AD 2002-08-16 Airworthiness Directives; Eurocopter France Model SA341G, SA342J, and SA-360C Helicopters

Models named: SA341G, SA342J, SA-360C. Read the applicability below — it usually turns on serial or part numbers too.

Model SA341G, SA342J, and SA-360C helicopters with a main rotor head torsion tie bar (tie bar), part number (P/N): 341A31-4904-00, -01, -02, -03; 341A31-4933-00, -01; 360A31-1097-02, or -03, 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 (d) 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 prevent failure of a tie bar, loss of a main rotor blade, and subsequent loss of control of the aircraft, accomplish the following: (a) Before further flight, remove each tie bar, P/N 341A31-4904-00, -01, -02, or -03; or 360A31-1097-02 or -03, from service. (b) For each tie bar, P/N 341A31-4933-00 or -01: (1) Before further flight, determine the date of initial installation on any helicopter using the date of manufacture if the date of installation cannot be determined. (2) For each tie bar with 7 or more years time-in-service (TIS) since initial installation on any helicopter, remove within 5 hours TIS. (3) For each tie bar manufactured before 1995 with less than 7 years TIS since initial installation on any helicopter, remove before accumulating 7 years TIS, within 300 hours TIS, or within 1 year, whichever occurs first. (4) For each tie bar manufactured in 1995 or subsequent years with less than 7 years TIS since initial installation on any helicopter, remove before accumulating 7 years TIS, within 600 hours TIS, or within 2 years, whichever occurs first. Note 2: Eurocopter France (ECF) Alert Telex Nos. 01.29R1 and 01.39R1, both dated December 11, 2001, pertain to the subject of this AD. (c) This AD revises the limitations section of the maintenance manual by adding to the current life limit of 5000 hours TIS, the following additional alternative life limits for tie bars, P/N 341A31-4933-00 or 341A31-4933-01: (1) Seven years TIS from initial installation on any helicopter or (2) For tie bars manufactured before 1995, a life limit of 300 hours TIS or 1 year, or (3) For tie bars manufactured in 1995 or subsequent years, a life limit of 600 hours TIS or 2 years, whichever occurs first. (d) 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 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Regulations Group. (e) Special flight permits will not be issued. (f) This amendment becomes effective on May 8, 2002. Note 4: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) ADs 2001-587-041(A) R1 and 2001-588-047(A) R1, both dated December 26, 2001. Issued in Fort Worth, Texas, on April 11, 2002. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 02-9728 Filed 4-22-02; 8:45 am] BILLING CODE 4910-13-P