AD 98-05-17 Airworthiness Directives; Eurocopter France Model SA-365N, SA- 365N1, AS-365N2, and SA-366G1 Helicopters

Models named: SA-365N, SA-365N1, AS-365N2, SA-366G1. Read the applicability below — it usually turns on serial or part numbers too.

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 (b) 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.

Required within 50 hours time-in-service, unless accomplished previously. To prevent an outboard fin from separating and contacting the rotor blades during flight, resulting in loss of control of the helicopter, accomplish the following: (a) For helicopters with outboard fins that are secured with outboard fin attachment studs (studs), part number (P/N) 365A13- 3017-24, which have not been modified in accordance with MOD 0755B08, remove the outboard fins and inspect for the presence of washers in the seating plane of the outboard fins. (1) If washers are present, inspect for rotational play or looseness of the washers. (2) If washers are not present, use shims to inspect for play or looseness between the stud and the seating plane. (3) With each outboard fin removed, inspect each stud to ensure there is no incremental rotational movement or pure rotation when the tightening torque load specified in paragraph B.1) of the Accomplishment Instructions of both Eurocopter France AS 365 Service Bulletin No. 01.00.40, Revision No. 1, which is applicable to Model SA-365N, SA-365N1, and AS-365N2 helicopters, and Eurocopter France AS 366 Service Bulletin No. 01.20, Revision No. 1, which is applicable to Model SA-366G1 helicopters, both dated October 24, 1996, is applied. (4) If no play or looseness between the stud and the seating plane and no incremental rotational movement or pure rotation is discovered, reinstall the outboard fins as specified in paragraph B.2) of the Accomplishment Instructions in the applicable service bulletins specified in paragraph (3) of this AD. (5) If play or looseness between the stud and the seating plane and incremental movement or rotation is discovered, remove the washers (if present) and studs and perform a dye-penetrant inspection of the stud for cracks in accordance with paragraph B.3) of the Accomplishment Instructions in the applicable service bulletins specified in paragraph (3) of this AD. (6) If a crack is discovered as a result of the inspection required by paragraph (5) of this AD, replace the stud with an airworthy stud. Reinstall the outboard fin in accordance with Note I in the applicable service bulletins specified in paragraph (3) of this AD. (b) 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. (c) 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. (d) The inspections shall be done in accordance with Eurocopter France AS 365 Service Bulletin No. 01.00.40, Revision No. 1, and Eurocopter France AS 366 Service Bulletin No. 01.20, Revision No. 1, both dated October 24, 1996. These incorporations by reference were 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. (e) This amendment becomes effective on March 23, 1998. [[Page 11118]] Note 3: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 94-077-016(B)R1 and AD 94- 076-036(B)R1, both dated December 4, 1996. Issued in Fort Worth, Texas, on February 26, 1998. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 98-5733 Filed 3-5-98; 8:45 am] BILLING CODE 4910-13-P