- the right wing, in parenthesis, (FIN).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞28-42-00∞∞∞∞∞∞∞∞∞∞Page A207
Aug 01/05 CES
(1) Temporarily replace the FQIC 3QT with a serviceable item (Ref. AMM TASK 28-42-34-000-001) and (Ref. AMM TASK 28-42-34-400-001).
NOTE : The step (1) has been included because it is important to make
____ sure that the FQIC is serviceable before you start more steps.
(2) If the message L(R) QTY PROBE 26QT1(2) is not shown:
- complete the installation of the FQIC (3QT) (Ref. AMM TASK 28-42-34-000-001) and (Ref. AMM TASK 28-42-34-400-001).
(3) If the message L(R) QTY PROBE 26QT1(2) is shown:
(a) Remove the temporary installed serviceable FQIC 3QT (Ref. AMM TASK 28-42-34-000-001) and return it to stores.
(b) Install the initial FQIC 3QT (Ref. AMM TASK 28-42-34-400-001).
(4) Get access to the fused connector 4043VC-A (4044VC-A) (Ref. AMM TASK 28-42-43-000-008).
(5) Remove the fused connector 4043VC-A (4044VC-A).
NOTE : Each capacitive fuel probe is supplied with an alternating
____ current drive, of 30 volts at 30 kilo-hertz, from the FQIC. The fuel probes in a tank group (harness) share the drive and drive return (two aircraft wires) between the FQIC rack connector and the fused connector 4043VC-A (4044VC-A). The fused connector is adjacent to and below its related tank wall connector. In the fused connector:
- the drive wire divides to supply each of the related fuel probes, in parallel
- the drive return wire also divides to connect to each of the
related fuel probes, in parallel through a fuse. All of the discrete drive and drive return wires then go to the tank wall connector 4040VC1(2)-A. Diodes located in the terminal housing of the fuel probe half wave rectify the output signal. The negative going, dc current signal (in proportion to the capacitance value/fuel height from the fuel probe) is routed directly from the tank wall connector 4040VC1(2)-A to the FQIC rack connector.
(6) Use a multimeter to do a check for continuity, of the related in line fuse (Ref. ASM 28-42/07) ((Ref. ASM 28-42/08)) between the pins K and
Y.
(7) If the continuity test shows:
(a) The fuse has continuity (serviceable), install the serviceable fused connector and continue with step (8).
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(b) The fuse is open circuit (first time unserviceable):
1 Replace the fused connector 4043VC-A(4044VC-A) with a
_
serviceable item.
2 Do the test given in Para. 3.B.
_
(c) The fuse is open circuit (second time unserviceable):
1 Continue with step (8), only replace the fused connector
_ 4043VC-A (4044VC-A) when the cause of the short circuit has been identified and corrected.
(8) Get access to the tank wall connector 4040VC1(2)-A and the fused connector 4043VC-A(4044VC-A) (Ref. AMM TASK 28-42-43-000-008).
(a) Disconnect the:
- tank wall connector 4040VC1(2)-A
- fused connector 4043VC-A(4044VC-A).
(9) Remove the FQIC 3QT (Ref. AMM TASK 28-42-34-000-001).
(10) Do a visual inspection and electrical tests of the aircraft wiring (Ref. AWM 28-42-11) ((Ref. AWM 28-42-10)) and (Ref. AWM 28-42-13) ( (Ref. AWM 28-42-12)) between the FQIC rack connector 3QT-A and the tank wall connector 4040VC1-A(4040VC2-A) as follows:
(a) Visual Inspection Make sure that good lighting is available. Do a visual inspection and look for distortion (bent, pinched or stretched), damage (broken, chafed or cut), discoloration, overheating (burnt, melted or arcing), liquid contamination, loose electrical connection, or incorrect assembly of the items that follow:
- FQIC rack connector 3QT-A, pins 6D(10K), 1C(6J) and 15D(15K)
- 92VU shelf receptacle 210VC (214VC) and connector 210VC-A(214VC-A)
- receptacle 1970VC (1521VC) and connector 1970VC-A(1521VC-A)
- receptacle 2973VC and connector 2973VC-A (right wing only)
- receptacle 7155VC(7110VC) and connector 7155VC-A(7110VC-A)
- pressure seal feedthrough 4017VP(4016VP)
- fused connector 4043VC-A(4044VC-A) and receptacle 4043VC(4044VC) 中國(guó)航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320 Trouble Shooting Manual 排故手冊(cè) FUEL 燃油2(155)
