AD 2015-02-27 Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Helicopters

This AD supersedes AD 2013-19-19, Amendment 39-17601 (78 FR 60188, October 1, 2013).

(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.

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to James Blyn, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email james.blyn@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.

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 cracked shaft resulting in loss of MGB oil pressure. These actions are intended to prevent loss of the MGB lubrication system and subsequent loss of control of the helicopter.