DOC AIRBUS | TSM A320FFuel - ACT 1 Manual Transfer Failure (In Flight)
TASK 28-28-00-810-803-A
Fuel - ACT 1 Manual Transfer Failure (In Flight)
A. Fixtures, Tools, Test and Support Equipment
B. Referenced Information
3. Fault Confirmation
Subtask 28-28-00-865-078-A ** ON A/C NOT FOR ALL
Subtask 28-28-00-810-052-B ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:28:50 UTC
Fuel - ACT 1 Manual Transfer Failure (In Flight)
WARNING:
OBEY THE FUEL SAFETY PROCEDURES.
1. Possible Causes- aircraft wiring
- LGCIU-1 [5GA1]
- C/B-ACT1/CTL & SPLY [9QH]
- SWITCH-INDICATOR, ACT [24QH]
- C/B-ACT XFR VALVE MAN CTL [30QH]
- CONTACTOR-ACT PUMP SUPPLY [26QH]
- ACTUATOR-FUEL TRANSFER VALVE, ACT [6QH]
- VALVE-FUEL TRANSFER, ACT [165QM]
- RELAY-TRANSFER VALVE CONTROL, ACT [21QH]
- RELAY- INLET VALVE CONTROL, ACT1 [19QH]
- RELAY-SEQUENCE [18QH]
- RELAY-POWER SUPPLY SWITCH [39QU]
- ACTUATOR-FUEL INLET VALVE, ACT1 [5QH1]
- VALVE-FUEL INLET, ACT1 [166QM1]
- RELAY-REFUEL/TRANSFER CONTROL, ACT1 [35QU]
- RELAY-REFUEL INHIBIT, ACT1 [37QU]
- RELAY-MANUAL TRANSFER, ACT [16QH]
- RELAY-LOW LEVEL OVERRIDE, ACT [17QH]
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | MULTIMETER - STANDARD |
| REFERENCE | DESIGNATION |
|---|---|
| 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 32-31-00-810-802-A | LGCIU Fault |
| 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 |
| ASM 282501 | |
| AMM 28-28-00-710-001 | Operational Check of the ACT Manual Transfer System |
| ASM 282801 | |
| AWM 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 28-28-34-000-001 | Removal of the ACT Fuel Inlet Valve (166QM) |
| AMM 28-28-34-400-001 | Installation of the ACT Fuel Inlet Valve (166QM) |
| AMM 28-28-54-000-001 | Removal of the ACT Fuel Inlet Valve Actuator (5QH) |
| AMM 28-28-54-400-001 | Installation of the ACT Fuel Inlet Valve Actuator (5QH) |
| ASM 284601 | |
| ASM 326201 | |
| AMM 32-69-00-860-001 | Simulation of Flight (With Aircraft on Ground) |
Subtask 28-28-00-865-078-A ** ON A/C NOT FOR ALL
A. Table of the circuit breakers referred to in this procedure:
Subtask 28-28-00-710-052-A ** ON A/C NOT FOR ALL | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 121VU | ACT XFR VALVE MAN CTL | 30QH | N29 |
| 121VU | ACT1/CTL & SPLY | 9QH | P29 |
| 121VU | ACT2/CTL & SPLY | 10QH | P28 |
B. Test
(1) Do the Operational Test of the ACT Manual Transfer System AMM 28-28-00-710-001.
4. Fault Isolation(1) Do the Operational Test of the ACT Manual Transfer System AMM 28-28-00-710-001.
NOTE: When the aircraft is in flight or flight simulation, and in the ACT XFR FWD - Manual Mode, fuel can be transferred FWD even with the center tank full.
That is when the center tank high level sensor 20QJ is wet.
That is when the center tank high level sensor 20QJ is wet.
NOTE: For the Simulation of Flight, with the Aircraft on the Ground AMM 32-69-00-860-001.
