AD 97-24-04 Airworthiness Directives; Eurocopter France (Eurocopter) Model SE 3130, SE 313B, SA 3180, SA 318B, and SA 318C Helicopters

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

Model SE 3130, SE 313B, SA 3180, SA 318B, and SA 318C helicopters with part number (P/N) 3130-S-11-10000, 3130-S-11- 20000, or 3130-S-11-30000 main rotor blades, 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 as indicated, unless accomplished previously. To detect debonding, cracks, or corrosion in the affected blades and to prevent failure of a main rotor blade (blade) and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, and thereafter at intervals not to exceed 25 hours time-in-service, for part number (P/N) 3130-S-11- 10000, 3130-S-11-20000, or 3130-S-11-30000, visually inspect: (1) For debonding in the area extending 5 mm (0.200 inch) from the strip reinforcing the inboard edge of the blade as shown in Figure 1. If there is any debonding of the reinforcement strip, replace the blade with an airworthy blade. (2) For debonding between the blade and the reinforcement strip on the leading edge of the blade that covers the blade spar. If debonding is present for more than 0.750 inches 2 (500 mm 2 ) at any point on the blade, replace the blade with an airworthy blade. (3) For cracks in the blade skin in the first 12 inches (300 mm) of the blade measured from the root reinforcement strip using a 3 x or higher magnifying glass. If any crack is found, replace the blade with an airworthy blade. (4) For corrosion in the blade skin in the first 12 inches (300 mm) of the blade measured from the root reinforcement strip. If any corrosion 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, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff. 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 are prohibited. (d) This amendment becomes effective on December 8, 1997. Note 3: The subject of this AD is addressed in Direction General De L'Aviation Civile (France) AD 97-135-055(B), dated June 20, 1997. BILLING CODE 4910-13-U [[Page 62241]] [GRAPHIC] [TIFF OMITTED] TR21NO97.013 BILLING CODE 4910-13-C Issued in Fort Worth, Texas, on November 14, 1997. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 97-30603 Filed 11-20-97; 8:45 am] BILLING CODE 4910-13-U