Airworthiness Directive · Amendment 39-18096 · Main rotor gearbox
Airbus Helicopters (Previously Eurocopter France) Helicopters
This AD applies to Airbus Helicopters Model AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters with a main gearbox (MGB) bevel gear vertical shaft (shaft), part number (P/N) 332A32-5101-00, 332A32-5101-05, 332A32-5101-10, or 332A32-5101-15, certificated in any category.
We are superseding Airworthiness Directive (AD) 2013-19-19 for certain Eurocopter France Model AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters. AD 2013-19-19 required replacing certain serial- numbered main gearbox (MGB) bevel gear vertical shafts and inspecting and replacing, if necessary, each MGB bevel gear vertical shaft (shaft). This new AD requires the same actions as AD 2013-19-19 but corrects an error in the term used to identify an inspection qualification and updates the type certificate holder's name. This AD is prompted by two incidents of emergency ditching after warning indications of loss of MGB oil pressure. These actions are intended to detect a cracked shaft, which could result in loss of MGB oil pressure, loss of the MGB lubrication system, and subsequent loss of control of the helicopter.
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) Before further flight, remove shaft, P/N 332A32-5101-00, 332A32-5101-05, 332A32-5101-10, or 332A32-5101-15, with S/N M330 through M340 (inclusive) and S/N M370 through M5000 (inclusive) from service, which are no longer considered airworthy.
(2) For Model AS332C, AS332L, AS332L1, and AS332L2 helicopters, before further flight and thereafter at intervals not to exceed 10 hours time-in-service (TIS), eddy current inspect the shaft for a crack in the area of the weld, which must be done by a Level II or Level III inspector certified in the eddy current fault detection method in the Aeronautics Sector according to the EN4179 or NAS410 standard.
(3) For Model EC225LP helicopters, either do paragraphs (3)(i) and (3)(ii) or do paragraph (3)(iii).
(i) Before further flight, install a placard in full view of the pilot with the following statement in red, 6 millimeter letters on a white background: “MAXIMUM CONTINUOUS TORQUE LIMITED TO 70% DURING LEVEL FLIGHTS AT IAS EQUAL TO OR MORE THAN 60 KTS,” and
(ii) Before further flight and thereafter at intervals not to exceed 11.5 hours TIS, remove the main jet and emergency spraying jet, and ultrasonic inspect the shaft in the weld area for a crack, which must be done by a Level II or Level III inspector certified in the ultrasonic fault detection method in the Aeronautics Sector according to the EN4179 or NAS410 standard, or
(iii) Before further flight, and thereafter at intervals not to exceed 8 hours TIS, remove the main jet and emergency spraying jet, and ultrasonic inspect the shaft for a crack in the area of the weld, which must be done by a Level II or Level III operator certified in the ultrasonic fault detection method in the Aeronautics Sector according to the EN4179 or NAS410 standard.
(4) If there is a crack, before further flight, replace the shaft with an airworthy part.
