AD 2001-19-51 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 the following main rotor head torsion tie bar (tie bar), part number (P/N):  341A31-4904-00, -01, -02, -03;  341A31-4933-00, -01; or  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 before further flight, 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) Remove each tie bar, P/N 341A31-4904-00, -01, -02, or -03; 360A31-1097-02 or -03, from service and replace with an airworthy tie bar, P/N 341A31-4933-00 or 341A31-4933-01. Note 2: Eurocopter France Telex Alert Nos. 01.28 and 01.38, both dated August 7, 2001, pertain to the subject of this AD. (b) Replace each tie bar, P/N 341A31-4933-00 or 341A31-4933-01, if 20 or more years have elapsed since initial installation on any helicopter, with an airworthy tie bar, P/N 341A31-4933-00 or 341A31-4933-01. If the date of initial installation on any helicopter cannot be determined, use the date of manufacture of the tie bar as the date of initial installation. (c) This AD revises the limitations section of the maintenance manual by adding a life limit for tie bars, P/N 341A31-4933-00 and 341A31-4933-01, of 20 years from initial installation on any helicopter and retains the existing 5,000 hours time-in-service (TIS) life limit on those tie bars. Tie bars, P/N 341A31-4933-00 and 341A31-4933-01, are to be removed from service when either the years or hours TIS life limit is reached, whichever occurs first. Tie bars, P/N 341A31-4904-00, -01, -02, and -03, and 360A31-1097-02 and -03, are not approved for installation on any helicopter. (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 December 10, 2001, to all persons except those persons to whom it was made immediately effective by Emergency AD 2001-19-51, issued September 21, 2001, 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's 2001-374-040(A) and 2001-375-046(A), both dated August 22, 2001. Issued in Fort Worth, Texas, on November 9, 2001. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 01-29189 Filed 11-21-01; 8:45 am] BILLING CODE 4910-13-U