DOC AIRBUS | TSM A320FFuel - ACT Automatic Transfer Failure (802VU ACT Relay Testbox)
TASK 28-28-00-810-804-A-01
Fuel - ACT Automatic Transfer Failure (802VU ACT Relay Testbox)
A. Fixtures, Tools, Test and Support Equipment
B. Referenced Information
3. Fault Confirmation
Subtask 28-28-00-865-083-A ** ON A/C NOT FOR ALL
Subtask 28-28-00-810-109-C ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:28:51 UTC
Fuel - ACT Automatic Transfer Failure (802VU ACT Relay Testbox)
WARNING:
OBEY THE FUEL SAFETY PROCEDURES.
1. Possible Causes- FLSCU 3 [47QJ]
- PROBE-FQI NO 1, ACT1 [65QT1]
- PROBE-FQI NO 2, ACT1 [66QT1]
- RELAY-AUTO/MANUAL TRANSFER, ACT [23QH]
- PROBE-FQI NO 1, ACT2 [65QT2]
- PROBE-FQI NO 2, ACT2 [66QT2]
- FLSCU-1 [7QJ]
- SENSOR-HIGH LEVEL, CHANNEL A [20QJ]
- RELAY-FLSCU 1 SUPPLY [50QJ]
- LGCIU-1 [5GA1]
- RELAY-POWER SUPPLY SWITCH [39QU]
- aircraft wiring
- SLAT/FLAP CONTR.COMP. [21CV]
- SLAT/FLAP CONTR.COMP. [22CV]
- RELAY-LOW LEVEL OVERRIDE, ACT [17QH]
- RELAY-TRANSFER CONTROL, ACT [22QH]
- RELAY-TRANSFER INHIBIT, ACT [15QH]
[13QH] [14QH] - RELAY-MANUAL TRANSFER, ACT [16QH]
- RELAY-REFUEL/TRANSFER CONTROL, ACT1 [35QU]
- RELAY-SEQUENCE [18QH]
- RELAY-REFUEL INHIBIT, ACT1 [37QU]
- RELAY- INLET VALVE CONTROL, ACT1 [19QH]
- RELAY-INLET VALVE CONTROL, ACT2 [20QH]
- RELAY-REFUEL/TRANSFER CONTROL, ACT2 [36QU]
- RELAY-PRESSURIZATION CONTROL, ACT [28QH]
- ACTUATOR-FUEL TRANSFER VALVE, ACT [6QH]
- VALVE-FUEL TRANSFER, ACT [165QM]
- ACTUATOR-AIR SHUTOFF VALVE, ACT [3QH]
- VALVE-AIR SHUTOFF, ACT [168QM]
RELAY-PANEL (802VU) - ACTUATOR-VENT VALVE, ACT1 [4QH1]
- VALVE-VENT, ACT1 [167QM1]
- ACTUATOR-VENT VALVE, ACT2 [4QH2]
- VALVE-VENT, ACT2 [167QM2]
- VALVE-PRESSURE REDUCING, ACT1 [171QM]
- AIR FILTER-CABIN INTAKE, ACT PRESSURIZATION [183QM]
- CHECK VALVE-CABIN AIR INTAKE, ACT PRESSURIZATION [179QM]
- CHECK VALVE-ACT PRESSURIZATION [178QM]
- PROTECTOR-OVERPRESSURE, ACT1 [170QM1]
- PROTECTOR-OVERPRESSURE, ACT2 [170QM2]
- VALVE-PRESSURE HOLDING, ACT1 [191QM1]
- VALVE-PRESSURE HOLDING, ACT2 [191QM2]
- VALVE-INWARD PRESSURE RELIEF, ACT1 [172QM1]
- VALVE-INWARD PRESSURE RELIEF, ACT2 [172QM2]
- CHECK VALVE-ACT PRESSURIZATION [177QM1]
- CHECK VALVE-ACT2 [177QM2]
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| RIN28108706000 | 1 | TESTBOX-ACT 802VU |
| REFERENCE | DESIGNATION |
|---|---|
| TSM TASK 28-13-00-810-801-A | Fuel - Leak Shows at Drain Mast |
| TSM TASK 28-28-00-810-801-A | Fuel Pumps - ACT Manual Transfer Pump 1QH System Malfunction |
| TSM TASK 28-28-00-810-801-A-01 | Fuel Pumps - ACT Manual Transfer Pump 1QH System Malfunction (802VU ACT Relay Testbox) |
| TSM TASK 28-28-00-810-802-A | Fuel - ACT 1 Manual Transfer Failure (On The Ground) |
| TSM TASK 28-28-00-810-802-A-01 | Fuel - ACT 1 Manual Transfer Failure (On The Ground) (802VU ACT Relay Testbox) |
| TSM TASK 28-28-00-810-806-A | Fuel - ACT Transfer System Flag/Symbol Failure |
| TSM TASK 28-28-00-810-807-A | Fuel - ACT 2 Sequence Failure |
| TSM TASK 28-28-00-810-807-A-01 | Fuel - ACT 2 Sequence Failure (802VU ACT Relay Testbox) |
| TSM TASK 28-46-00-810-828-A | ACT 1 - FLSCU-3 Channel LS1 - Low Level Sensor No. 1 Failure |
| TSM TASK 28-46-00-810-829-A | ACT 1 - FLSCU-3 Channel LS5 - Low Level Sensor No. 2 Failure |
| TSM TASK 28-46-00-810-834-A | ACT 2 - FLSCU-3 Channel LS8 - Low Level Sensor No. 1 Failure |
| TSM TASK 28-46-00-810-835-A | ACT 2 - FLSCU-3 Channel LS2 - Low Level Sensor No. 2 Failure |
| AMM 12-11-28-650-003 | Pressure Refuel with Automatic Control |
| AMM 25-71-11-000-001 | Removal of the Additional Center-Tank (ACT) Relay-Box 802VU |
| AMM 25-71-11-400-001 | Installation of the Additional Center-Tank (ACT) Relay-Box 802VU |
| AMM 27-51-34-000-001 | Removal of the SFCC |
| AMM 27-51-34-400-001 | Installation of the SFCC |
| AMM 27-80-00-866-004 | Extending the Slats on the Ground |
| AMM 27-80-00-866-005 | Retracting the Slats on the Ground |
| AMM 28-12-55-000-001 | Removal of the ACT Overpressure Protector (170QM) |
| AMM 28-12-55-400-001 | Installation of the ACT Overpressure Protector (170QM) |
| AMM 28-12-56-000-001 | Removal of the Inward Pressure Relief Valve (172QM) |
| AMM 28-12-56-400-001 | Installation of the Inward Pressure Relief Valve (172QM) |
| AMM 28-25-00-650-001 | Pressure Defuel |
| AMM 28-25-00-869-001 | Fuel Transfer |
| ASM 282501 | |
| AMM 28-28-00-710-001 | Operational Check of the ACT Manual Transfer System |
| AMM 28-28-00-710-004 | Operational Test of the ACT Automatic Transfer System |
| AMM 28-28-00-710-016 | Operational Test of the ACT Pressure Holding Valves (191QM) |
| AMM 28-28-00-720-001 | Functional Test of the ACT Pressure Reducing Valve |
| ASM 282801 | |
| ASM 282802 | |
| ASM 282803 | |
| ASM 282804 | |
| AMM 28-28-33-000-001 | Removal of the ACT Fuel Transfer-Valve |
| AMM 28-28-33-400-001 | Installation of the ACT Fuel Transfer-Valve |
| AMM 28-28-35-000-001 | Removal of the ACT Vent Shut-off Valve (167QM) |
| AMM 28-28-35-400-001 | Installation of the ACT Vent Shut-off Valve (167QM) |
| AMM 28-28-36-000-001 | Removal of the ACT Air Shut-Off Valve |
| AMM 28-28-36-400-001 | Installation of the ACT Air Shut-Off Valve |
| AMM 28-28-39-000-001 | Removal of the Cabin Air Intake Filter-Assembly |
| AMM 28-28-39-400-001 | Installation of the Cabin Air Intake Filter-Assembly |
| AMM 28-28-42-000-001 | Removal of the ACT Pressure Reducing Valve |
| AMM 28-28-42-400-001 | Installation of the ACT Pressure Reducing Valve |
| AMM 28-28-48-000-001 | Removal of the ACT Pressure Holding Valve |
| AMM 28-28-48-400-001 | Installation of the ACT Pressure Holding Valve |
| AMM 28-28-53-000-001 | Removal of the ACT Transfer-Valve Actuator |
| AMM 28-28-53-400-001 | Installation of the ACT Transfer-Valve Actuator |
| AMM 28-28-55-000-001 | Removal of the ACT Vent Shut-off Valve Actuator (4QH) |
| AMM 28-28-55-400-001 | Installation of the ACT Vent Shut-off Valve Actuator (4QH) |
| AMM 28-28-56-000-001 | Removal of the ACT Air Shut-Off Valve Actuator |
| AMM 28-28-56-400-001 | Installation of the ACT Air Shut-Off Valve Actuator |
| AMM 28-46-34-000-001 | Removal of the Fuel-Level Sensing Control-Unit (FLSCU) |
| AMM 28-46-34-400-001 | Installation of the Fuel-Level Sensing Control-Unit (FLSCU) |
| AMM 32-31-71-000-001 | Removal of the LGCIU |
| AMM 32-31-71-400-001 | Installation of the LGCIU |
| ASM 326201 | |
| AMM 32-69-00-860-001 | Simulation of Flight (With Aircraft on Ground) |
Subtask 28-28-00-865-083-A ** ON A/C NOT FOR ALL
A. Table of the circuit breakers referred to in this procedure:
Subtask 28-28-00-710-088-A ** ON A/C NOT FOR ALL | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 121VU | FUEL/HI/LVL/SPLY | 1QJ | L25 |
| 121VU | ACT1/CTL & SPLY | 9QH | P29 |
| 121VU | ACT2/CTL & SPLY | 10QH | P28 |
B. Initial Test
(1) Do a check of the three leak monitors (Ref. TSM TASK 28-13-00-810-801).
(2) If you find fuel in a leak monitor, do the related trouble-shooting (Ref. TSM TASK 28-13-00-810-801).
Subtask 28-28-00-710-089-B ** ON A/C NOT FOR ALL (1) Do a check of the three leak monitors (Ref. TSM TASK 28-13-00-810-801).
(2) If you find fuel in a leak monitor, do the related trouble-shooting (Ref. TSM TASK 28-13-00-810-801).
C. Test
It is important to make sure that there are no (known/obvious) fuel leaks in the ACT system assemblies before you do the test that follows.
(1) Do the Operational Test of the ACT Automatic Transfer System AMM 28-28-00-710-004.
4. Fault IsolationIt is important to make sure that there are no (known/obvious) fuel leaks in the ACT system assemblies before you do the test that follows.
(1) Do the Operational Test of the ACT Automatic Transfer System AMM 28-28-00-710-004.
NOTE: The ACT Fuel Auto Transfer system is powered by a controlled air bleed from the cabin pressurization and is therefore not effective on the ground or at low altitude.
The ACT auto transfer system is pressurized when the aircraft has taken off and the center tank high level sensor has been dry for ten (10) minutes. The ACT transfer system will stay pressurized until the aircraft lands.
If the slats are extended to more than 16 degrees the auto transfer stops (inlet valve and transfer valve go to closed) and starts when the slats are less than 16 degrees.
If the center tank high level sensor becomes wet (re-wets because the fuel burn rate is less than the ACT transfer rate) the auto transfer stops (inlet valve and transfer valve go to closed). When the center tank high level sensor becomes dry there is a ten (10) minute delay before the inlet valve opens and fuel transfers.
When the ACT 2 contains less than approximately 80 kg (176.3698 lb) of fuel (the two ACT 2 low level sensors become dry), the ACT auto transfer source of fuel to be transferred, changes from ACT 2 to ACT 1 (the ACT 2 inlet valve is closed and ACT 1 inlet valve is opened).
When the ACT 1 contains less than approximately 80 kg (176.3698 lb) of fuel (the two ACT 1 low level sensors become dry), the ACT auto transfer stops (the ACT 1 inlet valve and transfer valve go to closed).
The ACT auto transfer system is pressurized when the aircraft has taken off and the center tank high level sensor has been dry for ten (10) minutes. The ACT transfer system will stay pressurized until the aircraft lands.
If the slats are extended to more than 16 degrees the auto transfer stops (inlet valve and transfer valve go to closed) and starts when the slats are less than 16 degrees.
If the center tank high level sensor becomes wet (re-wets because the fuel burn rate is less than the ACT transfer rate) the auto transfer stops (inlet valve and transfer valve go to closed). When the center tank high level sensor becomes dry there is a ten (10) minute delay before the inlet valve opens and fuel transfers.
When the ACT 2 contains less than approximately 80 kg (176.3698 lb) of fuel (the two ACT 2 low level sensors become dry), the ACT auto transfer source of fuel to be transferred, changes from ACT 2 to ACT 1 (the ACT 2 inlet valve is closed and ACT 1 inlet valve is opened).
When the ACT 1 contains less than approximately 80 kg (176.3698 lb) of fuel (the two ACT 1 low level sensors become dry), the ACT auto transfer stops (the ACT 1 inlet valve and transfer valve go to closed).
NOTE: You can get more data about the ACT Transfer System from the:
- Description and Operation (D and O) section of the Aircraft Maintenance Manual (AMM) Chap. 28-28-00, the Additional Center Tank (ACT) Transfer System
- AMM Chap. 28-46-00, the Fuel Level Sensing System (FLSS)
- AMM Chap. 27-81-00, the Slats Electrical Control and Monitoring
- AMM Chap. 32-69-00, Landing Gear - Bite
- Aircraft Schematic Manual (ASM), ACT XFR System, Inlet Valve ASM 282801
- ASM, ACT XFR System, Transfer Valve ASM 282803
- ASM, ACT XFR System, Vent Valves ASM 282804
- ASM, FLSS, High Level Refuel Control ASM 282801
- ASM, FLSS, Low Level Indication ASM 282802.
Subtask 28-28-00-810-109-C ** ON A/C NOT FOR ALL
A. Procedure
(1) If the ACT automatic transfer system does not transfer fuel forward to the center tank:
(a) Is shown but fuel does not transfer forward as shown by the ACT and the center tank fuel quantities:
(4) If fuel does not transfer FWD in Manual control:
(a) Do ACT Manual Transfer, Pump System Failure (Ref. TSM TASK 28-28-00-810-801).
(b) Do ACT 2 Manual Transfer/Sequence Failure (On The Ground) (Ref. TSM TASK 28-28-00-810-807).
(c) Do ACT 1 Manual Transfer Failure (On The Ground) (Ref. TSM TASK 28-28-00-810-802).
(5) If the ACT transfer system flag/symbol was not shown in manual and/or automatic modes of operation but fuel transferred correctly:
(7) Do the FLSCU 3 [47QJ] , CHAN LS1 and LS5, ACT 1 low level inputs to the RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Examine the FUEL System Display ACT 1 fuel quantity, and make sure it contains more than 80 kg (176.3698 lb) of fuel:
(d) If there is no 28VDC on pins <b and <c:
1 Do the trouble-shooting task ACT 1 - FLSCU-3 (47QJ) Channel LS1 - Low Level Sensor No. 1 (65QT1) Failure (Ref. TSM TASK 28-46-00-810-828), part of PROBE-FQI NO 1, ACT1 [65QT1] .
2 Do the trouble-shooting task ACT 1 - FLSCU-3 (47QJ) Channel LS5 - Low Level Sensor No. 2 (66QT1) Failure (Ref. TSM TASK 28-46-00-810-829), part of PROBE-FQI NO 2, ACT1 [66QT1] .
3 Do the test given in Para. 3.C.
(f) If the fault continues, replace the RELAY-PANEL (802VU) AMM 25-71-11-000-001 and AMM 25-71-11-400-001.
(g) If the fault continues:
1 Do a check of ASM 282803 and replace, if necessary, the RELAY-AUTO/MANUAL TRANSFER, ACT [23QH] .
2 Do a check of the RELAY-PANEL (802VU) wiring ASM 282803 between the connector to relay and connector to connector lines, as shown in the table that follows:
a Repair all the unserviceable wiring and connectors.
b Do the test given in Para. 3.C.
(8) Do the FLSCU 3 [47QJ] , CHAN LS8 and LS2, ACT 2 low level inputs to the RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Examine the FUEL System Display ACT 2 fuel quantity, and make sure it contains more than 80 kg (176.3698 lb) of fuel:
There must not be 28VDC on these pins.
(d) If the lights do not come on there is no 28VDC at pins A and B:
1 Do the trouble-shooting task ACT 2 - FLSCU-3 (47QJ) Channel LS8 - Low Level Sensor No. 1 (65QT2) Failure (Ref. TSM TASK 28-46-00-810-834), part of PROBE-FQI NO 1, ACT2 [65QT2] .
2 Do the trouble-shooting task ACT 2 - FLSCU-3 (47QJ) Channel LS2 - Low Level Sensor No. 2 (66QT2) Failure (Ref. TSM TASK 28-46-00-810-835), part of PROBE-FQI NO 2, ACT2 [66QT2] .
3 Do the test given in Para. 3.C.
(f) If the fault continues, replace the RELAY-PANEL (802VU) AMM 25-71-11-000-001 and AMM 25-71-11-400-001.
(g) If the fault continues:
1 Do a check of ASM 282803 and replace, if necessary, the RELAY-AUTO/MANUAL TRANSFER, ACT [23QH] .
2 Do a check of the RELAY-PANEL (802VU) wiring ASM 282803 between the connector to relay and connector to connector lines, as shown in the table that follows:
a Repair all the unserviceable wiring and connectors.
b Do the test given in Para. 3.C.
(9) Do the FLSCU-1 [7QJ] , CHAN LS7 - SENSOR-HIGH LEVEL, CHANNEL A [20QJ] center tank high level input to the RELAY-PANEL (802VU) trouble-shooting as follows:
(c) Remove the FLSCU-1 (7QJ) AMM 28-46-34-000-001.
(d) Do a test, with a multimeter, to make sure 28VDC is available at the rack connector AA, pin 1B.
(e) Open, safety and tag the C/B-HIGH LEVEL SUPPLY (1QJ).
(f) Do a test, with a multimeter, to make sure 28VDC is not available at the rack connector AA, pin 1B.
(g) Do the Simulation of Flight with the Aircraft on the Ground AMM 32-69-00-860-001 for:
1 LGCIU-1 (5GA1).
2 NOSE + LH + RH.
3 UPLOCKED.
(i) If the test results are, as specified in (d), (f) and (h):
1 Install the FLSCU-1 (7QJ) AMM 28-46-34-400-001 removed in step (c).
2 Remove tag and close the C/B-HIGH LEVEL SUPPLY (1QJ).
3 Go to step (10).
(j) If the test results are, not as specified in (d), (f) and (h), do the trouble-shooting as follows:
1 Do a check of and replace, if necessary:
2 Do a check of the aircraft wiring ASM 282501 between:
b Do the test given in Para. 3.C.
3 If the fault continues, replace the RELAY-PANEL (802VU) AMM 25-71-11-000-001 and AMM 25-71-11-400-001.
4 If the fault continues, do the step 5_ or the step 6_ as applicable:
5 Do a check of and replace, if necessary, the RELAY-POWER SUPPLY SWITCH [39QU] .
6 Do a check of the RELAY-PANEL (802VU) wiring between the connector to relay lines, as shown in the table that follows:
a Repair all the unserviceable wiring and connectors.
b Do the test given in Para. 3.C.
c Do the Simulation of Flight with the Aircraft on the Ground and return the aircraft to the ground configuration AMM 32-69-00-860-001.
(10) Do the SFCC-1 (21CV) and SFCC-2 (22CV) slats input to RELAY-PANEL (802VU) trouble-shooting as follows:
(b) Do a check of the aircraft wiring ASM 282803 between:
(d) Install the SFCC-1 (21CV) AMM 27-51-34-400-001.
(e) Make sure that the slats are extended to more than 16 degrees:
This test must show continuity.
(g) Retract the slats to less than 16 degrees AMM 27-80-00-866-005.
This test must show an open circuit.
(i) If the test results (for SFCC-1) are:
1 As specified in (f) and (h):
(k) Do the steps (e) thru (h) to test the SFCC-2.
(l) If the test results (for SFCC-2) are:
1 As specified in (f) and (h):
(11) Do the LGCIU-1 (5GA1) ground/flight input to RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Use a multimeter to do a test for continuity, at the free connector 4065VC-A between the pin V and a suitable ground ASM 282803 and ASM 326201.
This test must show continuity.
(b) Do the Simulation of Flight with the Aircraft on the Ground AMM 32-69-00-860-001 for:
1 LGCIU-1 (5GA1).
2 NOSE + LH + RH.
3 UPLOCKED.
(c) Use a multimeter to do a test for continuity, at the free connector 4065VC-A between the pin V and a suitable ground ASM 282803 and ASM 326201.
This test must show an open circuit.
(d) If the test results are:
1 As specified in (a) and (c):
a Remove the LGCIU-1 (5GA1) AMM 32-31-71-000-001.
b Do a check of the aircraft wiring ASM 282803 and ASM 326201 between:
d If there is no fault in the aircraft wiring, replace the LGCIU-1 [5GA1] with a serviceable item and install AMM 32-31-71-400-001.
e Do the test given in Para. 3.C.
(12) Connect the free connector 4065VC-A to the RELAY-PANEL (802VU).
(Inputs from external systems required for a two ACT system auto fuel transfer are correct).
(13) Do the steps that follow. This will let the ACT AUTO transfer sequence start.
(a) Release out the P/BSW-FUEL/ACT/AUTO (24QH).
(b) Make sure that the ACT 1 contains more than 250 kg (560 lb) of fuel.
(c) Make sure that the ACT 2 contains more than 250 kg (560 lb) of fuel.
(d) Make sure that the center tank contains less than 6000 kg (13220 lb) of fuel.
(e) Make sure that the slats are retracted AMM 27-80-00-866-005.
(f) Close the Refuel Panel door.
(g) Do the Simulation of Flight with the Aircraft on the Ground AMM 32-69-00-860-001.
(14) Connect the RIN28108706000 TESTBOX-ACT 802VU to the RELAY PANEL (802VU).
1 Go to step (15).
2 Do a check of ASM 282803 and replace, if necessary, the RELAY-LOW LEVEL OVERRIDE, ACT [17QH] .
3 Do a check of the RELAY-PANEL (802VU) wiring ASM 282803 between the connector to relay and relay to relay lines, as shown in the table that follows:
a Repair all the unserviceable wiring and connectors.
b Do the test given in Para. 3.C.
(15) On the testbox, do a check of the Auto Transfer (pin V) Active light.
2 Do a check of ASM 282803 and replace, if necessary:
3 Do a check of the RELAY-PANEL (802VU) wiring ASM 282803 between the connector to relay and relay to relay lines, as shown in the table that follows:
a Repair all the unserviceable wiring and connectors.
b Do the test given in Para. 3.C.
(16) On the testbox, do a check of the Relay 37QU (Refuel Inhibit, ACT1 (Pin T) not engaged light.
2 Do a check of ASM 282803 and replace, if necessary:
b Do the test given in Para. 3.C.
(17) On the testbox, do a check of the Inlet Valve ACT. ACT1 (5QH1) (CMD) OPEN light (Pin <A).
2 Do a check of ASM 282801 and replace, if necessary:
a Repair all the unserviceable wiring and connectors.
b Do the test given in Para. 3.C.
(18) On the testbox, do a check of the Sequenc Relay 18QH (Pin E) ACT1 Transfer (28VDC) light.
2 Do a check of ASM 282801 and replace, if necessary:
Additionally because there is no monitor test point of the input signal (ground) to the RELAY-INLET VALVE CTL, ACT 2 (20QH) coil at terminal X2 In a similar manner to the monitor test point T is supplied to monitor the RELAY-PANEL (802VU) ACT 1 channel. Continue as follows:
The input signal (ground) up to the sequence relay (18QH) was checked in steps (15) and (16).
a Repair all the unserviceable wiring and connectors.
b Do the test given in Para. 3.C.
(20) On the testbox, do a check of the Air Shut Off Vave (CMD) (3QH) OPEN light.
2 Do a check of ASM 282804 and replace, if necessary:
a Repair all unserviceable wiring and connectors.
b Do the test given in Para. 3.C.
(21) If the fault continues, examine the see/feel indicators of the actuators shown in the table that follows:
(a) Disconnect the ACTUATOR FUEL XFR VALVE (6QH) free connector 6QH-A.
(b) Do a test, with a multimeter, at the free connector 6QH-A, between the pins A (+ve) and E (-ve) ASM 282802 to see if 28VDC is available.
a The ACTUATOR-FUEL TRANSFER VALVE, ACT [6QH] AMM 28-28-53-000-001 and AMM 28-28-53-400-001.
b The VALVE-FUEL TRANSFER, ACT [165QM] AMM 28-28-33-000-001 and AMM 28-28-33-400-001.
2 If the voltage is not correct:
a Do a check of the aircraft wiring ASM 282803 between:
c Do the test given in Para. 3.C.
(24) Do the Actuator Fuel Inlet Valve, ACT 1 (5QH1) automatic transfer trouble-shooting as follows:
(a) An aircraft wiring check between the Inlet Valve Actuator and the RELAY-PANEL (802VU) is not applicable. This is because the same wires are used for an auto ACT transfer as for a manual ACT transfer:
(a) Disconnect the AIR SHUTOFF VALVE (3QH) free connector 3QH-A.
