Document ID: chunk:federal_register_of_legislation:F2006B01913:body:0
Version: federal_register_of_legislation:F2006B01913
Segment Type: other
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Character Range: 0–1810

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 Airbus Industrie A319, A320 and A321 Series Aeroplanes

 AD/A320/22 Thrust Reverser/ECU Electrical Harness Assemblies 12/91

DM

             Applicability: 1. All A320 aircraft fitted with CFM56-5A engines and Electrical Harness Assemblies P/No 238W0908-511, 238W0904-509 and 238W0904-511.

             2. All Electrical Harness Assemblies P/No 238W0908-511, 238W0904-509 and 238W0904-511 held as spares.

             Requirement: 1. Action in accordance with Phase 1 of Airbus Industries All Operator Telex (AOT) 71-01.

             2. Action in accordance with Phase 2 of Airbus Industries All Operator Telex (AOT) 71-01.

Note: Rohr Industries Service Bulletin RA32071-63 also refers.

Compliance: 1. For installed harnesses - prior to 100 hours' Time in Service after 23 October 1991.
             For harnesses held as spares - prior to installation on an aircraft.

            2. For harness assemblies found during phase 1 to have moisture or corrosion present
             - prior to exceeding 600 hours' time in service after 23 October 1991.

             For harness assemblies found during phase 1 to have no moisture or corrosion present - within 3000 hours' time in service after 23 October 1991.

            Background: One operator of A320 aircraft equipped with CFM56-5A powerplants has reported an uncommanded engine power reduction to idle in flight which has been partly attributed to corrosion in the ECU electrical harness. Compliance with this AD requires an inspection of the thrust reverser and ECU harness assemblies, for corrosion and moisture ingress, and the installation of draining provisions in the harness chafe guards.