Airworthiness directives › 2012-11-12
AD 2012-11-12 Airworthiness Directives; AGUSTA S.p.A. Helicopters
Applicability*9
This AD becomes effective July 3, 2012.
Compliance
(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Sharon Miles, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222-5110; email sharon.y.miles@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.
Required actions
The subject of this AD is addressed in European Aviation Safety Agency AD No. 2011-0226-E, dated December 2, 2011.
Unsafe condition
(1) Within 5 hours time-in-service (TIS) or 7 days, whichever occurs earlier, inspect the connection between the collective control rod C2 and the torque tube C3 for proper installation of the: bolt, part number (P/N) NAS6604D15; washer under the bolt head, P/N A160A0432K; self-locking nut, P/N MS17825-4; washer under the self-locking nut, P/N NAS1149D0432K; and the cotter pin, P/N MS24655-136, as depicted in Figures 1 and 2, of Agusta Bollettino Tecnico No. 139-275, dated December 1, 2011, (ABT 139-275). (2) If the connection between the collective control rod C2 and the torque tube C3 is not as depicted in Figures 1 and 2 of ABT 139-275, before further flight, properly connect control rod C2 to torque tube C3. In order to obtain the correct bolt grip length and cotter pin installation, you may use a maximum of 2 washers, P/N NAS1149D0432K, under the self-locking nut.
Affected ADs
This AD defines the unsafe condition as an incorrectly installed collective control rod, which could result in detachment of the collective control rod, resulting in subsequent loss of control of the helicopter.
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