(b) Do a test, with a multimeter, at the free connector 3QH-A, between the pins A (+ve) and E (-ve) ASM 282804 to see if 28VDC is available.
1 If the voltage is correct, do a check of and replace, if necessary:
a The ACTUATOR-AIR SHUTOFF VALVE, ACT [3QH] AMM 28-28-56-000-001 and AMM 28-28-56-400-001.
b The VALVE-AIR SHUTOFF, ACT [168QM] AMM 28-28-36-000-001 and AMM 28-28-36-400-001.
2 If the voltage is not correct:
a Do a check of the aircraft wiring ASM 282804 between:
c Do the test given in Para. 3.C.
(26) If the fault continues:
(a) Do a check of and replace, if necessary, theRELAY-PANEL (802VU) AMM 25-71-11-000-001 and AMM 25-71-11-400-001.
(b) Do the test given in Para. 3.C.
(27) Do the Actuator Vent Valve, ACT 1 (4QH1) automatic transfer trouble-shooting as follows:
(a) Make sure that the Actuator Air Shut-off Valve free connector 3QH-A is connected to the 3QH receptacle.
(c) Do a test, with a multimeter, at the free connector 4QH1-A, between the pins B (+ve) and E (-ve) ASM 282804 to see if 28VDC is available.
1 If the voltage is correct do a check of and replace, if necessary:
a The ACTUATOR-VENT VALVE, ACT1 [4QH1] AMM 28-28-55-000-001 and AMM 28-28-55-400-001.
b The VALVE-VENT, ACT1 [167QM1] AMM 28-28-35-000-001 and AMM 28-28-35-400-001.
2 If the voltage is not correct do a check of and replace, if necessary:
a The ACTUATOR-AIR SHUTOFF VALVE, ACT [3QH] AMM 28-28-56-000-001 and AMM 28-28-56-400-001.
d Do the test given in Para. 3.C.
(28) Do the Actuator Fuel Inlet Valve, ACT 2 (5QH2) automatic transfer trouble-shooting as follows:
(a) An aircraft wiring check between the Inlet Valve Actuator and the RELAY-PANEL (802VU) is not applicable as the same lines are used for an auto ACT transfer as for a manual ACT transfer:
(a) Make sure that the Actuator Air Shut-off Valve free connector 3QH-A is connected to the 3QH receptacle.
(c) Do a test, with a multimeter, at the free connector 4QH2-A, between the pins B (+ve) and E (-ve) ASM 282804 to see if 28VDC is available.
1 If the voltage is correct do a check of and replace, if necessary:
a The ACTUATOR-VENT VALVE, ACT2 [4QH2] AMM 28-28-55-000-001 and AMM 28-28-55-400-001.
b The VALVE-VENT, ACT2 [167QM2] AMM 28-28-35-000-001 and AMM 28-28-35-400-001.
2 If the voltage is not correct and the actuator vent valve, ACT 1 (4QH1) has also failed to close, do a check of and replace, if necessary:
a The ACTUATOR-AIR SHUTOFF VALVE, ACT [3QH] AMM 28-28-56-000-001 and AMM 28-28-56-400-001.
b Do a check of the aircraft wiring ASM 282804 between:
d Do the test given in Para. 3.C.
3 If the voltage is not correct, the actuator vent valve, ACT 2 (4QH2) has failed to close, but the actuator vent valve, ACT 1 (4QH1) is closed:
a Do a check of the aircraft ASM 282804 wiring between:
c Do the test given in Para. 3.C.
(30) Make sure that the aircraft to ACT tank break air line connections are tight and free from twists, at the ACT 1 and the ACT 2.
(31) Do the Functional Test of the ACT Pressure Reducing Valve AMM 28-28-00-720-001.
(32) If the air pressure is not to the specification:
(a) The AIR FILTER-CABIN INTAKE, ACT PRESSURIZATION [183QM] AMM 28-28-39-000-001 and AMM 28-28-39-400-001.
(b) The CHECK VALVE-CABIN AIR INTAKE, ACT PRESSURIZATION [179QM] .
(c) The CHECK VALVE-ACT PRESSURIZATION [178QM] .
(d) The air lines and connections for damage or loose connections.
(e) Do the test given in Para. 3.C.
(34) If the fault continues, do a check of and replace, if necessary, items of the ACT pressurization system as follows:
(a) The PROTECTOR-OVERPRESSURE, ACT1 [170QM1] ( PROTECTOR-OVERPRESSURE, ACT2 [170QM2] ) AMM 28-12-55-000-001 and AMM 28-12-55-400-001.
1 Replace, if necessary, AMM 28-28-48-000-001 and AMM 28-28-48-400-001.
(c) The VALVE-INWARD PRESSURE RELIEF, ACT1 [172QM1] ( VALVE-INWARD PRESSURE RELIEF, ACT2 [172QM2] ) AMM 28-12-56-000-001 and AMM 28-12-56-400-001.
(1) If the ACT automatic transfer system does not transfer fuel forward to the center tank:
- examine the pilots report/aircraft log for more data.
(a) Is shown but fuel does not transfer forward as shown by the ACT and the center tank fuel quantities:
- go to step (6).
- do the Operational Test of the ACT Manual Transfer System AMM 28-28-00-710-001.
NOTE: This step is included as the most direct way of checking that the ACT Transfer Valve, and either the ACT 1 or the ACT 2 Inlet Valve can be made to open.
(3) If fuel transfers FWD in Manual control go to step (6). (4) If fuel does not transfer FWD in Manual control:
(a) Do ACT Manual Transfer, Pump System Failure (Ref. TSM TASK 28-28-00-810-801).
(b) Do ACT 2 Manual Transfer/Sequence Failure (On The Ground) (Ref. TSM TASK 28-28-00-810-807).
(c) Do ACT 1 Manual Transfer Failure (On The Ground) (Ref. TSM TASK 28-28-00-810-802).
(5) If the ACT transfer system flag/symbol was not shown in manual and/or automatic modes of operation but fuel transferred correctly:
- do ACT Transfer System Flag/Symbol Failure (Ref. TSM TASK 28-28-00-810-806).
(7) Do the FLSCU 3 [47QJ] , CHAN LS1 and LS5, ACT 1 low level inputs to the RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Examine the FUEL System Display ACT 1 fuel quantity, and make sure it contains more than 80 kg (176.3698 lb) of fuel:
- refuel if necessary AMM 12-11-28-650-003.
NOTE: This is to make sure that the two (2) ACT 1 low level sensors are wet.
During an ACT auto fuel transfer, the outputs from the two low level sensor channels are connected in series.
During normal operation when the two low level sensors become dry, a ground (ACT 1, auto transfer low level signal) causes the ACT 1 inlet valve to close.
(b) Connect the RIN28108706000 TESTBOX-ACT 802VU to the RELAY PANEL (802VU): During an ACT auto fuel transfer, the outputs from the two low level sensor channels are connected in series.
During normal operation when the two low level sensors become dry, a ground (ACT 1, auto transfer low level signal) causes the ACT 1 inlet valve to close.
- Use a clamp to connect the test box to the nearest bonding cable to electrically ground it.
NOTE: The lights on the test box will come on if there is 28VDC on the applicable pin.
(c) Do a check of the LS1 Low Level ACT 1 and LS5 Low Level ACT 2 lights <B or <C, and a suitable ground ASM 282803. (d) If there is no 28VDC on pins <b and <c:
- go to step (8).
1 Do the trouble-shooting task ACT 1 - FLSCU-3 (47QJ) Channel LS1 - Low Level Sensor No. 1 (65QT1) Failure (Ref. TSM TASK 28-46-00-810-828), part of PROBE-FQI NO 1, ACT1 [65QT1] .
2 Do the trouble-shooting task ACT 1 - FLSCU-3 (47QJ) Channel LS5 - Low Level Sensor No. 2 (66QT1) Failure (Ref. TSM TASK 28-46-00-810-829), part of PROBE-FQI NO 2, ACT1 [66QT1] .
3 Do the test given in Para. 3.C.
(f) If the fault continues, replace the RELAY-PANEL (802VU) AMM 25-71-11-000-001 and AMM 25-71-11-400-001.
- If there is no relay panel available, go to step (g).
