This amendment adopts a new AD for BHTI Model 214B and 214B-1 helicopters. This action requires, within 10 hours TIS, determining the hours TIS for each strap fitting, P/N 214-010-185-107, and creating a component history card or equivalent record for each strap fitting. This action also requires that if a strap fitting has 2,500 or more hours TIS or if the hours TIS cannot be determined, replacing the strap fitting with an airworthy strap fitting before further flight. This strap fitting is structurally identical to strap fitting, P/N 214-010-189-103, which currently has a retirement life of 2,500 hours. The strap fitting has been sold for spares since approximately 1982. This amendment is prompted by fatigue testing which indicates that a fatigue crack may occur in the strap fitting leading to failure of the strap fitting if it is allowed to remain in service in excess of 2,500 hours. The actions specified in this AD are intended to prevent a failure of a strap fitting, separation of a main rotor blade, and subsequent loss of control of the helicopter.
The FAA has reviewed BHTI Alert Service Bulletin 214-00-62, dated June 2, 2000, which describes procedures for establishing a 2,500-hour airworthiness life pending formal revision of the 214B series Maintenance Manual and provides information to determine continued serviceability for strap fitting, P/N 214-010-185-107.
We have identified an unsafe condition that is likely to exist or develop on other BHTI Model 214B and 214B-1 helicopters of the same type design. Therefore, this AD is being issued to require the following for each strap fitting, P/N 214-010-185-107:
o Within 10 hours TIS, by referring to the helicopter maintenance records, create a component history card or equivalent record for each strap fitting and record the hours TIS and serial number.
o If the hours TIS cannot be determined, replace the strap fitting with an airworthy strap fitting before further flight.
o If the strap fitting has accumulated 2,500 or more hours TIS, replace it with an airworthy strap fitting before further flight.
o Continue to record the subsequent hours TIS.
o Revise the Airworthiness Limitations section of the maintenance manual by establishing a retirement life of 2,500 hours TIS for the strap fitting.
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, replacing any strap fitting, P/N 214-010-185-107, that has 2,500 or more hours TIS or a strap fitting for which the hours TIS cannot be determined is required within 10 hours 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 11 helicopters will be affected by this proposed AD, that it will take approximately 14 work hours to replace each of the 2 strap fittings, 2 work hours to create a new component history card, and 10 work hours annually to maintain the records, and that the average labor rate is $60 per work hour. Required parts will cost approximately $4807 per helicopter. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $79,277 the first year assuming all strap fittings will be replaced.
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 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 mailed comments submitted in response to this rulemust submit a self-addressed, stamped postcard on which the following statement is made: "Comments to Docket No. 2000-SW-56-AD." 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 location provided under the caption "ADDRESSES."
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 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: