98-23-09: Tail Rotor Shaft Flapping Hinge Retainer

98-23-09 EUROCOPTER FRANCE: Amendment 39-10875. Docket No. 97-SW-38-AD. Applicability: Model SA 330F, G, and J helicopters with tail rotor head assembly, part number 330 A 33 0000 all dash numbers, or 330 A 33 0001 all dash numbers, 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 changedconfiguration 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 on a tail rotor shaft flapping hinge retainer (retainer) that could lead to high tail rotor vibrations, loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, and thereafter before the first flight of each day, perform a dye-penetrant inspection of each retainer for cracks. (b) If a crack is found on any retainer, replace it with an airworthy retainer before further flight. NOTE 2: Eurocopter Service Bulletin No. 05.84, Revision No. 1, dated January 29, 1996, pertains to the subject 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 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. (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. NOTE 4: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 96-076-075(AB)R1, dated November 5, 1997. (e) This amendment becomes effective on December 15, 1998.