(g) If the fault continues:
1 Do a check of ASM 282803 and replace, if necessary, the RELAY-AUTO/MANUAL TRANSFER, ACT [23QH] .
2 Do a check of the RELAY-PANEL (802VU) wiring ASM 282803 between the connector to relay and connector to connector lines, as shown in the table that follows:
NOTE: The circuit connections shown in the table are abbreviated, for example:
- the connector 4065VC, pin <A is shown as 4065VC-<A
- the RELAY-LO LVL SENSE, ACT 1 (13QH), terminal X2 is shown as RL 13QH-X2.
| CONNECTOR-PIN | RELAY-TERMINAL | TO RELAY-TERMINAL | CONNECTOR-PIN |
|---|---|---|---|
| 4065VC-<A | RL 13QH-X2 | ||
| 4065VC-<A | RL 23QH-B1 | ||
| 4065VC-<B | RL 23QH-A2 | ||
| 4065VC-<B | 4068VC-<C | ||
| 4065VC-<D | RL 23QH-B2 | ||
| 4065VC-<D | 4068VC-<B |
b Do the test given in Para. 3.C.
(8) Do the FLSCU 3 [47QJ] , CHAN LS8 and LS2, ACT 2 low level inputs to the RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Examine the FUEL System Display ACT 2 fuel quantity, and make sure it contains more than 80 kg (176.3698 lb) of fuel:
- refuel if necessary AMM 12-11-28-650-003.
NOTE: This is to make sure the two (2) ACT 2 low level sensors are wet.
During an ACT auto fuel transfer, the outputs from the two low level sensor channels are connected in series.
During normal operation when the two ACT 2 low level sensors become dry, a ground (ACT 2, auto transfer low level signal) causes the ACT 2 inlet valve open latch return circuit to the sequence relay (18QH) to be broken.
This de-energizes the sequence relay (18QH) and causes the auto transfer to change over from ACT 2 to ACT 1.
(b) Connect the RIN28108706000 TESTBOX-ACT 802VU to the RELAY PANEL (802VU). During an ACT auto fuel transfer, the outputs from the two low level sensor channels are connected in series.
During normal operation when the two ACT 2 low level sensors become dry, a ground (ACT 2, auto transfer low level signal) causes the ACT 2 inlet valve open latch return circuit to the sequence relay (18QH) to be broken.
This de-energizes the sequence relay (18QH) and causes the auto transfer to change over from ACT 2 to ACT 1.
- Use a clamp to connect the test box to the nearest bonding cable to electrically ground it.
NOTE: The lights on the test box will come on if there is 28VDC on the applicable pin.
(c) On the test box do a check of the Low Level ACT2 (LS2)(A) LOW and Low Level ACT2 (LS8)(B) lights. There must not be 28VDC on these pins.
(d) If the lights do not come on there is no 28VDC at pins A and B:
- Do step (9).
1 Do the trouble-shooting task ACT 2 - FLSCU-3 (47QJ) Channel LS8 - Low Level Sensor No. 1 (65QT2) Failure (Ref. TSM TASK 28-46-00-810-834), part of PROBE-FQI NO 1, ACT2 [65QT2] .
2 Do the trouble-shooting task ACT 2 - FLSCU-3 (47QJ) Channel LS2 - Low Level Sensor No. 2 (66QT2) Failure (Ref. TSM TASK 28-46-00-810-835), part of PROBE-FQI NO 2, ACT2 [66QT2] .
3 Do the test given in Para. 3.C.
(f) If the fault continues, replace the RELAY-PANEL (802VU) AMM 25-71-11-000-001 and AMM 25-71-11-400-001.
- If there is no relay panel available, go to step (g).
(g) If the fault continues:
1 Do a check of ASM 282803 and replace, if necessary, the RELAY-AUTO/MANUAL TRANSFER, ACT [23QH] .
2 Do a check of the RELAY-PANEL (802VU) wiring ASM 282803 between the connector to relay and connector to connector lines, as shown in the table that follows:
NOTE: The circuit connections shown in the table are abbreviated, for example:
- the connector 4065VC, pin D is shown as 4065VC-D
- the RELAY-LO LVL SENSE, ACT 2 (14QH), terminal X2 is shown as RL 14QH-X2.
| CONNECTOR-PIN | RELAY-TERMINAL | TO RELAY-TERMINAL | CONNECTOR-PIN |
|---|---|---|---|
| 4065VC-D | RL 14QH-X2 | ||
| 4065VC-D | RL 23QH-D1 | ||
| 4065VC-C | RL 23QH-D2 | ||
| 4065VC-C | 4068VC-B | ||
| 4065VC-B | RL 23QH-C2 | ||
| 4065VC-B | 4068VC-A |
b Do the test given in Para. 3.C.
(9) Do the FLSCU-1 [7QJ] , CHAN LS7 - SENSOR-HIGH LEVEL, CHANNEL A [20QJ] center tank high level input to the RELAY-PANEL (802VU) trouble-shooting as follows:
NOTE: During an ACT:
(a) Make sure that the center tank contains less than 6000 kg (13220 lb) of fuel: - auto transfer the 28VDC power supply to the center tank high level sensor channel 20QJ is supplied from the C/B-ACT1/XFR VALVE/AUTO CTL (9QH)
- manual transfer on the ground, the 28VDC power supply for the 20QJ channel is supplied from the FUELLING BUS via C/B-HIGH LEVEL SUPPLY (1QJ).
- defuel AMM 28-25-00-650-001 or transfer AMM 28-25-00-869-001 the fuel, to decrease the fuel quantity, if necessary.
NOTE: This is to make sure that the CTR TK high level sensor 20QJ is dry.
(b) Make sure that the refuel panel door 192MB/522KB/622KB is open, and/or cockpit refuel is set to on. (c) Remove the FLSCU-1 (7QJ) AMM 28-46-34-000-001.
(d) Do a test, with a multimeter, to make sure 28VDC is available at the rack connector AA, pin 1B.
(e) Open, safety and tag the C/B-HIGH LEVEL SUPPLY (1QJ).
(f) Do a test, with a multimeter, to make sure 28VDC is not available at the rack connector AA, pin 1B.
(g) Do the Simulation of Flight with the Aircraft on the Ground AMM 32-69-00-860-001 for:
1 LGCIU-1 (5GA1).
2 NOSE + LH + RH.
3 UPLOCKED.
NOTE: The Simulation of Flight is necessary to put the 28VDC supply to the FLSCU-1, level sense channel 7 (LS7) in the flight configuration. In the flight phase (weight off) the 28VDC is supplied from C/B-ACT1/XFR VALVE/AUTO CTL (9QH), via the RELAY-PANEL (802VU), and the RELAY-50QJ.
(h) Do a test, with a multimeter, to make sure 28VDC is available at the rack connector AA, pin 1B. (i) If the test results are, as specified in (d), (f) and (h):
1 Install the FLSCU-1 (7QJ) AMM 28-46-34-400-001 removed in step (c).
2 Remove tag and close the C/B-HIGH LEVEL SUPPLY (1QJ).
3 Go to step (10).
(j) If the test results are, not as specified in (d), (f) and (h), do the trouble-shooting as follows:
1 Do a check of and replace, if necessary:
- the RELAY-FLSCU 1 SUPPLY [50QJ]
- the LGCIU-1 [5GA1] AMM 32-31-71-000-001 and AMM 32-31-71-400-001.
2 Do a check of the aircraft wiring ASM 282501 between:
- the RELAY-PANEL (802VU) free connector 4065VC, pin P and the RELAY-FLSCU 1 SUPPLY (50QJ), terminal A1 and terminal X1
- the LGCIU-1 (5GA1) rack connector AB, pin 8E and the RELAY-FLSCU 1 SUPPLY (50QJ), terminal X2.
b Do the test given in Para. 3.C.
3 If the fault continues, replace the RELAY-PANEL (802VU) AMM 25-71-11-000-001 and AMM 25-71-11-400-001.
- If there is no relay panel available, go to step 4_.
4 If the fault continues, do the step 5_ or the step 6_ as applicable:
5 Do a check of and replace, if necessary, the RELAY-POWER SUPPLY SWITCH [39QU] .
6 Do a check of the RELAY-PANEL (802VU) wiring between the connector to relay lines, as shown in the table that follows:
NOTE: The circuit connections shown in the table are abbreviated, for example:
- the connector 4065VC, pin <G is shown as 4065VC-<G
- the RELAY-POWER SUPPLY SWITCH (39QU), terminal C3 is shown as RL 39QU-C3.
| CONNECTOR-PIN | RELAY-TERMINAL | TO RELAY-TERMINAL | CONNECTOR-PIN |
|---|---|---|---|
| 4065VC-<G | RL 39QU-C3 | ||
| RL 39QU-C2 | 4065VC-P |
b Do the test given in Para. 3.C.
c Do the Simulation of Flight with the Aircraft on the Ground and return the aircraft to the ground configuration AMM 32-69-00-860-001.
