AD 98-16-02 Airworthiness Directives; Eurocopter France Model SA 3180, SA 318B, SA 318C, SE 3130, SE 313B, SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 Helicopters

Models named: SA 3180, SA 318B, SA 318C, SE 3130, SE 313B, SA.315B, SA.316B, SA.316C, SA.319B, SE.3160. Read the applicability below — it usually turns on serial or part numbers too.

Model SA 3180, SA 318B, SA 318C, SE 3130, SE 313B, SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters, with tail rotor blades, part number (P/N) 3160S-34-10000-all dash numbers, or P/N 3160S-34-11000-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 (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 10 hours time-in-service (TIS), and thereafter at intervals not to exceed 10 hours TIS, unless accomplished previously. To prevent fatigue failure of a tail rotor blade (blade), and subsequent loss of control of the helicopter, accomplish the following: (a) With the blade installed on the helicopter: (1) Clean the blade root skin area using Teepol or an equivalent product. (2) Using an 8-power or higher magnifying glass, visually inspect the blade skin near the attachment bolts on the blade cuff stem for cracks on the upper and lower surfaces. (3) If a crack is found, replace the blade with an airworthy blade. (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) This amendment becomes effective on September 4, 1998, to all persons except those persons to whom it was made immediately effective by Priority Letter AD 98-16-02, issued July 22, 1998, which contained the requirements of this amendment. Issued in Fort Worth, Texas, on August 12, 1998. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 98-22365 Filed 8-19-98; 8:45 am] BILLING CODE 4910-13-U