AD 98-10-09 Airworthiness Directives; Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 Helicopters

Models named: 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.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. 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 (f) 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 prevent separation of a blade and subsequent loss of control of the helicopter, accomplish the following: (a) Within 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). (b) Within 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. (c) Within 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: (1) Without removing the blade from the helicopter, clean each blade root area using ``Teepol'' or an equivalent product. (2) Support the blade tip to eliminate blade droop while inspecting the lower blade surface. (3) Visually 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). (4) Before returning the blades to service, confirm that there is a sealing bead (1) around the edge of the blade cuff. Note 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. (d) If 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. (e) If a crack is found in a blade spar or cuff, remove the blade and replace it with an airworthy blade prior to further flight. BILLING CODE 4910-13-U [[Page 46163]] [GRAPHIC] [TIFF OMITTED] TR31AU98.000 BILLING CODE 4910-13-C [[Page 46164]] (f) 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. (g) Special flight permits will not be issued. (h) The 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. 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. (i) This 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. Note 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. Issued in Fort Worth, Texas, on August 21, 1998. Larry M. Kelly, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 98-23095 Filed 8-28-98; 8:45 am] BILLING CODE 4910-13-U