AD 2022-24-12 Airworthiness Directives; Airbus Helicopters

Models named: EC225LP. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Helicopters Model EC225LP helicopters, certificated in any category, with a main rotor (M/R) rotating swashplate (swashplate) part number (P/N) 332A31-3074-00 or P/N 332A31-3074-01 installed.

Comply with this AD within the compliance times specified, unless already done.

Before further flight, review Appendix 4.A. of Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 05A051, Revision 4, dated February 28, 2022 (EASB 05A051 Rev 4) to determine the date of manufacture of the swashplate. (1) If the swashplate has accumulated 13 or more years since the date of manufacture, remove the swashplate from service. (2) If the swashplate has accumulated less than 13 years since the date of manufacture, create a component history card or equivalent record indicating a life limit of 13 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 any swashplate from service before accumulating 13 years since the date of manufacture. (3) For each swashplate that has accumulated 7 or more years, but less than 13 years, since the date of manufacture, within 15 hours time-in-service (TIS) or 7 days, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 15 hours TIS or 7 days, whichever occurs first, until the swashplate accumulates 13 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 05A051 Rev 4. If there is any crack on the yoke, before further flight, remove the swashplate from service. (i) If no cracks are visually detected, before further flight, visually inspect for a scratch and surface degradation on the yoke. (ii) If there is any scratch or surface degradation on the yoke, before further flight, perform a dye penetrant inspection of the yoke for a crack. (iii) If there is any crack on the yoke, before further flight, remove the swashplate from service. (4) For each swashplate that has accumulated 7 or more years, but less than 13 years, since the date of manufacture, within 100 hours TIS after the effective date of this AD: (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 Rev 4. 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 Rev 4. 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 Rev 4 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 the swashplate from service. (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 Rev 4. (A) If there is any crack on the yoke, before further flight, remove the swashplate from service. (B) If no cracks are visually detected, before further flight, perform the actions as required in paragraphs (g)(3)(i) through (iii) of this AD.

This AD was prompted by results of testing, which determined that a crack could develop in a swashplate control rod attachment yoke (yoke), and the notification of a new life limit for certain swashplates. The FAA is issuing this AD to detect and correct a crack in a yoke. The unsafe condition, if not addressed, could result in failure of the yoke, loss of M/R control, and subsequent loss of control of the helicopter.

This AD replaces AD 2020-23-05, Amendment 39-21321 (85 FR 73604, November 19, 2020).