This amendment adopts a new airworthiness directive (AD) applicable to Bell Helicopter Textron, Inc. (BHTI) Model 206A, 206A-1, 206B, 206B-1, 206L, 206L-1, and 206L-3 series helicopters, equipped with swashplate support assembly, part number (P/N) 206-010-452-001, -005, or -109. BHTI has received three reports of swashplate support assemblies with cracks in the fillet radius area near the base. The cracks originated on the aft section of the swashplate support assembly. The total time-in-service (TIS) on each of the reported swashplate support assemblies exceeded 1,500 hours. The swashplate support assembly is a critical, non-rotating, rotor system component that supports the rotating swashplate. Through the swashplate support assembly and subsequently the swashplate, the pilot control movements that are necessary to maintain rotorcraft control are transferred to the main rotor system. Therefore, a crack in a swashplate support assembly creates an unsafe condition. This condition, if not corrected, could result in failure of the swashplate support assembly, loss of control of the main rotor system, and subsequent loss of control of the helicopter.
The FAA has reviewed and approved Bell Helicopter Textron, Inc. Alert Service Bulletin No. 206-93-74, Revision B, and 206L-93-89, Revision B, both dated April 4, 1994, which describe procedures for an initial visual inspection for cracks within the next 25 hours TIS using a 10-power magnifying glass, and thereafter, repetitive visual inspections for cracks at intervals not to exceed 50 hours TIS from the last inspection. The inspections are for swashplate support assemblies that have more than 1,500 hours TIS. If a crack is suspected, the Alert Service Bulletins provide for a dye penetrant inspection. If a crack is found, the applicable Alert Service Bulletin specifies replacement of the swashplate support assembly with an airworthy swashplate support assembly prior to the next flight. Neither BHTI Alert Service Bulletin No. 206-93-74, Revision B, nor 206L-93-89, Revision B, both dated April 4, 1994, shows the Model 206A-1 as being an affected model helicopter. However, this model helicopter uses the same swashplate support assembly as the Model 206A helicopter. Therefore, for purposes of this AD, Alert Service Bulletin No. 206-93-74, Revision B, dated April 4, 1994, will also apply to the Model 206A-1 helicopter.
Since an unsafe condition has been identified that is likely to exist or develop on other Bell Helicopter Textron, Inc. Model 206A, 206A-1, 206B, 206B-1, 206L, 206L-1, and 206L-3 series helicopters of the same type design, this AD is being issued to prevent failure of the swashplate support assembly, loss of control of the main rotor system, and subsequent loss of control of the helicopter. For swashplate support assemblies that have 1,500 hours or more total TIS, this AD requires an initial visual inspection for cracks using a 10-power or higher magnifying glass within 25 hours TIS. Also, for swashplate support assemblies with less than 1,500 hours total TIS, this AD requires an initial visual inspection for cracks using a 10-power or higher magnifying glass prior to attaining 1,525 hours total TIS. Thereafter, repetitive inspections of the affected swashplate support assemblies are required at intervals not to exceed 50 hours TIS from the last inspection. If a crack is suspected, a dye penetrant inspection is required. Replacement of cracked swashplate support assemblies with airworthy swashplate support assemblies is required. Installation of an airworthy swashplate support assembly, P/N 206-010-452-113, constitutes a terminating action for the requirements of this AD. The actions are required to be accomplished in accordance with the service bulletins described previously. Due to the criticalness of the swashplate suppor t assembly and the short compliance times, this rule must be issued immediately to correct an unsafe condition in aircraft.
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.
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 supportsthe 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 Number 93-SW-22-AD." The postcard will be date stamped and returned to the commenter.
The regulations adopted herein will not have substantial direct effects 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, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.
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. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89.
39.13 - [AMENDED]
2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: