AD 2001-12-16 Airworthiness Directives; Eurocopter France Model AS332L2 Helicopters

Models named: AS332L2. Read the applicability below — it usually turns on serial or part numbers too.

Model AS332L2 helicopters, with main rotor hub sleeve, part number (P/N) 332A31-1860-03 or -04, and sleeve-to-drag damper attachment bolt, P/N 332A31-1961-20, 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 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 (c) 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.

Required as indicated, unless accomplished previously. To detect corrosion on a sleeve-to-blade damper attachment bolt (bolt) or a crack on the main rotor blade sleeve yoke (sleeve) and to prevent failure of the damper attachment and subsequent loss of control of the helicopter, accomplish the following: (a) For sleeves with 175 or less hours time-in-service (TIS), before accumulating 275 hours TIS, and thereafter at intervals not to exceed 275 hours TIS, remove the sleeve-to-blade-damper assembly in accordance with paragraph 2.B.2 of the Accomplishment Instructions in Eurocopter Service Bulletin No. 05.00.53, Revision 1, dated July 6, 1999 (SB), and inspect in accordance with paragraphs 2.B.2.1, 2.B.2.2, and 2.B.2.3 of the SB. Returning a sleeve to the manufacturer is not required by this AD. Replace any unairworthy part before further flight. (b) For sleeves with more than 175 hours TIS that have not complied with paragraph (a) of this AD, before the first flight of each day, visually inspect the sleeve for a crack in accordance with paragraph 2.B.1 of the SB. Replace any cracked sleeve with an airworthy sleeve before further flight. Within the next 100 hours TIS and thereafter at intervals not to exceed 275 hours TIS, remove the sleeve-to-blade-damper assembly in accordance with paragraph 2.B.2 of the SB, and inspect in accordance with paragraphs 2.B.2.1, 2.B.2.2, and 2.B.2.3 of the SB. Returning a sleeve to the manufacturer is not required by this AD. Replace any unairworthy part before further flight. (c) 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. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Regulations Group. (d) 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. (e) Removing the sleeve-to-blade damper assembly and inspecting the sleeve shall be done in accordance with the Accomplishment Instructions, paragraphs 2.B.1, 2.B.2, 2.B.2.1, 2.B.2.2, and 2.B.2.3, of Eurocopter Mandatory Service bulletin No. 05.00.53, Revision 1, dated July 6, 1999. 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. This information may be examined at the FAA, Office of the Regional Counsel, Southwest Region, Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. 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. (f) This amendment becomes effective on July 12, 2001. Note 3: The subject of this AD is addressed in Direction Générale de L'Aviation Civile (France) AD No. 1999-260-014(A) R1, dated July 13, 1999. Issued in Fort Worth, Texas, on June 8, 2001. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 01-15792 Filed 6-26-01; 8:45 am] BILLING CODE 4910-13-U