Airworthiness Directive · Amendment 39-19881 · Main rotor gearbox
Airbus Helicopters
Superseded. A later AD replaced this one: AD 2025-23-07. Comply with the one in force.
This AD applies to Airbus Helicopters Model AS332L2 and EC225LP helicopters, certificated in any category, with a main gearbox (MGB) suspension bar front attachment bolt (bolt) part number (P/N) 332A22-1613-21 or 332A22-1613-20, MGB suspension bar rear bolt P/N 332A22-1614-20, MGB suspension bar front attachment fitting (fitting) P/N 332A22-1623-01, MGB suspension bar rear left hand fitting P/N 332A22-1624-02 or 332A22-1624-04, or MGB suspension bar rear right hand fitting P/N 332A22-1624-03 or 332A22-1624-05 installed.
The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332L2 and EC225LP helicopters. This AD requires determining the accumulated hours time-in-service (TIS) of certain part-numbered main gearbox (MGB) suspension bar attachment bolts and fittings, applying a life limit add-on factor, and inspecting the torque of certain MGB suspension bar attachment nuts. This AD was prompted by a report of torque loss on an MGB suspension bar bolt. 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 30 hours time-in-service (TIS), review records to determine the total hours TIS of each MGB suspension bar bolt.
(i) Determine the life limit of each bolt by applying the hours TIS by the add-on factor listed in Table No. 1 of Airbus Helicopters Emergency Alert Service Bulletin No. 01.00.86, Revision 1, dated August 25, 2017 (EASB 01.00.86), or Airbus Helicopters Emergency Alert Service Bulletin No. 04A013, Revision 1, dated August 25, 2017, as applicable to your model helicopter.
Note 1 to paragraph (e)(1)(i) of this AD: Airbus Helicopters refers to bolts as “pins.”
(A) Before further flight, remove from service any bolt that has reached or exceeded its life limit.
(B) For each bolt that has not exceeded its life limit, 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.
(ii) Thereafter following paragraph (e)(1)(i) of this AD, 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.
(2) For Model AS332L2 helicopters, within 30 hours TIS, review records to determine the total hours TIS of each MGB suspension bar fitting.
(i) Determine the life limit of each fitting by applying the hours TIS by the add-on factor listed in Table No. 1 of EASB 01.00.86.
(A) Before further flight, remove from service any fitting that has reached or exceeded its life limit.
(B) For each fitting that has not exceeded its life limit, 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 fitting before reaching its life limit.
(ii) Thereafter following paragraph (e)(2)(i) of this AD, continue to calculate and record the life limit of each fitting 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 fitting before reaching its life limit.
(3) For Model AS332L2 helicopters, within 150 hours TIS (without the add-on factor), inspect the torque of each MGB suspension bar attachment front and rear nut. The allowable torque for each front nut is 602-663 lbf. in (6.8-7.5 daN.m) and the allowable torque for each rear nut is 337-398 lbf. in (3.8-4.5 daN.m).
(i) If the torque on any nut is higher than the maximum allowable torque stated in paragraph (e)(3) of this AD, before further flight, remove from service the bolt and nut.
(ii) If the torque on any nut is lower than the minimum allowable torque value stated in paragraph (e)(3) of this AD, before further flight, tighten the nut to the allowable torque stated in paragraph (e)(3) of this AD. Within 150 hours TIS (without the add-on factor), remove from service any bolt and nut that were tightened as required by this paragraph.
