Airworthiness directives › 2015-25-04
AD 2015-25-04 Airworthiness Directives; Agusta S.p.A. Helicopters
Applicability*9
This AD becomes effective December 24, 2015.
Compliance
(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Martin R. Crane, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222-5110; email 9-ASW-FTW-AMOC-Requests@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
(1) AgustaWestland Bollettino Tecnico No. 109-149, dated May 29, 2015, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo; telephone 39-0331-664757; fax 39-0331-664680; or at http://www.agustawestland.com/technical-bulletins. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, Room 6N-321, 10101 Hillwood Pkwy, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2015-0097, dated June 1, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-2015-3783.
Unsafe condition
Within 25 hours time-in-service (TIS) and thereafter at intervals not to exceed 25 hours TIS, inspect the slider for play. If there is play greater than 2.3 millimeters (0.09 inch), replace the slider with an airworthy slider before further flight.
Affected ADs
This AD defines the unsafe condition as excessive wear and play on a slider. This condition could result in loss of tail rotor pitch control and consequently loss of helicopter control.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1