Document ID: chunk:federal_register_of_legislation:F2007L01505:body:0:p2
Version: federal_register_of_legislation:F2007L01505
Segment Type: other
Provision Reference: 
Character Range: 2922–4586

any EUROCOPTER AS 350 helicopter unless they have been previously returned to conformity by the equipment manufacturer as indicated in paragraph 2. of EUROCOPTER ASB No. 01.00.58 Revision 1 or later NAA approved revision.

             Note:  EASA Emergency AD 2007-0141-E dated 21May 2007 refers.
Compliance:     1. Before further flight, after the effective date of this AD.

                  2. a. During each pre-flight test (see Rotorcraft Flight Manual section 4) and until accomplishment of requirement 2c of this AD is completed.

                  b. Before further flight, after the effective date of this AD.

                  c. Within the next 50 Flight Hours or 4 months after the effective date of this AD, whichever occurs first.

                3. After the effective date of this AD.
             This Airworthiness Directive becomes effective on 25 May 2007.
Background:  An internal review revealed that some main and tail rotor servo-controls do not conform to the approved design.  This results in a greater play in the input lever bearing which could lead to off-centered lever/distributor slide valve.  If not corrected, this condition could jam the distributor slide valve in its sleeve contributing to reduced controllability of the rotors.  Such a jamming would be detected during the pre-flight hydraulic check by a "hard point" in the flight controls.  This Airworthiness Directive requires identification of the affected main and tail rotor servo-controls and mandates additional attention during the pre flight check and subsequent replacement.

Charles Lenarcic
Delegate of the Civil Aviation Safety Authority

22 May 2007