AD 97-26-18 Airworthiness Directives; Eurocopter France Model SA-360C Helicopters

Models named: SA-360C. Read the applicability below — it usually turns on serial or part numbers too.

Model SA-360C helicopters with main gearbox (MGB), part number (P/N) 360A32-2000--all dash numbers, 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 (c) 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 fatigue cracking of the MGB bevel pinion, failure of the MGB, and a subsequent forced landing, accomplish the following: (a) Before further flight, and thereafter at intervals not to exceed 1,000 hours time-in-service (TIS), replace the MGB bevel pinion, P/N 360A32-1021-20, on MGBs that have accumulated 900 or more hours TIS since first installed on any helicopter or since the last MGB overhaul. (b) On or before the accumulation of 1,000 hours TIS, and thereafter at intervals not to exceed 1,000 hours TIS, replace the bevel pinion, P/N 360A32-1021-20, on MGBs that have accumulated less than 900 hours TIS since first installed on any helicopter or since the last MGB overhaul. This AD revises the Airworthiness Limitations section of the maintenance manual by establishing a new retirement life for the bevel pinion, P/N 360A32-1021-20, of 1,000 hours TIS. Note 2: Eurocopter France Mandatory Service Bulletin No. 01.35, dated January 14, 1997, contains additional information concerning the subject of this AD. (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, Rotorcraft Standards Staff, FAA, Rotorcraft Directorate. 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. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 [[Page 66508]] 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) This amendment becomes effective on January 5, 1998. Note 4: The subject of this AD is addressed in Direction Generale de L'Aviation Civile (France) AD 97-027-041(B), dated February 12, 1997. Issued in Fort Worth, Texas, on December 12, 1997. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 97-33145 Filed 12-18-97; 8:45 am] BILLING CODE 4910-13-P