to determine if the interference fit between each drive pin and ring is adequate; and replacing any unairworthy drive pin. Transport Canada classified these service bulletins as mandatory and issued AD No. CF-99-16, dated June 9, 1999, to ensure the continued airworthiness of these helicopters in Canada.
These helicopter models are manufactured in Canada and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, Transport Canada has kept the FAA informed of the situation described above. The FAA has examined the findings of Transport Canada, reviewed all available information, and determined that AD action is necessary for products of these type designs that are certificated for operation in the United States.
Since an unsafe condition has been identified that is likely to exist or develop on other BHTC Model 222, 222B, 222U, and 230 helicopters of these same type designs registered in the United States, this AD is being issued to prevent fatigue failure of a drive pin, P/N 222-010-455-003, and subsequent loss of control of the helicopter. This AD requires inspecting each drive pin for damage or looseness, an initial torque test to determine if the interference fit between the drive pin and ring is adequate, and replacing any unairworthy drive pin. The actions are required to be accomplished in accordance with the service bulletins described previously.
The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the controllability and structural integrity of the helicopter. Therefore, an inspection and torque test of the drive pin is required within the next 50 hours time-in-service (TIS) and this AD must be issued immediately.
Since 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.
The FAA estimates that 105 helicopters will be affected by this AD, that itwill take approximately 1 work hour to accomplish the inspection and the torque test, and that the average labor rate is $60 per work hour. A special tool to perform the torque test will cost approximately $196 per helicopter. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $26,880.
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 FAA-public 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 self-addressed, stamped postcard on which the following statement is made: "Comments to Docket No. 99-SW-77-AD." The postcard will be date stamped and returned to the commenter.
The regulations adopted herein willnot 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 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 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. Section 39.13 is amended by adding a new airworthiness directive to read as follows: