AD 2020-23-05 Airworthiness Directives; Airbus Helicopters

This AD replaces AD 2018-08-01, Amendment 39-19254 (83 FR 17617, April 23, 2018).

Before further flight, review Appendix 4.A. of Airbus Helicopters Emergency Alert Service Bulletin No. 05A051, Revision 2, dated February 26, 2019 (EASB 05A051) to determine the date of manufacture of the swashplate. (1) If the swashplate has accumulated 12 or more years since the date of manufacture, remove from service the swashplate. (2) If the swashplate has accumulated less than 12 years since the date of manufacture, create a component history card or equivalent record indicating a life limit of 12 years since the date of manufacture. Thereafter, continue to record the life limit of the swashplate on its component history card or equivalent record and remove from service any swashplate before accumulating 12 years since the date of manufacture. (3) For each swashplate that has accumulated less than 7 years since the date of manufacture, within 15 hours time-in-service (TIS) and thereafter at intervals not to exceed 15 hours TIS, until the swashplate accumulates 7 years since the date of manufacture, visually inspect each yoke for a crack, paying particular attention to the areas shown in Details B, C, and D of Figure 1 of EASB 05A05. (i) If there are no cracks, perform a dye penetrant inspection of the yoke for a crack. (ii) If there is a crack on a yoke, before further flight, remove from service the swashplate. (4) For each swashplate that has accumulated 7 or more years, but less than 12 years, since the date of manufacture, within 100 hours TIS: (i) Remove the grease from areas (E), (F), (G), (H), (J), and (K) of each yoke as shown in Details B, C, and D of Figure 1 of EASB 05A051. Using a plastic spatula, strip areas (E), (F), (G), (H), (J), and (K) of each yoke as shown in Details B, C, and D of Figure 1 of EASB 05A051. Do not use a metal tool to strip any area of a yoke. (ii) Inspect areas (E), (F), (G), (H), (J) and (K) of each yoke as shown in Details B, C, and D of Figure 1 of EASB 05A051 for corrosion, pitting, and loss of material. (A) If there is any corrosion less than 0.0078 in. (0.2 mm), before further flight, remove the corrosion and apply varnish (Vernelec 43022 or equivalent) to the surface of areas (E), (F), (G), (H), (J) and (K). (B) If there is any pitting or loss of material of less than 0.0078 in. (0.2 mm), before further flight, remove the damage by sanding with sandpaper 200/400 or 330. (C) If there is any corrosion, pitting, or loss of material of 0.0078 in. (0.2 mm) or greater, before further flight, remove from service the swashplate. (iii) Visually inspect each yoke for a crack, paying particular attention to the areas shown in Details B, C, and D of Figure 1 of EASB 05A051. (A) If there are no cracks, perform a dye penetrant inspection of the yoke for a crack. (B) If there is a crack on a yoke, before further flight, remove from service the swashplate.

If you performed the actions in paragraph (f)(4) of this AD before the effective date of this AD using Airbus Helicopters Emergency Alert Service Bulletin No. 05A051, Revision 1, dated November 16, 2017, you met the requirements of paragraph (f)(4) of this AD.

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.

This AD defines the unsafe condition as a crack in a swashplate control rod attachment yoke (yoke). This condition could result in failure of the yoke, loss of M/R control, and subsequent loss of control of the helicopter.