- adjacent and related connecting wires.

 2 Electrical Tests
_ Do a continuity test (Ref. ESPM 20-52-21) and a test for a short circuit (Ref. ESPM 20-52-22) of the wires that follow (Ref. AWM 28-42-07) ((Ref. AWM 28-42-06)):
 - FQIC rack connector 3QT-A, pin 2C(2H) to connector 4039VC1(2)-A, pin A (probe 7 signal)

 - FQIC rack connector 3QT-A, pin 3C(3H) to connector 4039VC1(2)-A, pin W (common drive return)

 - FQIC rack connector 3QT-A, pin 1E(2G) to connector 4039VC1(2)-A, pin V (common drive).

 (d) Repair all the unserviceable wiring and connectors (Ref. ESPM 20-00-00).

 (e) Connect the:

 - shorting plug 4041VC-A(4042VC-A) to the receptacle 4041VC(4042VC) (Ref. AMM TASK 28-42-43-400-008)

 - tank wall connector 4039VC1-A(4039VC2-A) to the receptacle 4039VC1(4039VC2).

 (f) Install the initial FQIC 3QT (Ref. AMM TASK 28-42-34-400-001).

 (g) Do the test given in Para. 3.B.

 (4) If the fault continues, drain and open the tank to the air (Ref. AMM TASK 28-10-00-910-001) and (Ref. AMM TASK 28-10-00-910-002).

 (5) Do a check of the HARNESS-LEFT WING TANK A (57QT) (HARNESS-RIGHT WING TANK A (58QT)) (Ref. AWM 28-42-07) ((Ref. AWM 28-42-06)) and replace, if necessary, (Ref. AMM TASK 28-42-43-000-005) and (Ref. AMM TASK 28-42-43-400-005).

 (6) If the harness 57QT (58QT) is serviceable, replace the PROBE-FUEL QTY NO 7, RIB 6-7 L WNG TK INR GROUP A (27QT1) (PROBE-FUEL QTY NO 7, RIB 6-7 R WNG TK INR GROUP A (27QT2)) (Ref. AMM TASK 28-42-15-000-005) and (Ref. AMM TASK 28-42-15-400-005).

R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
 Post SB 28-1087 For A/C 001-049,051-061,101-105,201-203,
 A. Procedure
 NOTE : Where applicable, to show the difference between the left and
____ right wing installations, the FINs given in this procedure are written as follows:
 - the left wing, no parenthesis, FIN

 - 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 A221
 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 27QT1(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 27QT1(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 4041VC-A (4042VC-A) (Ref. AMM TASK 28-42-43-000-008).

 (5) Remove the fused connector 4041VC-A (4042VC-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 4041VC-A (4042VC-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 4039VC1(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 4039VC1(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 28-42/05) ((Ref. ASM 28-42/06)) between the pins K and

 R.

 (7) If the continuity test shows:

 (a) The fuse has continuity (serviceable), install the serviceable fused connector and continue with step (8).
 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞28-42-00∞∞∞∞∞∞∞∞∞∞Page A222
　
中國(guó)航空網(wǎng) m.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(161)