A. Preparation for Installation
(1)
Clean the component interface and/or the adjacent area.
(2)
Clean the attachment hardware with CLEANING AGENTS (Material No. 11-004A) and dry with filtered compressed air.
(3)
Apply a light coat of SPECIAL MATERIALS (Material No. 05-047) to the threads of all the screws.
Subtask 32-51-51-420-054
B. Installation of the Electro-Distributor
(1)
Remove blanking caps from the electrical connectors (4) and (11).
(2)
Make sure that the electrical connectors (4) and (11) are in the correct condition.
(3)
Install the new packing (7) and packing (10).
(4)
Install the new packing (8) and packing (9) with their thrust ring.
(5)
Put the electro-distributor (5) in position with the screws (6).
1EFF : ALL 1 32-51-51Page 429 1 1 Aug 01/05 1 1 1CES 1
(6)
Push the electro-distributor (5) to connect the electrical connector (4).
(7)
Make sure that the seals (7), (8), (9) and (10) are in the correct condition.
(8)
TORQUE the screws (6) to between 0.4 and 0.5 m.daN (35.39 and 44.24 lbf.in).
(9)
Safety the screws (6) with lockwire corrosion resistant steel dia 0.8 mm (0.03 in.).
(10) Apply SEALANTS (Material No. 09-001) to the heads of the screws (6). Subtask 32-51-51-865-058
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1GG, 2GG, 3GG, 4GG
Subtask 32-51-51-720-052
D. Functional Test
(1) Do the functional test of the nose wheel steering (Ref. TASK 32-51-00-720-003) or (Ref. TASK 32-51-00-720-004).
5. Close-up
________ Subtask 32-51-51-860-058
A. Put the aircraft back to its initial configuration.
(1)
Remove the container.
(2)
Remove the safety barriers.
(3)
Remove the warning notice(s).
(4)
Make sure that the work area is clean and clear of tool(s) and other items.
1EFF : ALL 1 32-51-51Page 430 1 1 Aug 01/05 1 1 1CES 1 POSITION AND WARNING - DESCRIPTION AND OPERATION
________________________________________________
1. General
_______
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
(Ref. Fig. 001, 002)
The Position and Warning sub-system has two parts which are:
-Indicating and Warning (Ref. 32-61-00)
-L/G Built-in Test Equipment (BITE) (Ref. 32-69-00).
**ON A/C ALL
A. Indicating and Warning
The proximity sensors on the L/G and L/G doors give position data to the two Landing Gear Control and Interface Units (LGCIUs) (Ref. 32-31-00). There are two sets of proximity sensors. The sensors in System 1 supply data to LGCIU 1 and the sensors in System 2 supply data to LGCIU 2. Each LGCIU sends the position data to the Electronic Instrument System (EIS) (Ref. 31-60-00). The EIS includes the Engine/Warning Display (EWD) (Ref. 31-66-00) and the System Display (SD). Together these make the Electronic Centralized Aircraft Monitoring (ECAM).
The position of each L/G and L/G door shows on the WHEEL page of the SD. If specified failures (or incorrect L/G configurations) occur, the E/WD gives a warning or caution message. Also, the Master Warning, or Caution lights, come on and an aural warning operates (Ref. 31-50-00).
The downlock indicator lights also show the position of each L/G (but not the L/G doors). The downlock indicator lights for the MLG and NLG are independently supplied through LGCIU 1.
Position information is described in Landing Gear Position Information (Ref. 32-62-00).
The LGCIU's supply L/G position data to other aircraft systems. Two types of data are given. These are:
-discrete logic signals
-ARINC 429 data.
The discrete outputs are sent when the L/G is in specified positions
(e.g. L/G locked down). ARINC 429 data is sent all the time when an LGCIU is in operation.
2. Component Location
__________________
Not applicable
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