R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
The pressure switches 23QA(28QA), 27QA(24QA) and 39QA(40QA) monitor the output pressure of the fuel pumps. They are installed on the rear face of the wing and center tank rear spar. A banjo-connection and pressure pipe connect the pressure switch to the fuel pump. If the pressure from the main pump decreases to less than 0.41 bar (6.0 psi) the pressure switch:
-puts on the amber FAULT light in the related main pump P/BSW
1EFF : ALL 1 28-21-00Page 13 1 1 Aug 01/05 1 1 1CES 1
-
sends a signal to the Fuel Level Sensing Control Unit (FLSCU) (Ref. 28-46-00)
-
sends a signal to the ECAM system.
**ON A/C 301-399,
The pressure switches 23QA(24QA), 27QA(28QA) monitor the output pressure of the fuel pumps. They are installed on the rear face of the wing rear spar. A banjo-connection and pressure pipe connect the pressure switch to the fuel pump. If the pressure from the main pump decreases to less than 0.41 bar
(6.0 psi) the pressure switch:
-puts on the amber FAULT light in the related main pump P/BSW
-
sends a signal to the Fuel Level Sensing Control Unit (FLSCU) (Ref. 28-46-00)
-
sends a signal to the ECAM system.
**ON A/C ALL
The air release valve 86QM(87QM) releases the air caught in the engine fuel feed-line. The valve is installed at the high point between the pump and the LP valve (Ref. 28-24-00).
A suction valve is in the engine feed line in each of the collector cells. If all the main pumps fail the engines can use suction pressure to remove the fuel from the applicable tank through the suction valves.
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299,
(Ref. Fig. 003)
R **ON A/C 301-399,
(Ref. Fig. 003A)
R **ON A/C 401-499,
(Ref. Fig. 003B)
1EFF : ALL 1 28-21-00Page 14 1 1 Aug 01/05 1 1 1CES 1
Fuel Pump System - Cockpit Indications
Figure 003
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 28-21-00Page 15 1201-299, 1Aug 01/05 1 1 1CES 1
Fuel Pump System - Cockpit Indication
R Figure 003A
R 1EFF : 301-399, 1 28-21-00 Page 16
1 1 Aug 01/05
1 1
1CES 1
Fuel Pump System - Cockpit Indications
R Figure 003B
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1 1 Aug 01/05
1 1
1CES 1
**ON A/C ALL
Each fuel pump has a related control and indication circuit. These circuits have a P/BSW on the fuel control panel 40VU (which is part of the overhead panel). Each circuit also has an interface with the two System Data-Aquisition Concentrators (SDAC1 and SDAC2) (Ref. 31-54-00).
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
The P/BSWs are identified as:
-
L TK PUMP 1, 13QA
-
L TK PUMP 2, 15QA
-
R TK PUMP 1, 14QA
-
R TK PUMP 2, 16QA
-
CTR TK PUMP 1, 33QA
-
CTR TK PUMP 2, 34QA
-
CTR TK MODE SEL, 48QA.
**ON A/C 301-399,
The P/BSWs are identified as:
-
L TK PUMP 1, 13QA
-
L TK PUMP 2, 15QA
-
R TK PUMP 1, 14QA
-
R TK PUMP 2, 16QA.
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
The scavenge jet pumps 66QM(69QM), 67QM(68QM) are in the wing tank on the rear spar between RIB15 and RIB16. Fuel can enter the surge tank (Ref. 28-11-00) through the venting system (Ref. 28-12-00), when this occurs, the scavenge jet pumps 66QM(69QM) move fuel to the rear intercell transfer valves 28QM(30QM) (Ref. 28-15-00). The check valves 37QM(38QM) are in the fuel line between the surge tank and the related jet pump. They make sure that fuel cannot enter the surge tank through the related jet pump if the main pumps fail or are set to off. The scavenge jet pumps 67QM(68QM) move fuel caught in the wing tank outer cell to the rear intercell transfer valve.
1EFF : ALL 1 28-21-00Page 18 1 1 Aug 01/05 1 1 1CES 1 The scavenge jet pumps 89QM(90QM) are in the center tank on the rear spar. They move fuel caught in the center tank to the related center tank main pump inlet.
**ON A/C ALL
4. Power Supply
____________ R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
(Ref. Fig. 004)
**ON A/C 301-399,
(Ref. Fig. 004A)
**ON A/C ALL
(Ref. Fig. 005) 中國航空網(wǎng) m.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320飛機維護手冊 AMM FUEL 燃油2(101)