(10) Do the SFCC-1 (21CV) and SFCC-2 (22CV) slats input to RELAY-PANEL (802VU) trouble-shooting as follows:
NOTE: The inputs from each of the SFCCs are connected in parallel to the RELAY-PANEL (802VU).
(a) Remove the SFCC-1 (21CV) and the SFCC-1 (22CV) AMM 27-51-34-000-001. (b) Do a check of the aircraft wiring ASM 282803 between:
- the RELAY-PANEL (802VU) free connector 4065VC-A, pin <K and the SFCC-1 and SFCC-2 rack connectors AE, pin 10H.
(d) Install the SFCC-1 (21CV) AMM 27-51-34-400-001.
(e) Make sure that the slats are extended to more than 16 degrees:
- if necessary do Extending the Slats on the Ground AMM 27-80-00-866-004.
This test must show continuity.
(g) Retract the slats to less than 16 degrees AMM 27-80-00-866-005.
NOTE: This will let the ACT auto fuel transfer operate.
(h) Use a multimeter to do a test for continuity, at the free connector 4065VC-A between the pin <K and a suitable ground ASM 282803. This test must show an open circuit.
(i) If the test results (for SFCC-1) are:
1 As specified in (f) and (h):
- go to step (j).
- replace the SLAT/FLAP CONTR.COMP. [21CV] AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
(k) Do the steps (e) thru (h) to test the SFCC-2.
(l) If the test results (for SFCC-2) are:
1 As specified in (f) and (h):
- go to step (11).
- replace the SLAT/FLAP CONTR.COMP. [22CV] AMM 27-51-34-000-001 and AMM 27-51-34-400-001.
(11) Do the LGCIU-1 (5GA1) ground/flight input to RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Use a multimeter to do a test for continuity, at the free connector 4065VC-A between the pin V and a suitable ground ASM 282803 and ASM 326201.
This test must show continuity.
(b) Do the Simulation of Flight with the Aircraft on the Ground AMM 32-69-00-860-001 for:
1 LGCIU-1 (5GA1).
2 NOSE + LH + RH.
3 UPLOCKED.
(c) Use a multimeter to do a test for continuity, at the free connector 4065VC-A between the pin V and a suitable ground ASM 282803 and ASM 326201.
This test must show an open circuit.
(d) If the test results are:
1 As specified in (a) and (c):
- go to step (12).
a Remove the LGCIU-1 (5GA1) AMM 32-31-71-000-001.
b Do a check of the aircraft wiring ASM 282803 and ASM 326201 between:
- the RELAY-PANEL (802VU) free connector 4065VC-A, pin V and the LGCIU-1 (5GA1) rack connector AB, pin 7A.
d If there is no fault in the aircraft wiring, replace the LGCIU-1 [5GA1] with a serviceable item and install AMM 32-31-71-400-001.
e Do the test given in Para. 3.C.
(12) Connect the free connector 4065VC-A to the RELAY-PANEL (802VU).
(Inputs from external systems required for a two ACT system auto fuel transfer are correct).
(13) Do the steps that follow. This will let the ACT AUTO transfer sequence start.
(a) Release out the P/BSW-FUEL/ACT/AUTO (24QH).
(b) Make sure that the ACT 1 contains more than 250 kg (560 lb) of fuel.
(c) Make sure that the ACT 2 contains more than 250 kg (560 lb) of fuel.
(d) Make sure that the center tank contains less than 6000 kg (13220 lb) of fuel.
(e) Make sure that the slats are retracted AMM 27-80-00-866-005.
(f) Close the Refuel Panel door.
(g) Do the Simulation of Flight with the Aircraft on the Ground AMM 32-69-00-860-001.
(14) Connect the RIN28108706000 TESTBOX-ACT 802VU to the RELAY PANEL (802VU).
- Use a clamp to connect the test box to the nearest bonding cable to electrically ground it.
NOTE: The lights on the test box will come on if there is 28VDC on the applicable pin.
(a) On the testbox, do a check of the Flight/Ground Relay NLG 17QH (Pin L) Flight (28V) light. NOTE: This test pin allows a check to be made of the conditions that follow:
(b) If the light comes on there is 28VDC is available at pin L: - RELAY 17QH de-energized
- RELAY 22QH coil supplied with 28VDC.
1 Go to step (15).
NOTE: Make sure that the time between the step (13)(g) and the step (15) is more than ten (10) minutes.
(c) If the light does not come on replace the RELAY-PANEL (802VU) AMM 25-71-11-000-001 and AMM 25-71-11-400-001. - If there is no relay panel available, go to step 2_.
2 Do a check of ASM 282803 and replace, if necessary, the RELAY-LOW LEVEL OVERRIDE, ACT [17QH] .
3 Do a check of the RELAY-PANEL (802VU) wiring ASM 282803 between the connector to relay and relay to relay lines, as shown in the table that follows:
NOTE: The circuit connections shown in the table are abbreviated, for example:
- the connector 4068VC, pin L is shown as 4068VC-L
- the RELAY-LO LVL OVERRIDE, ACT (17QH), terminal A3 is shown as RL 17QH-A3.
| CONNECTOR-PIN | RELAY-TERMINAL | TO RELAY-TERMINAL | CONNECTOR-PIN |
|---|---|---|---|
| 4068VC-L | RL 17QH-A3 | ||
| RL 17QH-A3 | RL 22QH-X1 | ||
| 4065VC-<G | RL 17QH-A2 | ||
| 4065VC-<G | RL 17QH-X1 | ||
| 4065VC-V | RL 17QH-X2 |
b Do the test given in Para. 3.C.
(15) On the testbox, do a check of the Auto Transfer (pin V) Active light.
NOTE: This step makes sure the operation of the ten (10) minute time delay RELAY-XFR CTL, ACT (22QH).
The ten minutes starts when the two signals that follow occur together (AND gated):
(a) If the light comes on there is 28VDC at pin V. The ten minutes starts when the two signals that follow occur together (AND gated):
- the aircraft goes to flight or flight simmulation phase
- the center tank is dry.
- the ACT 1 not low level
- the slats are at less than 16 degrees.
- go to step (16).
- If there is no relay panel available, go to step 2_.
2 Do a check of ASM 282803 and replace, if necessary:
3 Do a check of the RELAY-PANEL (802VU) wiring ASM 282803 between the connector to relay and relay to relay lines, as shown in the table that follows:
NOTE: The circuit connections shown in the table are abbreviated, for example:
- the connector 4068VC, pin V is shown as 4068VC-V
- the RELAY-XFR CTL, ACT (22QH), terminal A1 is shown as RL 22QH-A1.
| CONNECTOR-PIN | RELAY-TERMINAL | TO RELAY-TERMINAL | CONNECTOR-PIN |
|---|---|---|---|
| 4068VC-V | RL 22QH-A1 | ||
| RL 22QH-A2 | RL 15QH-A2 | ||
| RL 15QH-A3 | RL 13QH-A3 | ||
| RL 13QH-A2 | 4065VC-<M | ||
| RL 13QH-A2 | 4065VC-<T |
b Do the test given in Para. 3.C.
(16) On the testbox, do a check of the Relay 37QU (Refuel Inhibit, ACT1 (Pin T) not engaged light.
NOTE: This step checks that there is no input signal (ground) to the RELAY-INLET VALVE CTL, ACT 1 (19QH) coil at terminal X2, in auto transfer configuration.
(a) If the light does not come on there is no 28VDC available at pin T: - go to step (17).
- If there is no relay panel available, go to step 2_.
2 Do a check of ASM 282803 and replace, if necessary:
- the
[14QH] - the RELAY-MANUAL TRANSFER, ACT [16QH]
- the RELAY-REFUEL/TRANSFER CONTROL, ACT1 [35QU]
- the RELAY-SEQUENCE [18QH]
- the RELAY-REFUEL INHIBIT, ACT1 [37QU] .
NOTE: The circuit connections shown in the table are abbreviated, for example:
- the connector 4068VC, pin T is shown as 4068VC-T
- the RELAY-INLET VALVE CTL, ACT 1 (19QH), terminal X2 is shown as RL 19QH-X2.
| CONNECTOR-PIN | RELAY-TERMINAL | TO RELAY-TERMINAL | CONNECTOR-PIN |
|---|---|---|---|
| 4068VC-T | RL 19QH-X2 | ||
| RL 19QH-X2 | RL 37QU-A3 | ||
| RL 37QU-A2 | RL 35QU-C2 | ||
| RL 35QU-C3 | RL 18QH-D3 | ||
| RL 18QH-D2 | RL 16QH-A2 | ||
| RL 16QH-A3 | RL 22QH-A1 | ||
| RL 16QH-A3 | 4068VC-V |
NOTE: The input control logic up to this step was checked in the previous step.
a Repair all the unserviceable wiring and connectors. b Do the test given in Para. 3.C.
