AD 98-08-13 Airworthiness Directives; Eurocopter France Model SA 330F, G, and J, and AS 332C, L, L1, and L2 Helicopters

Models named: SA 330F, G, J, AS 332C, L, L1, L2. Read the applicability below — it usually turns on serial or part numbers too.

Model SA 330F, G, and J helicopters with tail rotor head pitch change spider arm (spider arm), part number (P/N) 330A330104.20 or .21, or 332A330039.20 or .21, installed and Model AS 332C, L, L1, and L2 helicopters with spider arm, P/N 332A330039.20 or .21 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 (e) 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 failure of a spider arm, loss of control of the tail rotor blade, and subsequent loss of control of the helicopter, accomplish paragraphs (a) through (d) in accordance with the specified paragraphs of Eurocopter France Service Bulletin No. 01.52 R1, Revision No. 1, for Model SA 330 helicopters, or Eurocopter France AS 332 Service Bulletin No. 01.00.43, Revision No. 1, for Model AS 332 helicopters, both dated February 14, 1996: (a) Prior to the first flight of each day, inspect the root of each of the spider arms for cracks in accordance with paragraph 1.C.1) of the applicable service bulletin. (b) Within 250 hours time-in-service (TIS), or prior to the installation of a replacement spider arm, whichever occurs earlier, disassemble the tail rotor head and inspect each spider arm for cracks and fretting corrosion in accordance with Paragraph 2.B of the Accomplishment Instructions of the applicable service bulletin. The inspections in paragraph (a) of this AD are no longer required after accomplishment of the inspection specified in this paragraph. (c) If any crack is found, replace the spider arm with an airworthy spider arm in accordance with Paragraph 2.B.1)b)1) of the Accomplishment Instructions of the applicable service bulletin. Replacement of a cracked spider arm with an airworthy spider arm constitutes terminating action for the requirements of this AD. Note 2: Care should be taken to ensure that Revision 1 of the referenced service bulletins is used to set the shim thickness when attaching the spider arm upon reassembly. Operators who have complied with the initial release of the referenced service bulletins and not with Revision 1 of the service bulletins will not be in compliance with this AD. (d) If fretting corrosion is found as a result of the inspection in paragraph (b) of this AD, either repair the fretting corrosion in accordance with paragraph 2.B.1)b)2) of the Accomplishment Instructions of the applicable service bulletin; or, if the fretting corrosion is not repairable in accordance with the applicable service bulletin, replace the spider arm with an airworthy spider arm in accordance with paragraph 2.B of the Accomplishment Instructions of the applicable service bulletin. Repair of fretting corrosion in accordance with this paragraph or replacement of the spider arm with an airworthy spider arm in accordance with the applicable service bulletin constitutes terminating action for the requirements of this AD. (e) Installation of a spider that has been modified in accordance with MOD 330A07-66131 (for Model SA 330F, G, and J helicopters), or AMS 332A07-66151 (for Model AS 332C, L, L1, and L2 helicopters) constitutes a terminating action for the requirements of this AD. (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 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. (h) The inspections and replacements shall be done in accordance with Eurocopter France SA 330 Service Bulletin (SB) No. 01.52 R1, Revision No. 1, for Model SA 330 helicopters, or Eurocopter France AS 330 SB No. 01.00.43, Revision No. 1, for Model AS 332 helicopters, both dated February 14, 1996. 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 April 27, 1998. Note 4: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 95-262-056(B)R1 for the model AS 332 helicopters, and AD 95-263-073(B)R1 for the Model SA 330 helicopters, both dated April 10, 1996. Issued in Fort Worth, Texas, on April 3, 1998. Henry A. Armstrong, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 98-9477 Filed 4-9-98; 8:45 am] BILLING CODE 4910-13-U