Airworthiness Directive · Amendment 39-21642 · Main rotor head
Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) and Eurocopter France Helicopters
This AD applies to Airbus Helicopters (type certificate previously held by Eurocopter France) Model SA341G and SA342J and Eurocopter France Model SA-360C helicopters, certificated in any category, 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, -03; or 704A33-633-270, installed.
The FAA is superseding Airworthiness Directive (AD) 2002-08-16 for certain Eurocopter France SA341G, SA342J, and SA-360C helicopters. AD 2002-08-16 required removing certain main rotor head torsion tie bars (tie bars) from service and revising the limitations section of the existing maintenance manual for your helicopter by adding life limits for certain other tie bars. This AD was prompted by the determination that another part-numbered tie bar is affected by the same unsafe condition. This AD continues to require removing certain tie bars from service and establishing a life limit for certain other tie bars. The FAA is issuing this AD to address the unsafe condition on these products.
(1) For tie bar P/N 341A31-4904-00, -01, -02, and -03; and 360A31-1097-02 and -03, before further flight after May 8, 2002 (the effective date of AD 2002-08-16), remove the tie bar from service.
(2) For each tie bar P/N 341A31-4933-00 and -01:
(i) Before further flight after May 8, 2002 (the effective date of AD 2002-08-16), determine the date of initial installation on any helicopter, or if the date of initial installation cannot be determined, use the date of manufacture.
(A) For a tie bar that has accumulated 7 or more years since initial installation on any helicopter, within 5 hours time-in-service (TIS) after May 8, 2002 (the effective date of AD 2002-08-16), remove the tie bar from service.
(B) For a tie bar manufactured before 1995 that has accumulated less than 7 years since initial installation on any helicopter, before accumulating 7 years since initial installation on any helicopter, before accumulating 300 total hours TIS, or within 1 year after May 8, 2002 (the effective date of AD 2002-08-16), whichever occurs first, remove the tie bar from service.
(C) For a tie bar manufactured in 1995 or later that has accumulated less than 7 years since initial installation on any helicopter, before accumulating 7 years since initial installation on any helicopter, before accumulating 600 total hours TIS, or within 2 years after May 8, 2002 (the effective date of AD 2002-08-16), whichever occurs first, remove the tie bar from service.
(ii) Thereafter following paragraph (g)(2)(i) of this AD, remove any tie bar P/N 341A31-4933-00 and -01 from service as follows:
(A) For a tie bar manufactured before 1995, remove the tie bar from service before accumulating 300 total hours TIS or 1 year since initial installation on any helicopter, whichever occurs first, and
(B) For a tie bar manufactured in 1995 or later, remove the tie bar from service before accumulating 600 total hours TIS or 2 years since initial installation on any helicopter, whichever occurs first.
(3) For tie bar P/N 704A33-633-270:
(i) Before further flight after the effective date of this AD, determine the date of initial installation on any helicopter, or if the date of initial installation cannot be determined, use the date of manufacture.
(ii) If the tie bar has accumulated 600 or more total hours TIS or 2 or more years since initial installation on any helicopter, whichever occurs first, before further flight, remove the tie bar from service.
(iii) If the tie bar has accumulated less than 600 total hours TIS or 2 years since initial installation on any helicopter, whichever occurs first, remove the tie bar from service before accumulating 600 total hours TIS or 2 years since initial installation on any helicopter, whichever occurs first.
(iv) Thereafter following paragraph (g)(3)(ii) or (iii) of this AD, remove any tie bar P/N 704A33-633-270 from service before accumulating 600 total hours TIS or 2 years since initial installation on any helicopter, whichever occurs first.
(4) As of the effective date of this AD, do not install tie bar P/N 341A31-4904-00, -01, -02, or -03; or 360A31-1097-02 or -03, on any helicopter.
