AD 2025-23-07 Airworthiness Directives; Airbus Helicopters

Models named: AS 332L2, EC 225LP. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Helicopters, certificated in any category, identified in paragraphs (c)(1) and (2) of this AD. (1) Model AS 332L2 helicopters with a main gearbox (MGB) suspension bar front attachment bolt part number (P/N) 332A22-1613-20 or 332A22-1613-21, MGB suspension bar rear attachment bolt P/N 332A22-1614-20, MGB suspension bar front attachment fitting P/N 332A22-1623-01, MGB suspension bar rear left-hand attachment fitting P/N 332A22-1624-02 or 332A22-1624-04, or MGB suspension bar rear right-hand attachment fitting P/N 332A22-1624-03 or 332A22-1624-05 installed. (2) Model EC 225LP helicopters with MGB suspension bar front attachment bolt P/N 332A22-1613-21 or MGB suspension bar rear attachment bolt P/N 332A22-1614-20 installed. Note 1 to paragraph (c): Airbus Helicopters refers to MGB suspension bar attachment bolts as “pins.”

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

For helicopters identified in paragraphs (c)(1) and (2) of this AD without Airbus Helicopters modifications 0728521, 0728904, 0728496, and 0729044 installed, within 30 hours time-in-service (TIS) after the effective date of this AD, review records to determine the total hours TIS of each bolt. (1) Determine the life limit of each bolt by applying its total hours TIS by the add-on factor listed in Table No. 1 of Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 01.00.86, Revision 4, dated January 6, 2022 (EASB 01.00.86 Rev 4), or Airbus Helicopters EASB No. 04A013, Revision 4, dated January 6, 2022, as applicable to your model helicopter. (i) Before further flight, remove from service any bolt that has reached or exceeded its life limit, and remove its associated MGB suspension bar attachment nut (nut) and cotter pins from service. Remove the associated convex and concave washers. Thereafter, before each flight, continue to calculate and record the life limit of each bolt on its component history card or equivalent record by applying the add-on factor each time the helicopter accumulates hours TIS and remove from service any bolt before reaching its life limit, along with its associated nut and cotter pins. Remove its associated convex and concave washers. (ii) For each bolt that has not exceeded its life limit, before each flight, continue to calculate and record the life limit on its component history card or equivalent record by applying the add-on factor each time the helicopter accumulates hours TIS and remove from service any bolt before reaching its life limit, along with its associated nut and cotter pins. Remove the associated convex and concave washers. (2) Before further flight, if any nut, bolt, or cotter pin was removed from service as a result of the actions in paragraph (g)(1) of this AD, replace those parts with airworthy parts, and install new (never installed) convex and concave washers or reinstall the convex and concave washers that were removed (if washers are airworthy). Torque each newly-installed nut to the minimum allowable torque value of: 735-840 lbf. in (8.3 daN.m to 9.5 daN.m) on the front nuts of the fittings, and 496-566 lbf. in (5.6 daN.m to 6.4 daN.m) on the rear nuts of the fittings.

This AD was prompted by a report of torque loss on a MGB suspension bar attachment bolt (bolt). The FAA is issuing this AD to prevent MGB suspension bar attachment fittings (fitting) and bolts remaining in service beyond their fatigue life. The unsafe condition, if not addressed, could result in structural failure of an MGB attachment assembly, detachment of an MGB suspension bar, and consequent loss of control of the helicopter.

This AD replaces AD 2020-06-12, Amendment 39-19881 (85 FR 19077, April 6, 2020).