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)
- Aircraft Schematic Manual (ASM), ACT XFR System, Inlet Valve ASM 282801
- AWM, ACT XFR System, Manual XFR AWM 282802
- ASM, ACT XFR System, Transfer Valve ASM 282803
- ASM, ACT XFR System, Vent Valves ASM 282804
- ASM, FLSS, High Level Refuel Control ASM 284601.
Subtask 28-28-00-810-052-B ** ON A/C NOT FOR ALL
A. Procedure
(1) If the ACT transfer pump shows a low pressure indication:
(a) Disconnect the free connectors 4065VC-A and 4066VC-A from the RELAY-PANEL (802VU).
(b) Do a continuity test, with a MULTIMETER - STANDARD, AWM 282802 and ASM 282803 between:
(c) If the test results are:
1 As specified:
a Do a check of the aircraft wiring (ground lines) AWM 282802 and ASM 282803 between:
c Connect the free connectors 4065VC-A and 4066VC-A to the RELAY-PANEL (802VU).
d Do the test given in Para. 3.B.
(3) The FLSCU-1 (7QJ), CHAN 7 - CTR TK HI LVL SENSOR (20QJ) input to RELAY-PANEL (802VU) is switched out by the action of RELAY-LOW LEVEL OVERRIDE, ACT (17QH) B contacts when the aircraft goes to the flight phase. If the center tank is full of fuel, a ground applied by the B3 contact lets the ACT manual fuel transfer continue when the aircraft is in flight.
The FLSCU-1 (7QJ), CHAN 7 - CTR TK HI LVL SENSOR (20QJ) input to RELAY-PANEL (802VU) trouble-shooting is thus not applicable.
The trouble-shooting with reference to the line via the B contacts of the relay (17QH) is in step (25).
(4) Do the LGCIU-1 [5GA1] input to RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Disconnect the free connector 4065VC-A from the RELAY-PANEL (802VU).
(b) Do a continuity test, with a multimeter, ASM 282803 and ASM 326201 at the free connector 4065VC-A, between the pin V and a suitable ground.
This test should show a low resistance.
(c) 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.
(d) Do a continuity test, with a multimeter, ASM 282803 and ASM 326201 at the free connector 4065VC-A, between the pin V and a suitable ground.
This test should show a high resistance/open circuit.
(e) If the test results are:
1 As specified in (b) and (d):
a Do a check of the aircraft wiring (FLIGHT/GROUND line) ASM 282803 and ASM 326201 between:
c Do the test given in Para. 3.B.
d If the fault from the LGCIU-1 input continues:
(5) Do the 28VDC Normal Supply, ACT 1, input to RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Do a test, with a multimeter, ASM 282801 to make sure that 28VDC is available at the free connector 4065VC-A, pin <G.
(b) If the 28VDC:
1 Is available:
a Do a check of ASM 282801 and replace if necessary:
d Do the test given in Para. 3.B.
(6) Do the 28VDC ACT Manual XFR Control (28VDC Switched) Supply, input to RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Make sure the P/BSW-FUEL/ACT/AUTO (24QH) is set to FWD (pushed) in.
(b) Do a test, with a multimeter, AWM 282802 to make sure that 28VDC is available at the free connector 4066VC-A, pin P.
(c) If the 28VDC:
1 Is available:
a Do a check of AWM 282802 and replace if necessary:
b Do a check of the aircraft wiring AWM 282802 between:
d Do the test given in Para. 3.B.
(7) Do the 28VDC Pump Contactor Closed Supply, input to RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Make sure the P/BSW-FUEL/ACT/AUTO (24QH) is set to FWD (pushed) in.
(b) Do a test, with a multimeter, AWM 282802 to make sure that 28VDC is available at the free connector 4066VC-A, pin N.
(c) If the 28VDC:
1 Is available:
a Do a check of AWM 282802 and replace if necessary:
d Do the test given in Para. 3.B.
(8) Make sure the ACT fuel transfer system is set as follows:
(a) Open, safety and tag the C/B-ACT2/XFR VLV/AUTO CTL (10QH).
