98-10-09: Blade Spar for Crack Inspection

98-10-09 EUROCOPTER FRANCE: Amendment 39-10725. Docket No. 98-SW-23-AD. Supersedes AD 98-04-40, Amendment 39-10479, Docket 98-SW-09-AD. \n\n\tApplicability: Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters, with main rotor blades, part numbers 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, with 400 or more hours time-in-service (TIS), 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 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 (f) torequest 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. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent separation of a blade and subsequent loss of control of the helicopter, accomplish the following: \n\n\t(a)\tWithin 25 hours TIS, inspect each blade spar for cracks using a dye-penetrant method in accordance with paragraphs CC.1 through CC.4 of the Operational Procedures in Eurocopter France Service Telex No. 00055/0034/98, dated February 3, 1998 (Eurocopter Service Telex: 316/319 No. 01.64 and 315 No. 01.29). \n\n\t(b)\tWithin 25 hours TIS, visually inspect the upper and lower surfaces of each blade cuff for cracks, especially around the attachment bolts, using a 10-power or higher magnifying glass. \n\n\t(c)\tWithin 25 hours TIS from the last required inspection of each blade spar for cracks in the area indicated in Figure 1, and thereafter at intervals not to exceed 25 hours TIS: \n\n\t\t(1)\tWithout removing the blade from the helicopter, clean each blade root area using "Teepol" or an equivalent product. \n\n\t\t(2)\tSupport the blade tip to eliminate blade droop while inspecting the lower blade surface. \n\n\t\t(3)\tVisually inspect each blade spar with a 10-power or higher magnifying glass 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\t\t(4)\tBefore returning the blades to service, confirm that there is a sealing bead (1) around the edge of the blade cuff. \n\n\tNOTE 2: Eurocopter France Service Telex No. 00060/00099/98, dated April 9, 1998 (Eurocopter Service Telex: 316/319 No. 01.65 and 315 No. 01.30) pertains to the subject of this AD. \n\n\t(d)\tIf more than 25 hours TIS have elapsed since the last required inspection of each blade spar for cracks in the area indicated in Figure 1, before further flight, conduct the inspections required by paragraph (c) of this AD. \n\n\t(e)\tIf a crack is found in a blade spar or cuff, remove the blade and replace it with an airworthy blade prior to further flight. \n\n\t(f)\tAn 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. \n\n\tNOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. \n\n\t(g)\tSpecial flight permits will not be issued. \n\n\t(h)\tThe inspection shall be done in accordance with paragraphs CC.1 through CC.4 of the Operational Procedures in Eurocopter France Service Telex No. 00055/0034/98, dated February 3, 1998 (Eurocopter Service Telex: 316/319 No. 01.64 and 315 No. 01.29). 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\tNOTE 4:The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 98-088-055(A) and 98-089-038(A), both dated February 25, 1998; and Direction Generale De L'Aviation Civile (France) AD 98-170-056(A)R1 and 98-171-039(A)R1, both dated May 6, 1998. \n\n\t(i)\tThis amendment becomes effective on September 15, 1998, to all persons except those persons to whom it was made immediately effective by Priority Letter AD 98-10-09, issued May 6, 1998, which contained the requirements of this amendment.