Airworthiness Directive · Amendment 39-15357 · Eurocopter Deutschland GmbH Model EC135 Helicopters
Eurocopter Deutschland GmbH Model EC135 Helicopters
Superseded. A later AD replaced this one: AD 2020-26-03. Comply with the one in force.
Model EC135 helicopters, serial number (S/N) 0005 up to and including S/N 0444, except S/N 0028, and with tail rotor control rod (control rod), part number L672M2005207, installed, certificated in any category.
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2007-26-51, which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland GmbH (Eurocopter) Model EC135 helicopters by individual letters. This AD requires, within 5 hours time-in-service (TIS), inspecting the tail rotor control rod (control rod) and adjoining ball pivot and replacing any unairworthy parts before further flight. This amendment is prompted by a report of a fatal accident involving the failure of a control rod. The actions specified by this AD are intended to prevent failure of a control rod and subsequent loss of control of the helicopter.
Required as indicated, unless accomplished previously.
To prevent the failure of a control rod and subsequent loss of control of the helicopter, do the following:
(a) Within 5 hours time-in-service (TIS), inspect the control rod, shown in item 7, Figure 1, of this AD, with the parts identified in parenthesis as follows:
(1) Pull the control rod (7) until it reaches its stop position. Inspect attachment hardware of control rod (7) for a tight fit. Manually inspect for possible relative motion between control rod (7) and yaw actuator (8).
(2) Inspect the locking plate (9) for a tight fit.
(3) Visually inspect the attachment hardware between control rod (7) and yaw actuator (8) for play or thread exposure. If play or thread exposure is found, before further flight, replace the control rod with an airworthy control rod.
(b) Inspect the ball pivot as shown in item 11, Figure 1, of this AD by removing the tail rotor drive shaft fairing and inspecting for a loose bearing or play. If a loose bearing or play is found, before further flight, replace the ball pivot with an airworthy ball pivot.
Note 1: Eurocopter Alert Service Bulletin No. EC135-67A-017, dated December 13, 2007, pertains to the subject of this AD.
(c) 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: Chinh Vuong, Rotorcraft Directorate, Fort Worth, Texas 76193-0111, telephone (817) 222-5116, fax (817) 222-5961, for information about previously approved alternative methods of compliance.
Note 2: The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2007-0301-E, dated December 13, 2007.
(d) This amendment becomes effective on February 19, 2008, to all persons except those persons to whom it was made immediately effective by Emergency AD No. 2007-26-51, issued December 14, 2007, which contained the requirements of this amendment.
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.