(c) The P/BSW-FUEL/ACT/AUTO (24QH) is set to FWD (pushed) in.
(9) If the fault continues, examine the see/feel indicators of the actuators shown in the table that follows:
(b) Examine the C/B-ACT XFR VALVE MAN CTL (30QH) and make a record if it is open.
(c) Examine the items that follow for signs of damage:
(e) Close the C/Bs if they were open in (a) and (b).
(f) Do the test given in Para. 3.B.
(11) If the fault continues:
(a) Make sure the white FWD legend comes on.
(14) Disconnect the electrical supply cable connector 6QH-B from the ACTUATOR-FUEL XFR VALVE, ACT (6QH).
(15) Do a test, with a multimeter, AWM 282802 to make sure that the 28VDC supply is available at the connector 6QH-B between the pins as shown in the table that follows.
(16) If the 28VDC supply at:
(a) The two connectors, steps (13), and (15) is as specified:
1 Replace the ACTUATOR-FUEL TRANSFER VALVE, ACT [6QH] AMM 28-28-33-000-001 and AMM 28-28-33-400-001.
2 If the fault continues:
(c) Connector 6QH-B (MOTOR 2) step (15), is not as specified go to step (19).
(17) Do the ACTUATOR-FUEL XFR VALVE, ACT (6QH) MOTOR 1 28VDC Open Supply Trouble-shooting as follows:
(a) Do a check of the aircraft wiring ASM 282803 between:
(c) Do the test given in Para. 3.B.
(18) If the fault continues, replace the RELAY-PANEL (802VU) AMM 25-71-11-000-001 and AMM 25-71-11-400-001.
(a) Do a check of ASM 282803 ASM 282501 and replace if necessary:
1 Repair all the unserviceable wiring and connectors.
2 Do the test given in Para. 3.B.
(20) Do the ACTUATOR-FUEL XFR VALVE, ACT (6QH) MOTOR 2 28VDC Open Supply trouble-shooting as follows:
(a) Do a check of the aircraft wiring AWM 282802 between:
(c) Do the test given in Para. 3.B.
(21) If the fault continues:
1 Repair all the unserviceable wiring and connectors.
2 Do the test given in Para. 3.B.
(22) Do the Actuator Fuel Inlet Valve, ACT 1 (5QH1) Manual Transfer 28VDC Open Supply trouble-shooting as follows:
(a) Examine the C/B-ACT1/XFR VALVE/AUTO CTL (9QH) and make a record if it is open.
(b) Examine for signs of damage the items that follow:
(d) Close the C/B-ACT1/XFR VALVE/AUTO CTL (9QH) if it was open in step (a).
(e) Do the test given in Para. 3.B.
(23) If the fault continues:
(a) As specified in step (24):
1 Replace the ACTUATOR-FUEL INLET VALVE, ACT1 [5QH1] AMM 28-28-54-000-001 and AMM 28-28-54-400-001.
2 If the fault continues:
1 Do a check of the aircraft wiring ASM 282801 between:
3 Do the test given in Para. 3.B.
(26) If the fault continues:
1 Repair all the unserviceable wiring and connectors.
2 Do the test given in Para. 3.B.
(1) If the ACT transfer pump shows a low pressure indication:
- do the ACT Manual Transfer, Pump System Failure Trouble-shooting (Ref. TSM TASK 28-28-00-810-801).
(a) Disconnect the free connectors 4065VC-A and 4066VC-A from the RELAY-PANEL (802VU).
(b) Do a continuity test, with a MULTIMETER - STANDARD, AWM 282802 and ASM 282803 between:
- the free connector 4065VC-A, pin <M and the ground point DC1
- the free connector 4065VC-A, pin <T and the ground point DC1
- the free connector 4066VC-A, pin R and the ground point DC2
- the free connector 4066VC-A, pin V and the ground point DC2.
