Document ID: chunk:federal_register_of_legislation:F2007L01362:body:0:p3
Version: federal_register_of_legislation:F2007L01362
Segment Type: other
Provision Reference: 
Character Range: 5816–8232

be used in lieu of those listed in this AD.

             Note 4:  EASA AD 2007-0011 dated 9 January 2007 refers.  This AD supersedes DGAC AD F-2003-460.
Compliance:     1. Remains unchanged as 18 March 2004 (the effective date of Amendment 1 of this AD).

                  2. a. For each elevator servo control not yet dye penetrant inspected per Airbus All Operator Telex (AOT) A330-27A3115 Rev 01, prior to the accumulation of 1,000 FC since new or within 350 FC after 18 March 2004 the effective date of Amendment 1 of this AD, whichever occurs later.

                  For each elevator servo control already dye penetrant inspected as per Airbus AOT A330-27A3115 Rev 01, prior to the accumulation of 700 FC since the last dye penetrant inspection or prior to the accumulation of 1,350 FC since new, whichever occurs later.

                  2. b. At intervals not exceeding 350 FC.

                3. Before further flight after the effective date of this AD.

                4. From the effective date of this AD.

                5. Unless already accomplished, not later than 30 June 2008.

                6. Unless already accomplished, not later than 30 June 2008.
             This Amendment becomes effective on 7 June 2007.
Background:  Two cases have been reported of the elevator dropping to the full down position, without ECAM warning, while the flight crew was carrying out pre-flight controls check.  This occurred after hydraulic power-up and prior to engine start.  The cause has been identified as cracking of the elevator servo control mode selector valve position transducer body attachment lugs.  This resulted in displacement of the transducer, external hydraulic fluid leakage and subsequent loss of the corresponding hydraulic circuit.

             Amendment 1 of this AD introduced repetitive inspection of the transducer attachment and simplified the flight control check procedures.

             Amendment 2 mandates the replacement of the Mode Valve Transducer and excludes from the applicability aircraft fitted with P/N SC4800-113 or SC4800-114 or SC4800-xx4 servo controls.

             The original issue of this Directive became effective on 1 October 2003 and was based on DGAC Emergency AD U2003-371(B).

             Amendment 1 of this AD became effective on 18 March 2004.

David Punshon
Delegate of the Civil Aviation Safety Authority

24 April 2007