AD 2017-17-01 Airworthiness Directives; Airbus Helicopters

This AD becomes effective September 25, 2017.

(1) The Manager, Safety Management Section, FAA, may approve AMOCs for this AD. Send your proposal to: David Hatfield, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5116; 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.

The subject of this AD is addressed in European Aviation Safety Agency (EASA) No. 2015-0016, dated January 30, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2017-0419.

(1) For Model AS332L2 helicopters, within 410 hours time-in-service (TIS), and for Model EC225LP helicopters within 660 hours TIS, remove each attachment pin and inspect the protective coating on the inside of the attachment pin for scratches and missing protective coating. (i) If there is a scratch or any missing protective coating, sand the attachment pin to remove the varnish in the area depicted as “Area A” in Figure 1 of Airbus Helicopters Alert Service Bulletin (ASB) No. AS332-05.00.99, Revision 0, dated December 22, 2014 (AS332-05.00.99), or Airbus Helicopters ASB No. EC225-05A040, Revision 0, dated December 22, 2014 (EC225-05A040), as applicable to your model helicopter. (ii) Using a 10X or higher power magnifying glass, inspect for corrosion and pitting at the chamfer. An example of pitting is shown in the Accomplishment Instructions, paragraph 3.B.3., Note 1, of AS332-05.00.99, and paragraph 3.B.2., Note 1, of EC225-05A040. If there is any corrosion, remove the corrosion. If there is any pitting, replace the attachment pin. Do not sand the attachment pin to remove a corrosion pit. (iii) Using a 10X or higher power magnifying glass, inspect the inside and outside of the attachment pin for a crack in the areas depicted as “Area A” and “Area B” in Figure 1 of AS332-05.00.99 or EC225-05A040, as applicable to your model helicopter. Pay particular attention to the chamfer in “Area A.” If there is a crack, remove the attachment pin from service. (2) Thereafter, for Model AS332L2 helicopters, at intervals not to exceed 825 hours TIS or 26 months, whichever occurs first; and for Model EC225LP helicopters, at intervals not to exceed 1,320 hours TIS or 26 months, whichever occurs first; perform the actions specified in paragraph (e)(1) of this AD. Corrosion may be removed from an attachment pin as specified in paragraph (e)(1)(ii) of this AD a maximum of four times. If there is a fifth occurrence of corrosion on an attachment pin, before further flight, remove the attachment pin from service. (3) Do not install an attachment pin P/N 332A31-2123-00, P/N 332A31-2115-20, or P/N 332A31-3204-20 on any helicopter unless you have complied with the actions in paragraph (e)(1) of this AD.

This AD defines the unsafe condition as corrosion or a crack in an attachment pin. This condition could result in loss of an M/R blade and subsequent loss of control of the helicopter.