(c) If the test results are:
1 As specified:
- go to step (3).
a Do a check of the aircraft wiring (ground lines) AWM 282802 and ASM 282803 between:
- the free connector 4065VC-A, pin <M and the ground point DC1
- the free connector 4065VC-A, pin <T and the ground point DC1
- the free connector 4066VC-A, pin R and the ground point DC2
- the free connector 4066VC-A, pin V and the ground point DC2.
c Connect the free connectors 4065VC-A and 4066VC-A to the RELAY-PANEL (802VU).
d Do the test given in Para. 3.B.
(3) The FLSCU-1 (7QJ), CHAN 7 - CTR TK HI LVL SENSOR (20QJ) input to RELAY-PANEL (802VU) is switched out by the action of RELAY-LOW LEVEL OVERRIDE, ACT (17QH) B contacts when the aircraft goes to the flight phase. If the center tank is full of fuel, a ground applied by the B3 contact lets the ACT manual fuel transfer continue when the aircraft is in flight.
The FLSCU-1 (7QJ), CHAN 7 - CTR TK HI LVL SENSOR (20QJ) input to RELAY-PANEL (802VU) trouble-shooting is thus not applicable.
The trouble-shooting with reference to the line via the B contacts of the relay (17QH) is in step (25).
(4) Do the LGCIU-1 [5GA1] input to RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Disconnect the free connector 4065VC-A from the RELAY-PANEL (802VU).
(b) Do a continuity test, with a multimeter, ASM 282803 and ASM 326201 at the free connector 4065VC-A, between the pin V and a suitable ground.
This test should show a low resistance.
(c) 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.
(d) Do a continuity test, with a multimeter, ASM 282803 and ASM 326201 at the free connector 4065VC-A, between the pin V and a suitable ground.
This test should show a high resistance/open circuit.
(e) If the test results are:
1 As specified in (b) and (d):
- go to step (5).
a Do a check of the aircraft wiring (FLIGHT/GROUND line) ASM 282803 and ASM 326201 between:
- the free connector 4065VC, pin V and the LGCIU-1 (5GA1) rack connector AB, pin 7A.
c Do the test given in Para. 3.B.
d If the fault from the LGCIU-1 input continues:
- do the LGCIU-1 (2) Fault (Ref. TSM TASK 32-31-00-810-802).
(5) Do the 28VDC Normal Supply, ACT 1, input to RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Do a test, with a multimeter, ASM 282801 to make sure that 28VDC is available at the free connector 4065VC-A, pin <G.
(b) If the 28VDC:
1 Is available:
- go to step (6).
a Do a check of ASM 282801 and replace if necessary:
- the C/B-ACT1/CTL & SPLY [9QH] .
- the free connector 4065VC-A, pin <G and the C/B-ACT1/XFR VALVE/AUTO CTL (9QH), terminal 2.
d Do the test given in Para. 3.B.
(6) Do the 28VDC ACT Manual XFR Control (28VDC Switched) Supply, input to RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Make sure the P/BSW-FUEL/ACT/AUTO (24QH) is set to FWD (pushed) in.
(b) Do a test, with a multimeter, AWM 282802 to make sure that 28VDC is available at the free connector 4066VC-A, pin P.
(c) If the 28VDC:
1 Is available:
- go to step (7).
a Do a check of AWM 282802 and replace if necessary:
b Do a check of the aircraft wiring AWM 282802 between:
- the free connector 4066VC-A, pin P and the P/BSW-FUEL/ACT/AUTO (24QH), terminal C1
- the P/BSW-FUEL/ACT/AUTO (24QH), terminal C3 and the C/B-ACT XFR VALVE MAN CTL (30QH), terminal 2.
d Do the test given in Para. 3.B.
(7) Do the 28VDC Pump Contactor Closed Supply, input to RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Make sure the P/BSW-FUEL/ACT/AUTO (24QH) is set to FWD (pushed) in.
(b) Do a test, with a multimeter, AWM 282802 to make sure that 28VDC is available at the free connector 4066VC-A, pin N.
(c) If the 28VDC:
1 Is available:
- go to step (8).
a Do a check of AWM 282802 and replace if necessary:
- the CONTACTOR-ACT PUMP SUPPLY [26QH] .
