Airworthiness Directive · Amendment 39-11967 · Eurocopter France Model SA330F, G, and J Helicopters
Eurocopter France Model SA330F, G, and J Helicopters
Superseded. A later AD replaced this one: AD 2020-19-02. Comply with the one in force.
Model SA330F, G, and J helicopters with a tail rotor blade (blade), part number (P/N) 330A12-0000-(all dash numbers), 330A12-0000-(all dash numbers), 330A12-0006-(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 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 (b) 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.
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France Model SA330F, G, and J helicopters and requires inspecting the tail rotor blade (blade) skin for cracks and replacing, as necessary, the blade. This amendment requires skin bonding and eddy current inspections of the blade skin for cracks and would reference a more recent service bulletin (SB). This amendment is prompted by improved inspection methods and by the manufacturer revising the SB referenced in the current AD. The actions specified by this AD are intended to prevent fatigue cracking of a blade, failure of a blade, and subsequent loss of control of the helicopter.
To prevent fatigue cracking of a blade, failure of a blade, and subsequent loss of control of the helicopter, accomplish the following:
(a) Within 30 hours time-in-service (TIS), and thereafter at intervals not to exceed 15 hours TIS for blades equipped with deicing systems or 30 hours TIS for blades without deicing systems, conduct skin bonding and eddy current inspections on each affected blade for skin bonding and a crack. Inspect in accordance with paragraph 1.C of Aerospatiale Service Bulletin 05.71R4, dated December 18, 1990. Replace any blade failing the skin bonding inspection or eddy current inspection before further flight.
