Airworthiness Directive · Amendment 39-16486 · Eurocopter Deutschland GmbH Model MBB-BK 117 C-2 Helicopters
Eurocopter Deutschland GmbH Model MBB-BK 117 C-2 Helicopters
This AD applies to Model MBB-BK 117 C-2 helicopters with a tail rotor control lever B642M1009103, installed, certificated in any category.
This amendment supersedes an existing airworthiness directive (AD) for the Eurocopter Deutschland GmbH (ECD) Model MBB BK 117 C-2 helicopters. This amendment results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states there was an in- flight incident in which a dynamic weight broke off the control lever leading to considerable vibrations. A visual inspection revealed that the threaded bolt of the control lever had broken off. The actions specified by this AD are intended to prevent separation of dynamic weights, severe vibration, and subsequent loss of control of the helicopter.
Before further flight, unless already done, mark the position of the weights, remove the split pins, remove the weights, and visually inspect the tail rotor control lever in the area around the split pin bore for score marks, notching, scratching, or a crack. Inspect by following the Accomplishment Instructions, paragraph 3.A.(1) through 3.A.(3) and Figure 1, of Eurocopter Alert Service Bulletin MBB BK 117 C-2-64A-002, Revision 2, dated August 6, 2007 (ASB).
(1) If done previously, within the next 8 hours time-in-service (TIS) or before reaching 25 hours TIS after the last inspection, and thereafter at intervals not to exceed 8 hours TIS, repeat the visual inspection of the tail rotor control lever as required by paragraph (e) of this AD.
(2) If you find a score mark, a notch, or a scratch that exceeds the maintenance manual limits, or find a crack, before further flight:
(i) Replace the tail rotor control lever with an airworthy tail rotor control lever; and
(ii) Reidentify the tail rotor head, head assembly, and drive system with the new part numbers by following the Accomplishment Instructions, paragraph 3.B.(1) through 3.B.(8) and 3.C.(1) through 3.C.(2), of the ASB.
(f) Within 100 hours TIS, unless already done, replace the control levers and reidentify the tail rotor head, head assembly, and drive system with the new part numbers by following the Accomplishment Instructions, paragraph 3.B.(1) through 3.B.(8) and 3.C.(1) through 3.C.(2), of the ASB.
(g) Replacing the control levers and reidentifying the part numbers is terminating action for the requirements of this AD.
We refer to flight hours as hours TIS. We do not refer to a date of October 31, 2007, for replacing the levers because the date has passed.
(i) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, ATTN: DOT/FAA Southwest Region, Sharon Miles, ASW-111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5122, fax (817) 222 5961, has the authority to approve AMOCs for this AD, if requested, using the procedures found in 14 CFR 39.19.
(j) Special flight permits are prohibited.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