- the free connector 4066VC-A, pin N and the CONTACTOR-ACT PUMP SUPPLY (26QH), terminal 3.
d Do the test given in Para. 3.B.
(8) Make sure the ACT fuel transfer system is set as follows:
(a) Open, safety and tag the C/B-ACT2/XFR VLV/AUTO CTL (10QH).
NOTE: This is to prevent the RELAY-SEQUENCE (18QH) from energizing and to command the ACT 1 inlet valve actuator (5QH1) to open.
This procedure overrides:
(b) The free connectors 4065VC-A, and 4066VC-A are connected to their related receptacles on the RELAY-PANEL (802VU). This procedure overrides:
- the related fuel level sense system input from ACT 2
- the set sequence relay (18QH) control circuits.
(c) The P/BSW-FUEL/ACT/AUTO (24QH) is set to FWD (pushed) in.
(9) If the fault continues, examine the see/feel indicators of the actuators shown in the table that follows:
| ACTUATOR FUNCTIONAL DESIGNATION | FIN | CORRECT MANUAL XFR POSITION | IF ACTUATOR IS NOT AT THE CORRECT MANUAL XFR POSITION, GO TO THE TROUBLE-SHOOTING STEP SHOWN BELOW |
|---|---|---|---|
| FUEL XFR VALVE | 6QH | OPEN | (10) |
| FUEL INLET VALVE, ACT 1 | 5QH1 | OPEN | (21) |
NOTE: If AIDS or an ARINC reader is available, the actuator positions given in the table before can be monitored electronically. See ACT Manual Transfer, Pump System Failure (Ref. TSM TASK 28-28-00-810-801) for the related SDAC ARINC labels.
(10) Do the Actuator Fuel Transfer Valve (6QH) Manual XFR Trouble-shooting as follows: NOTE: When an ACT MANUAL fuel transfer FWD is selected, the ACT transfer valve will open, moved by the two actuator motors.
(a) Examine the C/B-ACT1/XFR VALVE/AUTO CTL (9QH) and make a record if it is open. (b) Examine the C/B-ACT XFR VALVE MAN CTL (30QH) and make a record if it is open.
(c) Examine the items that follow for signs of damage:
- the actuator supply cables, and end connectors 6QH-A, and 6QH-B
- the actuator electrical receptacles.
(e) Close the C/Bs if they were open in (a) and (b).
(f) Do the test given in Para. 3.B.
(11) If the fault continues:
- disconnect the electrical supply cable connector 6QH-A from the ACTUATOR-FUEL XFR VALVE, ACT (6QH).
(a) Make sure the white FWD legend comes on.
NOTE: The P/BSW-FUEL/ACT/AUTO (24QH) FAULT legend/light can come on for up to approximately ten (10) minutes if it is necessary for the fuel pump (impeller type) to prime/reprime the system. When the fuel pressure builds up sufficiently to operate the pressure switch (by the action of the ACT fuel transfer pump), the FAULT legend will go off.
During flight or flight simulation the FAULT legend/light operation is inhibited until at least one of the ACT low level sensors has been dry for four (4) minutes.
The four minute delay is the sum of the relay operation as follows:
(13) Do a test, with a MULTIMETER - STANDARD, ASM 282803 to make sure that the 28VDC supply is available at the connector 6QH-A between the pins as shown in the table that follows. During flight or flight simulation the FAULT legend/light operation is inhibited until at least one of the ACT low level sensors has been dry for four (4) minutes.
