AD 96-18-05

This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to Bell Helicopter Textron, A Division of Textron Canada Ltd. (BHTC) Model 206L, 206L-1, and 206L-3 helicopters, that currently requires a visual inspection of the tailboom skin in the areas around the nutplates and in the areas of the tailboom drive shaft cover retention clips for cracks and corrosion using a 10-power or higher magnifying glass. This amendment requires the same actions as the existing AD, but corrects a part number that was incorrectly stated in that AD. This amendment is prompted by a recent accident and several reports of fatigue cracks in the tailboom skin in the areas around the nutplates for the tail rotor fairing and in the areas of the tail rotor drive shaft cover retention clips. The actions specified by this AD are intended to prevent failure of the tailboom and subsequent loss of control of the helicopter.

Final rule; request for comments

96-18-05 BELL HELICOPTER TEXTRON, A DIVISION OF TEXTRON CANADA LTD.: Amendment 39-9729. Docket No. 96-SW-13-AD. Supersedes priority letter AD 96-14- 10, issued July 3, 1996.

Applicability: Model 206L, 206L-1, and 206L-3 helicopters, with tailboom, part number (P/N) 206-033-004-3, -11, -45, or -103 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 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 use the authority provided in paragraph (c) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously.

To prevent failure of the tailboom and subsequent loss of control of the helicopter, accomplish the following:

(a) Before further flight, and thereafter at intervals not to exceed 50 hours time-in-service (TIS), using a 10-power or higher magnifying glass, inspect the tailboom for cracks or corrosion. Perform this inspection in accordance with the inspection procedures stated in the Accomplishment Instructions, Part II or Part III, as applicable, of Bell Helicopter Textron Inc. Alert Service Bulletin 206L-87-47, Revision C, dated October 23, 1989. If a crack or corrosion is detected that is beyond the limits prescribed by the applicable maintenance manual, remove the tailboom and replace it with an airworthy tailboom.

(b) Replacement of the tailboom with tailboom, P/N 206-033-004-143 or -177, constitutes terminating action for the requirements of this AD.

(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, Rotorcraft Directorate, 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 will not be issued.

(e) The inspections and replacement shall be done in accordance with Bell Helicopter Textron Inc. Alert Service Bulletin 206L-87-47, RevisionC, dated October 23, 1989. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Bell Helicopter Textron Canada, A Division of Textron Canada Ltd., 12,800 rue de L'Avenir, Mirabel, Quebec, Canada, JON 1LO. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(f) This amendment becomes effective on September 16, 1996.

On July 3, 1996, the FAA issued priority letter AD 96-14-10, to require, before further flight, and thereafter at intervals not to exceed 50 hours time-in-service (TIS), a visual inspection of the tailboom skin in the areas around the nutplates and in the areas of the tailboom drive shaft cover retention clips for cracks and corrosion using a 10-power or higher magnifying glass. This inspection interval was to be repeated until the tailboom was replaced by part number (P/N) 206-033-004-143 or -173. That action was prompted by a recent accident and several reports of fatigue cracks in the tailboom skin in the areas around the nutplates for the tail rotor fairing and in the areas of the tail rotor drive shaft cover retention clips. That condition, if not corrected, could result in failure of the tailboom and subsequent loss of control of the helicopter.

Since the issuance of that AD, the FAA has determined that one of the replacement tailboom s P/N should have been stated as P/N 206-033-004-177 instead of P/N 206-033-004-173.

Since an unsafe condition has been identified that is likely to exist or develop on other BHTC Model 206L, 206L-1, and 206L-3 helicopters of the same type design, this AD supersedes priority letter AD 96-14-10 to require, before further flight, and thereafter at intervals not to exceed 50 hours TIS, a visual inspection of the tailboom skin in the areas around the nutplates and in the areas of the tailboom drive shaft cover retention clips for cracks and corrosion using a 10-power or higher magnifying glass. This inspection interval will be repeated until the tailboom is replaced by P/N-206-033-004-143 or -177. The actions are required to be accomplished in accordance with the service bulletin described previously.

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 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. 96-SW-13-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 USC 106(g), 40113, 44701.

39.13 - [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive (AD), Amendment 39-9729, to read as follows