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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.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105
CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Page 1 of 4
AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes
Airworthiness Directive (AD) AD/A320/187 and issues the following AD under subregulation 39.001(1) of CASR 1998. The AD requires that the action set out in
the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product
mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the
requirement section; and (c) at the time mentioned in the compliance section.
Airbus Industrie A319, A320 and A321 Series Aeroplanes
AD/A320/187
Amdt 1
Nose Landing Gear Steering 4/2007
Applicability: AIRBUS A318, A319, A320 and A321 aircraft that are equipped with an EMM
Braking and Steering Control Unit (BSCU) part number (PN) E21327001 (Standard
L4.1, AIRBUS Modification 26965 - Service Bulletin A320-32-1912) or PN
E21327003 (Standard L4.5, AIRBUS Modification 33376 - Service Bulletin
A320-32-1261).
This Airworthiness Directive (AD) is not applicable to aircraft that have been
delivered and equipped with BSCU standard L4.8 from production incorporating
modification 35216( installation of EMM BSCU PN E21327004) or non EM BSCU.
Requirement: 1. The following operational procedure is only for those aircraft that have not
incorporated AIRBUS modification 31152 in production (i.e. applicable only to
aircraft with the steering powered by the green hydraulic system).
Incorporate the following or AFM TR 4.02.00/33 for aircraft without FWC
H2E3P or H1E3P or subsequent standard, or TR 4.02.00/34 for aircraft with
FWC H2E3P or H1E3P into the Aircraft Operations Manual as well as the
Aircraft Flight Manual.
The ECAM message, in case of a nose wheel steering failure, will be worded as
follows:
- “WHEEL N/W STRG FAULT” for aircraft with FWC software post E3P
　
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