(g)
Temporarily install the connector (34) with the washer (31) and the nut (32).
(h)
Temporarily install the anti-rotation plate (44) with the bolts
(43)
and the nuts (45).
(i)
Attach applicable lengths of string to each of the ends of the disconnected harness 13QT1(13QT2). This will help to install the new harness.
(j)
Put tape around each of the ends of the disconnected harness 13QT1(13QT2). This will help to let it move more easily through the conduit.
(8)
Remove the harness 13QT1 (13QT2) from between RIB 6 and RIB 7 as follows:
(a)
Get access through the opening 540BB(640BB).
(b)
Carefully pull the harness 13QT1(13QT2) from the inboard part of the conduit until the ends attached to the string comes into view.
(c)
Carefully pull the harness 13QT1(13QT2) from the outboard part of the conduit until the ends attached to the string come into view.
R 1EFF : 001-049, 051-099, 101-105, 151-199, 1 28-42-43Page 413 1201-228, 1May 01/05 1 1 1CES 1
(d)
Carefully pull the full harness 13QT1(13QT2) and the connector 4039VC1(4039VC2) until all the string is in view.
(e)
Identify and mark the string. This will help to install the new harness 13QT1(13QT2).
(f)
Remove and discard the tape from the harness 13QT1(13QT2) and remove the harness from the string.
(g)
Remove the harness 13QT1(13QT2) from the aircraft.
(h)
Leave the string in position for the installation.
R **ON A/C 106-149, 229-299, 401-499,
Subtask 28-42-43-020-091-A
A. Remove the Wing-Tank Inner-Cell Group A Harness 13QT1 (13QT2)
(Ref. Fig. 403A/TASK 28-42-43-991-006-A)
WARNING : CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE
_______
LOCKWIRE CAN CUT OR BLIND YOU.
(1) Remove the harness 13QT1 (13QT2) at RIB 1 and RIB 2 as follows:
(a) Get access through the opening 540AB(640AB) and the access door 540AZ(640AZ) to:
-
the fuel probes 21QT1(21QT2), 23QT1(23QT2) and 25QT1(25QT2)
-
the fuel sensors 16QJ1(16QJ2), 29QJ1(29QJ2) and 38QJ1(38QJ2)
-
the sensor cadensicon 19QT1(19QT2).
(b)
Disconnect the terminal connectors (2) from the terminal block of the fuel probes 21QT1(21QT2), 23QT1(23QT2) and 25QT1(25QT2) and the sensor cadensicon 19QT1(19QT2).
(c)
Remove and discard the terminal connectors (2) from the ends of the harness.
(d)
Loosen the clamp screws (21), the connector screws (20) and remove the cables from the fuel sensors 16QJ1(16QJ2), 29QJ1(29QJ2) and 38QJ1(38QJ2).
(e)
Remove and discard the cable-ties (1) from the harness 13QT1(13QT2) and from the fuel probes 21QT1(21QT2), 23QT1(23QT2) and 25QT1(25QT2).
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 28-42-43Page 414 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1
(f)
Remove and keep the nylon spacers (5).
(g)
Remove the bolt (4) to release the P clip (3).
(h)
Remove the harness 13QT1(13QT2) from the P clip (3) and use the bolt (4) to temporarily install the P clip (3).
(i)
Remove the spacer sleeve (6) from the harness 13QT1(13QT2).
(2)
Remove the harness 13QT1 (13QT2) at RIB 3, RIB 4 and RIB 5 as follows: (Ref. Fig. 404/TASK 28-42-43-991-007)
(a)
Get access through the opening 540AB(640AB) and the openings in RIB3, RIB4 and RIB5.
(b)
Disconnect the terminal connectors (2) from the terminal block of the fuel probe 27QT1(27QT2).
(c)
Remove and discard the terminal connectors (2) from the ends of the harness.
(d)
Remove and discard the cable-ties (1) from the harness.
(3)
Remove the harness 13QT1 (13QT2) at RIB 6 as follows: (Ref. Fig. 404/TASK 28-42-43-991-007)
(a)
Get access through the opening 574BB(674BB).
(b)
Disconnect the plug connector (33) from the connector
4039VC1(4039VC2) (34).
(c)
Put a blanking cap on the plug connector (33).
(d)
Remove and discard the lockwire from the nut (32).
(e)
Remove the nut (32) and the washer (31) from the connector (34).
(f)
Get access through the opening 540BB (640BB) to the rear spar.
(g)
Use a plastic spatula to remove the sealant from between the connector (34) and the tank wall.
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機(jī)維護(hù)手冊 AMM FUEL 燃油5(85)