(17) On the testbox, do a check of the Inlet Valve ACT. ACT1 (5QH1) (CMD) OPEN light (Pin <A).
NOTE: This step will make sure the output of the relay logic to the ACT 1 inlet valve operates.
(a) If the light does not come on, there is no 28VDC available at pin <A: - go to step (18).
- If there is no relay panel available, go to step 2_.
2 Do a check of ASM 282801 and replace, if necessary:
- the RELAY- INLET VALVE CONTROL, ACT1 [19QH]
- the RELAY-REFUEL/TRANSFER CONTROL, ACT1 [35QU]
- the RELAY-POWER SUPPLY SWITCH [39QU] .
NOTE: The circuit connections shown in the table are abbreviated, for example:
- the connector 4068VC, pin <A is shown as 4068VC-<A
- the RELAY-INLET VALVE CTL, ACT 1 (19QH), terminal C1 is shown as RL 19QH-C1.
| CONNECTOR-PIN | RELAY-TERMINAL | TO RELAY-TERMINAL | CONNECTOR-PIN |
|---|---|---|---|
| 4068VC-<A | RL 19QH-C1 | ||
| RL 19QH-C1 | 4065VC-<H | ||
| RL 19QH-C2 | RL 35QU-B3 | ||
| RL 35QU-B2 | RL 39QU-C2 | ||
| RL 39QU-C3 | 4065VC-<G |
b Do the test given in Para. 3.C.
(18) On the testbox, do a check of the Sequenc Relay 18QH (Pin E) ACT1 Transfer (28VDC) light.
NOTE: This step will make sure that the sequence relay 18QH is in an energized state (shows that ACT 2 is selected for fuel transfer).
(a) If the light does not come on, there is no 28VDC available at pin E: - go to step (19).
- Do ACT 2 Sequence Failure (Ref. TSM TASK 28-28-00-810-807).
NOTE: This step will make sure the open command of the relay logic to the ACT 2 inlet valve operates.
(a) If the light comes on there is 28VDC available at pin P: - go to step (20).
- If there is no relay panel available, go to step 2_.
2 Do a check of ASM 282801 and replace, if necessary:
- the RELAY-INLET VALVE CONTROL, ACT2 [20QH]
- the RELAY-REFUEL/TRANSFER CONTROL, ACT2 [36QU]
- the RELAY-POWER SUPPLY SWITCH [39QU] .
NOTE: The circuit connections shown in the table are abbreviated, for example:
- the connector 4068VC, pin P is shown as 4068VC-P
- the RELAY-INLET VALVE CTL, ACT 2 (20QH), terminal C1 is shown as RL 20QH-C1.
| CONNECTOR-PIN | RELAY-TERMINAL | TO RELAY-TERMINAL | CONNECTOR-PIN |
|---|---|---|---|
| 4068VC-p | RL 20QH-C1 | ||
| RL 20QH-C1 | 4065VC-G | ||
| RL 20QH-C2 | RL 36QU-B3 | ||
| RL 36QU-B2 | RL 39QU-D2 | ||
| RL 39QU-D3 | 4065VC-H |
| CONNECTOR-PIN | RELAY-TERMINAL | TO RELAY-TERMINAL | CONNECTOR-PIN |
|---|---|---|---|
| RL 20QH-X2 | RL 38QU-A3 | ||
| RL 38QU-A2 | RL 36QU-C2 | ||
| RL 36QU-C3 | RL 18QH-D1 |
a Repair all the unserviceable wiring and connectors.
b Do the test given in Para. 3.C.
(20) On the testbox, do a check of the Air Shut Off Vave (CMD) (3QH) OPEN light.
NOTE: This step will make sure the open command of the relay logic to the actuator air shut-off valve - RELAY-28QH de-energized, operates.
(a) If the light comes on the, there is 28VDC available at pin Y. - go to step (21).
- If there is no relay panel available, go to step 2_.
2 Do a check of ASM 282804 and replace, if necessary:
- the RELAY-PRESSURIZATION CONTROL, ACT [28QH]
- the RELAY-LOW LEVEL OVERRIDE, ACT [17QH]
- the RELAY-TRANSFER CONTROL, ACT [22QH]
- the RELAY-POWER SUPPLY SWITCH [39QU] .
NOTE: The circuit connections shown in the table are abbreviated, for example:
- the connector 4068VC, pin Y is shown as 4068VC-Y
- the RELAY-PRESS CTL, ACT (28QH), terminal A3 is shown as RL 28QH-A3.
| CONNECTOR-PIN | RELAY-TERMINAL | TO RELAY-TERMINAL | CONNECTOR-PIN |
|---|---|---|---|
| 4068VC-Y | RL 28QH-A3 | ||
| RL 28QH-A3 | 4065VC-X | ||
| RL 28QH-A2 | RL 39QU-C2 | ||
| RL 28QH-X1 | RL 22QH-B2 | ||
| RL 39QU-C3 | 4065VC-<G | ||
| RL 28QH-X2 | RL 17QH-C2 | ||
| RL 28QH-X2 | RL 28QH-B2 | ||
| RL 28QH-X2 | 4065VC-K |
b Do the test given in Para. 3.C.
(21) If the fault continues, examine the see/feel indicators of the actuators shown in the table that follows:
| ACTUATOR FUNCTIONAL DESIGNATION | FIN | CORRECT AUTO XFR POSITION | IF ACTUATOR NOT AT THE CORRECT AUTO XFR POSITION, GO TO THE TROUBLE-SHOOTING STEP SHOWN BELOW |
|---|---|---|---|
| FUEL XFR VALVE | 6QH | OPEN | (23) |
| FUEL INLET VALVE, ACT 1 | 5QH1 | CLOSED | (24) |
| AIR SHUT OFF VALVE | 3QH | OPEN | (25) |
| VENT VALVE, ACT 1 | 4QH1 | CLOSED | (27) |
| FUEL INLET VALVE, ACT 2 | 5QH2 | OPEN | (28) |
| VENT VALVE, ACT 2 | 4QH2 | CLOSED | (29) |
NOTE: The actuator/valve positions shown are only correct when the ACT automatic transfer is on and the two ACTs each contain more than 80 kg (176.3698 lb) of fuel.
That is when:
(22) If all the actuators in the table are in the correct position for the start of a two ACT automatic transfer: That is when:
- the ACT auto transfer is set to on (P/BSW-FUEL/ACT/AUTO (24QH) released out)
- the center tank is not full (high level sensor dry)
- the two low level sensors in ACT 1 are wet
- the two low level sensors in ACT 2 are wet
- the sequence relay (18QH) energized initially when on the ground and at weight off (flight) is held latched
- the slats are set to less than 16 degrees (slats fully retracted)
- the aircraft is simulated in flight AMM 32-69-00-860-001
- ten (10) minutes have elapsed since the functions that follow occured (AND gated), the aircraft simulated in flight, the center tank high level sensor dry.
- go to step (30).
(a) Disconnect the ACTUATOR FUEL XFR VALVE (6QH) free connector 6QH-A.
(b) Do a test, with a multimeter, at the free connector 6QH-A, between the pins A (+ve) and E (-ve) ASM 282802 to see if 28VDC is available.
NOTE: In ACT automatic transfer only the MOTOR 1 of actuator 6QH is supplied with 28VDC to move the valve to open.
1 If the voltage is correct do a check of and replace, if necessary: a The ACTUATOR-FUEL TRANSFER VALVE, ACT [6QH] AMM 28-28-53-000-001 and AMM 28-28-53-400-001.
b The VALVE-FUEL TRANSFER, ACT [165QM] AMM 28-28-33-000-001 and AMM 28-28-33-400-001.
2 If the voltage is not correct:
a Do a check of the aircraft wiring ASM 282803 between:
- the Actuator Fuel XFR Valve, ACT free connector 6QH-A, pin A and the RELAY-PANEL (802VU) free connector 4065VC-A, pin <Q
- the Actuator Fuel XFR Valve, ACT free connector 6QH-A, pin E and the ground DC1.
c Do the test given in Para. 3.C.
(24) Do the Actuator Fuel Inlet Valve, ACT 1 (5QH1) automatic transfer trouble-shooting as follows:
(a) An aircraft wiring check between the Inlet Valve Actuator and the RELAY-PANEL (802VU) is not applicable. This is because the same wires are used for an auto ACT transfer as for a manual ACT transfer:
- refer to ACT Manual Transfer (On The Ground Failure) (Ref. TSM TASK 28-28-00-810-802).