The four minute delay is the sum of the relay operation as follows:
- RELAY-LO LVL SENSE, ACT 1 (3QH), one (1) minute
- RELAY-LO PRESSURE DELAY (27QH), three (3) minutes.
| ACTUATOR SIGNAL LINE | CONNECTOR 6QH-A PIN |
|---|---|
| MOTOR 1 OPEN 28VDC SUPPLY | A |
| MOTOR 1 GROUND | E |
(15) Do a test, with a multimeter, AWM 282802 to make sure that the 28VDC supply is available at the connector 6QH-B between the pins as shown in the table that follows.
| ACTUATOR SIGNAL LINE | CONNECTOR 6QH-B PIN |
|---|---|
| MOTOR 2 OPEN 28VDC SUPPLY | A |
| MOTOR 2 GROUND | E |
(a) The two connectors, steps (13), and (15) is as specified:
1 Replace the ACTUATOR-FUEL TRANSFER VALVE, ACT [6QH] AMM 28-28-33-000-001 and AMM 28-28-33-400-001.
2 If the fault continues:
- replace the VALVE-FUEL TRANSFER, ACT [165QM] AMM 28-28-33-000-001 and AMM 28-28-33-400-001.
(c) Connector 6QH-B (MOTOR 2) step (15), is not as specified go to step (19).
(17) Do the ACTUATOR-FUEL XFR VALVE, ACT (6QH) MOTOR 1 28VDC Open Supply Trouble-shooting as follows:
(a) Do a check of the aircraft wiring ASM 282803 between:
- the actuator free connector 6QH-A, pin A and the RELAY-PANEL (802VU) free connector 4065VC-A, pin <Q (MOT 1 28VDC SUPPLY)
- the actuator free connector 6QH-A, pin E and the ground point DC1 (MOT 1 GROUND).
(c) Do the test given in Para. 3.B.
(18) 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 (19).
- If the fault continues, go to step (20).
(a) Do a check of ASM 282803 ASM 282501 and replace if necessary:
- the RELAY-TRANSFER VALVE CONTROL, ACT [21QH]
- the RELAY- INLET VALVE CONTROL, ACT1 [19QH]
- the RELAY-SEQUENCE [18QH]
- the RELAY-POWER SUPPLY SWITCH [39QU] .
NOTE: The circuit connections shown in the table are abbreviated, for example:
- the connector 4065VC, pin <Q is shown as 4065VC-<Q
- the RELAY-XFR VALVE CTL, (21QH), terminal B1 is shown as RL 21QH-B1.
| ----------------------------------------------------------------------------- |
| ! CONNECTOR-PIN ! RELAY-TERMINAL TO RELAY-TERMINAL ! CONNECTOR-PIN ! |
| !-----------------------------------------------------------------------------! |
| ! 4065VC-<Q ---------------------------------- RL 21QH-B1 ! |
| ! 4065VC-<Q ---------------------------------- RL 19QH-A1 ! |
| ! RL 21QH-B2 ----------------- RL 19QH-A3 ! |
| ! RL 19QH-A2 ----------------- RL 18QH-A3 ! |
| ! RL 18QH-A2 ------------------RL 39QU-C2 ! |
| ! RL 39QU-C3 ---------------------------------- 4065VC-<G ! |
| ----------------------------------------------------------------------------- |
1 Repair all the unserviceable wiring and connectors.
2 Do the test given in Para. 3.B.
(20) Do the ACTUATOR-FUEL XFR VALVE, ACT (6QH) MOTOR 2 28VDC Open Supply trouble-shooting as follows:
(a) Do a check of the aircraft wiring AWM 282802 between:
- the actuator free connector 6QH-B, pin A and the free connector 4066VC-A, pin U (MOT 2 28VDC SUPPLY)
- the actuator free connector 6QH-B, pin E and the ground point DC2 (MOT 2 GROUND).
(c) Do the test given in Para. 3.B.
(21) If the fault continues:
NOTE: If you have replaced the relay panel 802VU in step (18), this step is not applicable.
(a) Do a check of AWM 282802 and replace if necessary: - the RELAY-TRANSFER VALVE CONTROL, ACT [21QH] .
NOTE: The relay 21QH is energized during manual transfer when the ACT pump supply contactor (26QH) closes. This input to the RELAY-PANEL (802VU) was checked in step (7).
