Airworthiness Directive · Amendment 39-16396 · Eurocopter France (Eurocopter) Model AS350B, BA, B1, B2, C, D, and D1 Helicopters and Model AS355E, F, F1, F2, and N Helicopters
Eurocopter France (Eurocopter) Model AS350B, BA, B1, B2, C, D, and D1 Helicopters and Model AS355E, F, F1, F2, and N Helicopters
Superseded. A later AD replaced this one: AD 2014-05-07. Comply with the one in force.
Model AS350B, BA, B1, B2, C, D, and D1 helicopters and Model AS355E, F, F1, F2, and N helicopters, with a tail gearbox (TGB) control lever, part number (P/N) 350A33-1058-00, P/N 350A33-1058-01, P/N 350A33-1058-02, or P/N 350A33-1058-03, that is not marked with an “X” near the P/N, installed, certificated in any category.
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2010-11-51, which was sent previously to all known U.S. owners and operators of the specified Eurocopter model helicopters by individual letters. This AD requires visually inspecting the tail gearbox (TGB) control lever for a crack. If a crack is found, this AD also requires replacing the cracked TGB control lever with an airworthy TGB control lever. Optional terminating actions for the inspection requirements of this AD can be done by either replacing a TGB control lever with an airworthy TGB control lever that is marked with an "X" near the part number or stripping the rework area and dye-penetrant inspecting that area for a crack, and if no crack is found, reworking and marking the TGB control lever. If a crack is found, removing and replacing the cracked TGB control lever with an airworthy TGB control lever is required. This AD is prompted by several reports of cracking in a TGB control lever. The actions specified by this AD are intended to prevent failure of the TGB control lever, loss of tail rotor control, and subsequent loss of control of the helicopter.
To detect cracking in a TGB control lever and prevent failure of the TGB control lever, loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following:
(a) Within 10 hours time-in-service (TIS), unless accomplished previously, and thereafter at intervals not to exceed 10 hours TIS, visually inspect the affected TGB control lever for cracking in accordance with the Accomplishment Instructions, paragraph 2.B.1.a., in Eurocopter Emergency Alert Service Bulletin (EASB) No. 05.00.62, Revision 1, dated April 23, 2010, for Model AS350 helicopters or EASB No. 05.00.57, Revision 1, dated April 23, 2010, for Model AS355 helicopters.
(b) If a crack is found, before further flight, remove and replace the cracked TGB control lever with an airworthy TGB control lever in accordance with the Accomplishment Instructions, paragraph 2.B.2., in the EASB appropriate for your model helicopter.
(c) Either of the following options constitutes a terminating action for the inspection requirements of this AD:
(1) Replace a TGB control lever with an airworthy TGB control lever that is marked with an “X” near the P/N; or
(2) Strip the rework area “B” as shown in Figure 4 of each EASB and perform a dye-penetrant inspection on that area for a crack. If no crack is found, rework and mark the TGB control lever in accordance with paragraph 2.B.3.b. of the EASB appropriate for your model helicopter, except you are not required to contact Eurocopter France. If a crack is found, before further flight, remove and replace the cracked TGB control lever with an airworthy TGB control lever in accordance with the Accomplishment Instructions, paragraph 2.B.2., in the EASB.
Note 1: One Eurocopter EASB contains four different service bulletin numbers but only portions of 2 EASBs are being incorporated.
Note 2: Installing a reinforced TGB control lever, P/N 350A33-1524-00 or P/N 350A33-1526-00, that does not need to be marked with an “X” constitutes compliance with paragraph (c) of this AD.
(d) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, FAA, ATTN: J.R. Holton, Jr., Aviation Safety Engineer, ASW-112, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-4964, fax (817) 222-5961, for information about previously approved alternative methods of compliance.
