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2001-04-13 EUROCOPTER FRANCE: Amendment 39-12132. Docket No. 2000-SW-13-AD. Supersedes AD 98-10-09, Amendment 39-10725, Docket No. 98-SW-23-AD. \n\n\tApplicability: Model SA.315B, SA.316B, SA.316C, SE.3160, and SA.319B helicopters with a main rotor blade (blade), with any of the following part numbers (P/N): 3160S11-10000 all dash numbers, 3160S11-30000 all dash numbers, 3160S11-35000 all dash numbers, 3160S11-40000 all dash numbers, 3160S11-45000 all dash numbers, 3160S11-50000 all dash numbers, or 3160S11-55000 all dash numbers, installed, certificated in any category. \n\n\tNote 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise 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 request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent a blade separation and subsequent loss of control of the helicopter, accomplish the following: \n\n\t(a) Within 25 hours time-in-service (TIS) or before the next flight following the onset of any one- per-rev vibration, whichever occurs first, and thereafter at intervals not to exceed 100 hours TIS or 600 "cycles" (a "cycle" is any landing, regardless of whether the main rotor rotation is continued or stopped, or any completion of an external load operation; e.g., load release), whichever occurs first, \n\n\t\t(1) Inspect each blade spar for a crack. \n\n\t\t\t(i) Withoutremoving the blade from the helicopter, clean each blade root area using "Teepol" or an equivalent product. \n\n\t\t\t(ii) Support the blade tip to eliminate blade droop while inspecting the lower blade surface. \n\n\t\t\t(iii) By either a dye penetrant or eddy current method, inspect each blade along the hatched area indicated in Figure 1, beginning on the blade lower surface, then on the flat section of the trailing edge (B), on the blade upper surface, and then on the flat section of the leading edge (A). \n\n\tNote 2: Eurocopter France Service Bulletins (SB) SA 315 No. 05.39 and SA 316/319 No. 05.98, dated November 12, 1999, pertain to the subject of this AD. \n\n\t\t\t(iv) If a crack is found, replace the blade with an airworthy blade before further flight. \n\n\n\n\nFigure 1 \n\n\n\t\t(2) Ensure that there is a sealant bead (1) around the edge of each blade cuff. If no sealant bead exists or if a sealant bead shows excessive wear, before further flight, apply a sealant bead in accordance with paragraph 2.2 of the Accomplishment Instructions of Eurocopter France SB 65.137R1, dated November 17, 1993. \n\n\t(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, Regulations Group, 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, Regulations Group. \n\n\tNote 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Regulations Group. \n\n\t(c) Special flight permits will not be issued. \n\n\t(d) The modification shall be done in accordance with paragraph 2.2 of the Accomplishment Instructions of Eurocopter France SB 65.137R1, dated November 17, 1993. 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. \n\n\t(e) This amendment becomes effective on April 16, 2001. \n\n\tNote 4: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 1998-171-039(A)R2 and 1998-170-056(A)R2, both dated January 12, 2000.
