Airworthiness Directive · Amendment 39-18991 · Main rotor system
Airbus Helicopters
This AD applies to the following helicopters, certificated in any category:
(1) Model AS332L2 helicopters with a main rotor (M/R) blade attachment pin (attachment pin) part number (P/N) 332A31-2123-00 or P/N 332A31-2115-20 installed; and
(2) Model EC225LP helicopters with an attachment pin P/N 332A31-3204-20 installed.
We are adopting a new airworthiness directive (AD) for Airbus Helicopters (Airbus) Model AS332L2 and EC225LP helicopters. This AD requires inspections of the main rotor (M/R) blade attachment pins (attachment pins). This AD was prompted by a report of three cracked attachment pins. The actions of this AD are intended to detect and prevent an unsafe condition on these products.
You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(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.
