AD 98-06-35 ACTIVE

This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SA-366G1 helicopters. This action requires initial and repetitive inspections of the tail rotor blade Kevlar tie-bar (Kevlar tie-bar) for delaminations. This amendment is prompted by a report of delamination of a Kevlar tie-bar. The actions specified in this AD are intended to detect delaminations of the Kevlar tie-bar, that could result in loss of anti-torque function and subsequent loss of control of the helicopter.

Final rule; request for comments

98-06-35 EUROCOPTER FRANCE: Amendment 39-10414. Docket No. 97-SW-31-AD.
Applicability: Model SA-366G1 helicopters, with tail rotor blades, part numbers (P/N) 365A12-0010-all dash numbers, 365A12-0020-01, 365A33-2131-all dash numbers, or 365A12-0020-03, 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 (d) 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 detect delaminations of the tail rotor blade Kevlar tie-bar (Kevlar tie-bar), that could result in loss of anti-torque function and subsequent loss of control of the helicopter, accomplish the following:

(a) Within 10 hours time-in-service (TIS), inspect each Kevlar tie-bar in accordance with paragraph CC of Eurocopter France Telex Service Bulletin 05.19, dated August 19, 1992. This initial inspection is not required for blade P/N 365A12-0020-03.

NOTE 2: Twisting the Kevlar tie-bar slightly when inspecting will make it easier to identify any faults.

(b) Within 250 hours TIS, and thereafter at intervals not to exceed 250 hours TIS, inspect each Kevlar tie-bar in accordance with paragraph 2.B of Eurocopter France Service Bulletin 05.20, Revision 3, dated November 14, 1996.

(c) If any delamination is found during any of the inspections required by paragraphs (a) or (b) of this AD, remove the blade and replace it with an airworthy blade before further flight.

(d) 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 Standards Staff, 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 Standards Staff.

NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff.

(e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished.

(f) The inspections shall be done in accordance with Eurocopter France Telex SB 05.19, dated August 19, 1992 and Eurocopter France SB 05.20, Revision 3, dated November 14, 1996. 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 American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

NOTE 4: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 92-186-014(B)R4, dated December 4, 1996.

(g) This amendment becomes effective on April 6, 1998.

The Direction Generale De L Aviation Civile (DGAC), which is the airworthiness authority for France, recently notified the FAA that an unsafe condition may exist on Model SA-366G1 helicopters. The DGAC advises that delamination outside certain tolerance limits may occur on Kevlar tie-bars.

Eurocopter France has issued Eurocopter France Telex Service Bulletin No. 05.19, dated August 19, 1992, which specifies visually checking the condition of the Kevlar tie-bar assembly for delamination around the blade-to-hub attachment point within 10 flying hours, and if delamination exists that is outside certain tolerance limits, removing the tail rotor blade and replacing it with an airworthy blade. Eurocopter France also issued Eurocopter France SA 366 Service Bulletin No. 05.20, Revision 3, dated November 14, 1996, which specifies repetitive visual inspections of the Kevlar tie-bar for delamination, and if delamination exists that is outside certain tolerance limits, removing the tail rotor blade and replacing it with an airworthy tail rotor blade at intervals of 250 flying hours. The DGAC classified these service bulletins as mandatory and issued DGAC AD 92-186-014(B)R4, dated December 4, 1996, in order to assure the continued airworthiness of these helicopters in France.

This helicopter model is manufactured in France and is 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, the DGAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the DGAC, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.

The FAA estimates that 91 helicopters of U.S. registry will be affected by this AD, that it will take 4 work hours per helicopter to accomplish the actions, and that the average labor rate is $60 per work hour. Required parts will cost approximately $3,000 per helicopter. Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $294,840.

Since an unsafe condition has been identified that is likely to exist or develop on other Eurocopter France Model SA-366G1 helicopters of the same type design registered in the United States, this AD is being issued to detect delaminations of the Kevlar tie-bar, that could result in loss of anti-torque function and subsequent loss of control of the helicopter. 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 of the helicopter. Therefore, an initial inspection within 10 hours time-in-service is required 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.

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. 97-SW-31-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. 106(g), 40113, 44701.

39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive to read as follows:

Submit comments in triplicate to the Federal Aviation Administration (FAA), Office of the Regional Counsel, Southwest Region, Attention: Rules Docket No. 97-SW-31-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.
The service information referenced in this AD may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. This information may be examined at the FAA, Office of the Regional Counsel, Southwest Region, 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.

Mr. Mike Mathias, Aerospace Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5123, fax (817) 222-5961.