Airworthiness directives › 2014-23-02
AD 2014-23-02 Airworthiness Directives; Agusta S.p.A. Helicopters (Type Certificate Currently Held by AgustaWestland S.p.A.) (Agusta)
Applicability*9
This AD becomes effective December 26, 2014.
Compliance
(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email rao.edupuganti@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 (EASA) AD No. 2013-0118, dated June 3, 2013. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0472.
Unsafe condition
(1) For main transmissions with 2,400 or more hours time-in-service (TIS), within 200 hours TIS and thereafter at intervals not exceeding 1,600 hours TIS, magnetic particle inspect the Gleason crown, P/N 109-0403-07-103, for a crack by following the procedures in: (i) Annex 1 of Agusta Bollettino Tecnico (BT) No. 109EP-128, Revision A, dated May 28, 2013, for Model A109E helicopters; (ii) Annex 1 of Agusta BT No. 109K-57, Revision A, dated May 28, 2013, for Model A109K2 helicopters; or (iii) Annex 1 of Agusta BT No. 119-058, Revision A, dated May 28, 2013, for Model A119 and AW119MKII helicopters. (2) If there is a crack, before further flight, replace the Gleason crown assembly with a Gleason Crown assembly, P/N 109-0401-27-107. Replacing the Gleason crown assembly with P/N 109-0401-27-107 is terminating action for the inspection requirements of this AD. (3) After the effective date of this AD, do not install a Gleason crown, P/N 109-0403-07-103, or a Gleason crown assembly, P/N 109-0401-27-101 or P/N 109-0401-27-109, on any helicopter.
Affected ADs
This AD defines the unsafe condition as a crack in a Gleason crown. This condition could cause damage to or loss of the main rotor drive and subsequent loss of control of the helicopter.
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