Wire Loom Chafing at Conduit Exits

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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/A320/23
Amdt 2
Wire Loom Chafing at Conduit Exits 2/95
Applicability: All A320 series aircraft without Airbus Industrie Modification 22109 or Airbus
Industrie Service Bulletin A320-24-1045 Revision 3 incorporated.
Requirement: 1. Inspect wires in wiring zone 574 and 674 in accordance Airbus Industrie Service
Bulletin A320-24-1044 Revision 2.
a. For any wire showing signs of chafing or overheating, repair or replace in
accordance with the aircraft Maintenance Manual or Aircraft Wiring Manual.
b. For any wire loom not correctly guided centrally into the conduit end fitting, realign
and protect the loom in accordance with Airbus Industrie Service Bulletin
A320-24-1045 Revision 1, or in accordance with the temporary repair defined
in Airbus Industrie SB A320-24-1044 Revision 2, paragraph 2.B(2)(b).
2. Inspect wires in wing and horizontal stabilizer (except in zones 574 and 674 - refer
Requirement 1) in accordance with Airbus Industrie Service Bulletin
A320-24-1044 Revision 2.
a. For any wire showing signs of chafing or overheating, repair or replace in
accordance with the aircraft Maintenance Manual or Aircraft Wiring Manual.
b. For any wire loom not correctly guided centrally into the conduit end fitting, realign
and protect the loom in accordance with Airbus Industrie SB
A320-24-1045 Revision 1, or in accordance with the temporary repair defined
in Airbus Industrie SB A320-24-1044 Revision 2, paragraph 2.B(6)(b).
3. Inspect wires in the main landing gear bays in accordance with Airbus Industrie
Service Bulletin A320-24-1044 Revision 3.
a. For any wire showing signs of chafing or overheating, repair or replace, before
the next flight, in accordance with the aircraft Maintenance Manual or Aircraft
Wiring Manual.
b. For any wire loom which is in contact with the edge of the conduit end fitting or
which may come in contact with the edge of the conduit end fitting during inflight
vibration, re-align and protect the loom, before the next flight, in
accordance with Airbus Industrie Service Bulletin A320-24-1045 Revision 3, or
in accordance with the temporary repair defined in Airbus Industrie SB
A320-24-1044 Revision 3, paragraph 2.B(6)(b).
Note: DGAC AD 91-182-020(B) R2 dated 7 December 1994 refers.
Compliance: The compliance for Requirements 1 and 2 remain unchanged as follows:
1 - Initially within 450 hours time in service after 26 December 1991 and
thereafter, at intervals not exceeding 450 hours time in service.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105
CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
2 - Initially within 1500 hours time in service after 26 December 1991 and
thereafter, at intervals not exceeding 3100 hours time in service.
Requirement 3:
Initially within 1500 hours time in service after 2 February 1995 and thereafter, at
intervals not exceeding 3500 hours time in service.
Compliance with Airbus Industrie SB A320-24-1045 Revision 3 constitutes
terminating action for Requirements 1, 2 and 3. Repeat inspections are only required
if temporary repairs are made in accordance with Airbus Industrie SB A320-24-1044
Revision 2 or 3 instead of permanent repairs in accordance with Airbus Industrie SB
A320-24-1045 Revision 1, 2 or 3 as appropriate.
This amendment becomes effective 2 February 1995.
Background: Compliance is necessary in order to prevent the risk of a short circuit of the engine
fire extinguisher bottle circuitry due to chafing of the wiring. Amendment 1 corrected
reference documentation data, included reference to the DGAC Airworthiness
Directive and aligned the title with that of the DGAC Directive. This amendment
adds the main landing gear area to the inspection requirements and contains minor
editorial changes.