Airworthiness directives › 2015-05-52
AD 2015-05-52 Airworthiness Directives; Agusta S.p.A. Helicopters
Applicability*9
This AD becomes effective April 29, 2015 to all persons except those persons to whom it was made immediately effective by Emergency AD 2015-05-52, issued on March 4, 2015, which contains the requirements of this AD.
Compliance
(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Martin Crane, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email martin.r.crane@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) Emergency AD No. 2015-0035-E, dated February 27, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2015-0908.
Unsafe condition
(1) Before further flight, inspect the pitch link for freedom of movement while it is installed on the helicopter. (i) If there is rotation resistance or binding, before further flight, perform the actions in paragraphs (e)(2) through (e)(3) of this AD. (ii) If there is no rotation resistance and no binding, within 5 hours time-in-service, perform the actions in paragraphs (e)(2) through (e)(3) of this AD. (2) Remove the pitch link and inspect each pitch link spherical bearing for corrosion. If there is any corrosion, the pitch link is unairworthy. (3) Determine the force required to rotate each pitch link spherical bearing as depicted in Figure 1 of AgustaWestland Alert Bollettino Tecnico (BT) No. 109-145, 109EP-141, 109K-65, 109S-065, 109SP-087, or 119-072, all Revision A, and all dated February 27, 2015, as applicable to your model helicopter. (i) If the force required to rotate a spherical bearing in either end of the pitch link is greater than 7.30 N (1.64 pounds force), the pitch link is unairworthy. (ii) If the force required to rotate the spherical bearings in both ends of the pitch link is equal to or less than 7.30 N (1.64 pounds force), after cleaning the pitch link rod using aliphatic naphtha or equivalent and a soft non-metallic bristle brush, visually inspect the pitch link rod for a crack in the area depicted in Figure 1 of AgustaWestland Alert BT No. 109-145, 109EP-141, 109K-65, 109S-065, 109SP-087, or 119-072, all Revision A, and all dated February 27, 2015, as applicable to your model helicopter, using a 10x or higher power magnifying glass or by dye penetrant inspection. If there is a crack, the pitch link is unairworthy.
Affected ADs
This AD defines the unsafe condition as failure of a pitch link. This condition could result in loss of tail rotor pitch control and subsequent loss of control of the helicopter.
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