(a) Disconnect the AIR SHUTOFF VALVE (3QH) free connector 3QH-A.
(b) Do a test, with a multimeter, at the free connector 3QH-A, between the pins A (+ve) and E (-ve) ASM 282804 to see if 28VDC is available.
1 If the voltage is correct, do a check of and replace, if necessary:
a The ACTUATOR-AIR SHUTOFF VALVE, ACT [3QH] AMM 28-28-56-000-001 and AMM 28-28-56-400-001.
b The VALVE-AIR SHUTOFF, ACT [168QM] AMM 28-28-36-000-001 and AMM 28-28-36-400-001.
2 If the voltage is not correct:
a Do a check of the aircraft wiring ASM 282804 between:
- the Actuator Air Shutoff Valve free connector 3QH-A, pin A and RELAY-PANEL (802VU) free connector 4065VC-A, pin X
- the Actuator Air Shutoff Valve free connector 3QH-A, pin E and ground point DC1.
c Do the test given in Para. 3.C.
(26) If the fault continues:
(a) Do a check of and replace, if necessary, the
(b) Do the test given in Para. 3.C.
(27) Do the Actuator Vent Valve, ACT 1 (4QH1) automatic transfer trouble-shooting as follows:
(a) Make sure that the Actuator Air Shut-off Valve free connector 3QH-A is connected to the 3QH receptacle.
NOTE: This step is necessary because the vent valve shut 28VDC is sourced from the air shut-off valve actuator when powered to open.
(b) Disconnect the ACTUATOR VENT VALVE, ACT 1 (4QH1) free connector 4QH1-A. (c) Do a test, with a multimeter, at the free connector 4QH1-A, between the pins B (+ve) and E (-ve) ASM 282804 to see if 28VDC is available.
1 If the voltage is correct do a check of and replace, if necessary:
a The ACTUATOR-VENT VALVE, ACT1 [4QH1] AMM 28-28-55-000-001 and AMM 28-28-55-400-001.
b The VALVE-VENT, ACT1 [167QM1] AMM 28-28-35-000-001 and AMM 28-28-35-400-001.
2 If the voltage is not correct do a check of and replace, if necessary:
a The ACTUATOR-AIR SHUTOFF VALVE, ACT [3QH] AMM 28-28-56-000-001 and AMM 28-28-56-400-001.
NOTE: This step is necessary because even if the actuator has taken up the correct position, the open microswitch and/or wiring may have failed.
b If the fault continues, do a check of the aircraft wiring ASM 282804 between: - the Actuator Air Shutoff Valve free connector 3QH-A, pin C and the ACT to aircraft tank break connector 7619VC1, pin 19
- the ACT to aircraft tank break free connector 7619VC1-A, pin 19 and the Actuator Vent Valve, free connector 4QH1-A, pin B
- the ACT to aircraft tank break connector 7619VC1, pin 8 and the ground point DC1
- the ACT to aircraft tank break free connector 7619VC1-A, pin 8 and the Actuator Vent Valve, free connector 4QH1-A, pin E.
d Do the test given in Para. 3.C.
(28) Do the Actuator Fuel Inlet Valve, ACT 2 (5QH2) automatic transfer trouble-shooting as follows:
(a) An aircraft wiring check between the Inlet Valve Actuator and the RELAY-PANEL (802VU) is not applicable as the same lines are used for an auto ACT transfer as for a manual ACT transfer:
- refer to ACT Manual Transfer (On The Ground Failure) (Ref. TSM TASK 28-28-00-810-802).
(a) Make sure that the Actuator Air Shut-off Valve free connector 3QH-A is connected to the 3QH receptacle.
NOTE: This step is necessary because the vent valve shut 28VDC is sourced from the air shut-off valve actuator when powered to open.
(b) Disconnect the ACTUATOR VENT VALVE, ACT 2 (4QH2) free connector 4QH2-A. (c) Do a test, with a multimeter, at the free connector 4QH2-A, between the pins B (+ve) and E (-ve) ASM 282804 to see if 28VDC is available.
1 If the voltage is correct do a check of and replace, if necessary:
a The ACTUATOR-VENT VALVE, ACT2 [4QH2] AMM 28-28-55-000-001 and AMM 28-28-55-400-001.
b The VALVE-VENT, ACT2 [167QM2] AMM 28-28-35-000-001 and AMM 28-28-35-400-001.
2 If the voltage is not correct and the actuator vent valve, ACT 1 (4QH1) has also failed to close, do a check of and replace, if necessary:
a The ACTUATOR-AIR SHUTOFF VALVE, ACT [3QH] AMM 28-28-56-000-001 and AMM 28-28-56-400-001.
b Do a check of the aircraft wiring ASM 282804 between:
- the Actuator Air Shutoff Valve free connector 3QH-A, pin C and the ACT to aircraft tank break connector 7619VC1, pin 19
- the aircraft tank break connector 7619VC1-A, pin 19 and the Actuator-Vent Valve, Act 1 free connector 4QH1-A, pin B
- the Actuator-Vent Valve, Act 1 free connector 4QH1-A, pin E and the aircraft tank break connector 7619VC1-A, pin 8
- the aircraft tank break connector 7619VC1, pin 8 and the ground DC1
- the Actuator Air Shutoff Valve free connector 3QH-A, pin C and the ACT to aircraft tank break connector 7619VC2, pin 19
- the aircraft tank break connector 7619VC2-A, pin 19 and the Actuator-Vent Valve, Act 2 free connector 4QH2-A, pin B
- the Actuator-Vent Valve, Act 2 free connector 4QH2-A, pin E and the aircraft tank break connector 7619VC2-A, pin 8
- the aircraft tank break connector 7619VC2, pin 8 and the ground DC1.
d Do the test given in Para. 3.C.
3 If the voltage is not correct, the actuator vent valve, ACT 2 (4QH2) has failed to close, but the actuator vent valve, ACT 1 (4QH1) is closed:
a Do a check of the aircraft ASM 282804 wiring between:
- the ACT to aircraft tank break free connector 7619VC2-A, pin 19 and the Actuator Vent Valve, free connector 4QH2-A, pin B
- the ACT to aircraft tank break connector 7619VC2, pin 8 and the ground DC1.
c Do the test given in Para. 3.C.
(30) Make sure that the aircraft to ACT tank break air line connections are tight and free from twists, at the ACT 1 and the ACT 2.
(31) Do the Functional Test of the ACT Pressure Reducing Valve AMM 28-28-00-720-001.
(32) If the air pressure is not to the specification:
- replace the VALVE-PRESSURE REDUCING, ACT1 [171QM] AMM 28-28-42-000-001 and AMM 28-28-42-400-001.
(a) The AIR FILTER-CABIN INTAKE, ACT PRESSURIZATION [183QM] AMM 28-28-39-000-001 and AMM 28-28-39-400-001.
(b) The CHECK VALVE-CABIN AIR INTAKE, ACT PRESSURIZATION [179QM] .
(c) The CHECK VALVE-ACT PRESSURIZATION [178QM] .
(d) The air lines and connections for damage or loose connections.
(e) Do the test given in Para. 3.C.
(34) If the fault continues, do a check of and replace, if necessary, items of the ACT pressurization system as follows:
(a) The PROTECTOR-OVERPRESSURE, ACT1 [170QM1] ( PROTECTOR-OVERPRESSURE, ACT2 [170QM2] ) AMM 28-12-55-000-001 and AMM 28-12-55-400-001.
NOTE: If the protector-overpressure (burst disc) has operated it is not possible to pressurize an ACT.
(b) Do a test of the applicable VALVE-PRESSURE HOLDING, ACT1 [191QM1] ( VALVE-PRESSURE HOLDING, ACT2 [191QM2] ) AMM 28-28-00-710-016. 1 Replace, if necessary, AMM 28-28-48-000-001 and AMM 28-28-48-400-001.
(c) The VALVE-INWARD PRESSURE RELIEF, ACT1 [172QM1] ( VALVE-INWARD PRESSURE RELIEF, ACT2 [172QM2] ) AMM 28-12-56-000-001 and AMM 28-12-56-400-001.
NOTE: If the valve-inward pressure relief is not completely closed it is not possible to pressurize an ACT.
(d) The CHECK VALVE-ACT PRESSURIZATION [177QM1] ( CHECK VALVE-ACT2 [177QM2] ). NOTE: If the check valve does not open it is not possible to pressurize an ACT.
(e) Do the test given in Para. 3.C.