AD 98-12-08

This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France (Formerly Aerospatiale, Society Nationale Industrielle, Sud Aviation) Model SA-365N, SA-365N1, AS-365N2, and SA-366G1 helicopters, that requires an inspection of the transmission deck for cracks; repair of any cracked transmission deck; and replacement of the transmission deck support beams (support beams) with redesigned support beams. This amendment is prompted by several reports of cracks in the transmission deck and support beams. The actions specified by this AD are intended to detect cracks that reduce the strength of the main gearbox strut attachment and could result in failure of the main gearbox mounting, and subsequent loss of control of the helicopter.

Final rule

98-12-08 EUROCOPTER FRANCE (FORMERLY AEROSPATIALE, SOCIETY NATIONALE INDUSTRIELLE, SUD AVIATION): Amendment 39-10564. Docket No. 96-SW-22-AD.

Applicability: Model SA-365N, SA-365N1, AS-365N2, and SA-366G1 helicopters, 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 detect cracks that reduce the strength of the main gearbox strut attachment and could result in failure of the main gearbox mounting, and subsequent loss of control of the helicopter, accomplish the following:

(a) For Model SA-365N, SA-365N1, and SA-366G1 helicopters, on or before attaining 4,000 hours time-in-service (TIS), or within 50 hours TIS after the effective date of this AD, whichever occurs later; and for Model SA-365N2 helicopters, on or before attaining 2,000 hour TIS, or within 50 hours TIS after the effective date of this AD, whichever occurs later; perform the following:

(1) Inspect the transmission deck for cracks using a dye-penetrant inspection method, in accordance with paragraph BB of Eurocopter France Telex Service No. 10011, dated February 24, 1995. If a crack is found in the transmission deck, repair prior to further flight.

NOTE 2: A FAA-approved repair solution can be initiated by contacting the American Eurocopter Technical Support Department, ATTN: Manager, telephone (972) 641-3460, fax (972) 641-3527.

(2) Replace the currently installed transmission deck support beams, part numbers (P/N) 365A21-3365-49 and 365A21-3365-CY, with reinforced transmission deck support beams, P/N 365A21-3365-JE-01 and 365A21-3365-JF-01, in accordance with the Accomplishment Instructions in Eurocopter France Service Bulletin No. 05.00.36, Rev. 1, dated December 16, 1996.

(b) After completion of paragraphs (a)(1) and (a)(2) of this AD, clean, prime and paint the affected areas of the transmission deck and the reinforced support beams in accordance with paragraph BB 2A of Eurocopter France Telex Service No. 10011, dated February 24, 1995.

(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 Standards Staff, FAA, Rotorcraft Directorate. 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.

(d) 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.

(e) The inspection and repair or modification, if necessary, shall be done in accordance with the Accomplishment Instructions in Eurocopter France Service Bulletin No. 05.00.36, Rev. 1, dated December 16, 1996, and paragraphs BBand BB 2A of Eurocopter France Telex Service No. 10011, dated February 24, 1995. 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; 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 95-068-017(B) and AD 95-067-038(B), both dated April 12, 1995.

(f) This amendment becomes effective on July 9, 1998.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to Eurocopter France SA-365N, SA-365N1, AS-365N2, and SA-366G1 helicopters was published in the Federal Register on December 3, 1997 (62 FR 63912). That action proposed to require an inspection of the transmission deck for cracks; repair of any cracked transmission deck; and replacement of the support beams with redesigned support beams.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA's determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

The FAA estimates that 137 helicopters of U.S. registry will be affected by this AD, that it will take approximately 50 work hours per helicopter to accomplish the required actions, and that the average labor rate is $60 per work hour. Required parts will cost approximately $5,000 per helicopter. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $1,096,000.

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.

For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive ornegative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it 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: