Airworthiness Directive · Amendment 39-21319 · Emergency flotation section
Airbus Helicopters
This airworthiness directive (AD) applies to Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters with emergency flotation gear installed, certificated in any category, except those helicopters that have Airbus Helicopters Modification (MOD) 0728456 already installed.
The FAA is superseding Airworthiness Directive (AD) 2017-09-05 for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters. AD 2017-09-05 required repetitively checking screws in the emergency flotation gear. This new AD retains the requirements of AD 2017-09-05 but also requires installing a modification (MOD), which is a terminating action for the repetitive checks. This AD was prompted by the development of the MOD by Airbus Helicopters that addresses the unsafe condition. The actions of this AD are intended to address 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) Within 15 hours time-in-service (TIS), and before each flight over water thereafter, visually check each emergency flotation gear left hand (LH) and right hand (RH) rear upper fitting to determine whether the heads of the lower screws are present. Figure 1 to paragraph (f)(1) of this AD depicts where the lower three screws (noted as B and E) are located. Check each screw for looseness by determining whether it can be rotated by hand. These actions may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9(a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439.
(2) If a screw head is missing, or if a screw is loose, before further flight over water, install MOD 0728456 by completing paragraph (f)(3) of this AD.
(3) Within 300 hours TIS, unless required before further flight over water by paragraph (f)(2) of this AD, install MOD 0728456 by doing the following:
Note 1 to paragraph (f)(3): The installation of MOD 0728456 on the LH and RH sides is identical.
(i) Remove external fitting (a) and remove from service screws (c), (d) and (e), washers (f), and nuts (g) as shown in Figure 1, Detail A of Airbus Helicopters Alert Service Bulletin (ASB) No. AS332-25.03.43, Revision 0, dated April 4, 2018 (ASB AS332-25.03-43 Rev 0), or ASB No. EC225-25A207, Revision 0, dated April 4, 2018 (ASB EC225-25A207 Rev 0), as applicable to your model helicopter. As an option, you may use Airbus Helicopters ASB No. AS332-25.03.43 or ASB No. EC225-25A207, each Revision 2 and dated March 21, 2019 (ASB AS332-25.03-43 Rev 2 or ASB EC225-25A207 Rev 2), as applicable to your model helicopter, instead of ASB AS332-25.03-43 Rev 0 or ASB EC225-25A207 Rev 0.
(ii) Install base washers (1) (structural side), spherical washers (2) (screw side), and screws (3) and coat with sealing compound (or similar) on the smooth surface of the nuts (5) as shown in Figure 2 of ASB AS332-25.03-43 Rev 0 or ASB EC225-25A207 Rev 0, as applicable to your model helicopter. As an option, you may use ASB AS332-25.03-43 Rev 2 or ASB EC225-25A207 Rev 2, as applicable to your model helicopter, instead of ASB AS332-25.03-43 Rev 0 or ASB EC225-25A207 Rev 0.
(iii) Inspect each washer on the external fitting (a) for contact with a weld as shown in Figure 2, Detail A of ASB AS332-25.03-43 Rev 0 or ASB EC225-25A207 Rev 0, and inspect each washer on the internal fitting for contact with the fitting radius. As an option, you may use or ASB AS332-25.03-43 Rev 2 or ASB EC225-25A207 Rev 2, as applicable to your model helicopter, instead of ASB AS332-25.03-43 Rev 0 or ASB EC225-25A207 Rev 0.
(A) If a washer on the external fitting makes contact with a weld, perform a spotfacing to the diameter of 17mm (+ 0.1/− 0.1) with a cutter root radius of 0.5mm.
(B) If a washer on the internal fitting falls in the radius of the bracket, perform a spotfacing to the diameter of 17mm (+ 0.1/− 0.1) with a cutter root radius of 0.5mm.
(iv) Torque each nut to 169-203 lbf.in (1.9-2.3 daN.m), and apply sealing compound to outer edge of the LH rear upper fitting.
(4) Completion of the requirements in paragraph in (f)(3) of this AD constitutes terminating action for the repetitive checks required in paragraph (f)(1) of this AD.
