Document ID: chunk:federal_register_of_legislation:F2006B01864:body:0:p2
Version: federal_register_of_legislation:F2006B01864
Segment Type: other
Provision Reference: 
Character Range: 2872–5283

a positive means).

            Note 1: If the Requirement 2.b. option is adopted, the aircraft may be dispatched in accordance with an approved MEL (based on associated DGAC MMEL 28-21).

             3.    If a circuit breaker is collared opened in accordance with Requirement 2.b. carry out the Requirement 2.a. inspection.

             4.    If any damage is detected during the Requirement 2.a. inspections submit a report to Airbus Industrie including the following details:

                1. description of the damage found,

                2. aeroplane serial number,

                3. total number of landings,

                4. total time in service (hours), and

                5. details of the last maintenance actions performed on the fuel boost pump and/or fairing.

             1.  Modify the engine feed pump electrical harness and underwing fairings in accordance with SB A320-28-1093 and remove the AFM amendment introduced by Requirement 1.

            Note 2: DGAC AD 2002-221(B) refers.

            Compliance: For Requirement 1 - Remains unchanged as 'Within ten days after the effective date of the original issue of this Directive'.

            For Requirement 2 - Before further flight unless SB A320-28-1093 has been incorporated in accordance with Requirement 5.

            For Requirement 3 - Within ten days of the circuit breaker being collared open in accordance with Requirement 2.b.

            For Requirement 4 - Within ten days after accomplishing the Requirement 2.a. inspection.

            For Requirement 5 - Before 30 April 2004.

            This Amendment becomes effective on 13 June 2002.

            Background: The original issue of this Directive superseded AD/A320/111, clarified the inspection requirements and allowed despatch of the aircraft with wing fuel tank pumps rendered inoperable. AD/A320/111 was issued to limit the risk of electrical arcing between the wing fuel tank boost pump wiring and the wing structural skin by the introduction of an AFM limitation.

            This Amendment introduces terminating action for Requirements 1 and 2.

            The original issue of this Airworthiness Directive became effective on 28 February 2001.

 James Coyne
 Delegate of the Civil Aviation Safety Authority 3 May 2002

 The above AD is notified in the Commonwealth of Australia Gazette on 22 May 2002.