Air-Release-Valve 86QM(87QM) AMM 28-21-52-000-004 Removal of the Check Valve of the Fuel Pump Canister AMM 28-21-52-400-004 Installation of the Check Valve of the Fuel Pump
Canister
AMM 28-46-00-740-001 Functional (BITE) Test
TSM 28-CFDS PB 101
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3. Fault Confirmation
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R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
A. Prerequisite Test
NOTE : If there are any failed LRUs in the FLSS, this test is necessary
____ to find and to show them. This is because the FLSS Bite test is only done when the aircraft is electrically powered up and the FLSS defect report transferred to the Post Flight Report (PFR) at take off.
If a FLSS LRU is unserviceable and causes the fuel to be used in the incorrect sequence, the FQIC will issue (at all times excluding refuel):
- inputs to the FWC to show the FUEL-AUTO FEED FAULT warning
- a ground to the P/BSW-CTR TK/MODE SEL/AUTO (48QA) to light the FAULT legend if set to AUTO.
This procedure is based on actual aircraft malfunctions:
- that did not give any reported WARNINGS or MESSAGES on the PFR
- where the fuel imbalance was seen by the flight crew before a FUEL imbalance advisory was given.
(1) Do the FLSS BITE Test (Ref. AMM TASK 28-46-00-740-001).
(2) Examine the FLSS STATUS page for any of the FUEL LEVEL SENSING messages that follow:
- L(R) FULL SENSOR 23QJ1(2)
- L(R) UNFULL SENSOR 24QJ1(2)
- L(R) UNFULL SENSOR 25QJ1(2)
- L(R) UNFULL SENSOR 26QJ1(2)
- L(R) FULL SENSOR 27QJ1(2)
- L(R) SURGE SENSOR 28QJ1(2)
- FLSCU1(2) 7(9)QJ.
(3) If none of the messages given in step (2) are shown, go to the Operation Test in Para. 3.B.
(4) If one or more of the messages given in step (2) are shown:
(a) Go to (Ref. TSM 28-CFDS PB 101) for the applicable Task(s) number(s).
(b) Trouble shoot the applicable LRU(s) shown.
(c) Go to the Operational Test in Para. 3.B.
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B. Operational Test
(1) Go to the Operational Leak Test of the Air Release Valve Float (Ref. AMM TASK 28-21-00-710-011).
NOTE : The engine feed system (internal to the collector cell) has a
____ suction valve with a controlled leak rate when in the closed position. The suction valve has a number of slots in the valve seat. These slots let fuel go (escape from) between the clack valve and the valve seat. The fuel flow generated through the slots (controlled leak) is to prevent the formation of ice in the mouth of the suction valve. This is necessary because a proportion of water can be in the fuel. The maximum permitted flow of the controlled leak is 210 kg (460 lb)/hour.
(a) If the left side fuel quantity was more than the right side (or fuel was discharged from the left side NACA vent):
- do the AMM TASK with the PUMP-FUEL No. 1, CTR TK (37QA).
NOTE : During this test procedure fuel from the center tank is
____ pressurized by the PUMP-FUEL No. 1, CTR TK (37QA). This fuel pressure is then applied to the ENG 1 (aircraft left side) LP fuel supply line to test for a leak.
(b) If the right side fuel quantity was more than the left side (or fuel was discharged from the right side NACA vent):
- do the AMM TASK with the PUMP-FUEL No. 2, CTR TK (38QA).
NOTE : During this test procedure fuel from the center tank is
____ pressurized by the PUMP-FUEL No. 2, CTR TK (38QA). This fuel pressure is then applied to the ENG 2 (aircraft right side) LP fuel supply line to test for a leak.
(2) If this is the first time this failure occurred and the related engine LP fuel supply line operates as specified:
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 FUEL 燃油1(144)