(b) Do a check of the RELAY-PANEL (802VU) wiring AWM 282802 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 4066VC, pin N is shown as 4066VC-N
- the RELAY-XFR VALVE CTL, ACT (21QH), terminal A2 is shown as RL 21QH-A2.
| ----------------------------------------------------------------------------- |
| ! CONNECTOR-PIN ! RELAY-TERMINAL TO RELAY-TERMINAL ! CONNECTOR-PIN ! |
| !-----------------------------------------------------------------------------! |
| ! 4066VC-N ----------------------------------- RL 21QH-A2 ! |
| ! 4066VC-N ----------------------------------- RL 21QH-X1 ! |
| ! RL 21QH-A1 ---------------------------------- 4066VC-U ! |
| ! RL 21QH-X2 ---------------------------------- 4066VC-V ! |
| ! RL 21QH-X2 ---------------------------------- 4066VC-R ! |
| ----------------------------------------------------------------------------- |
1 Repair all the unserviceable wiring and connectors.
2 Do the test given in Para. 3.B.
(22) Do the Actuator Fuel Inlet Valve, ACT 1 (5QH1) Manual Transfer 28VDC Open Supply trouble-shooting as follows:
(a) Examine the C/B-ACT1/XFR VALVE/AUTO CTL (9QH) and make a record if it is open.
(b) Examine for signs of damage the items that follow:
- the actuator supply cable and end connector 5QH1-A
- the actuator 5QH1 electrical receptacle
- the ACT 1 aircraft to tank break receptacle 7619VC1, and its related connector 7619VC1-A.
(d) Close the C/B-ACT1/XFR VALVE/AUTO CTL (9QH) if it was open in step (a).
(e) Do the test given in Para. 3.B.
(23) If the fault continues:
- disconnect the electrical supply cable connector 5QH1-A from the ACTUATOR-FUEL INLET VALVE (5QH1).
| ACTUATOR SIGNAL LINE | CONNECTOR 5QH1-A PIN |
|---|---|
| MOTOR OPEN 28VDC SUPPLY | A |
| MOTOR GROUND | E |
NOTE: The RELAY-PANEL (802VU) output command to the ACTUATOR-FUEL INLET VALVE, ACT 1 (5QH1) can be checked at the test connector 4068VC, pin <A.
(25) If the 28VDC supply voltage is: (a) As specified in step (24):
1 Replace the ACTUATOR-FUEL INLET VALVE, ACT1 [5QH1] AMM 28-28-54-000-001 and AMM 28-28-54-400-001.
2 If the fault continues:
- replace the VALVE-FUEL INLET, ACT1 [166QM1] AMM 28-28-34-000-001 and AMM 28-28-34-400-001.
NOTE: If the ACT 2 (the rear ACT) is installed, it will be necessary to remove it to get access to the ACT 1 man-hole cover. The Removal and Installation (R and I) task numbers for the ACT 2 are given in the R and I for the valve-fuel inlet, ACT 1.
(b) Not as specified in step (24): 1 Do a check of the aircraft wiring ASM 282801 between:
- the actuator free connector 5QH1-A, pin A, and the ACT aircraft to tank break free connector 7619VC1-A, pin 15 (MOT 28VDC SUPPLY)
- the ACT aircraft to tank break connector 7619VC1, pin 15 and the RELAY-PANEL (802VU) free connector 4065VC-A, pin <H (MOT 28VDC SUPPLY)
- the actuator free connector 5QH1-A, pin E, and the ACT aircraft to tank break free connector 7619VC1-A, pin 5 (MOT GROUND)
- the ACT aircraft to tank break connector 7619VC1, pin 5 and the ground point DC1 (MOT GROUND).
3 Do the test given in Para. 3.B.
(26) If the fault continues:
NOTE: If you have replaced the relay panel 802VU in step (18), this step is not applicable.
(a) 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]
- the RELAY-REFUEL INHIBIT, ACT1 [37QU]
- the RELAY-MANUAL TRANSFER, ACT [16QH]
- the RELAY-LOW LEVEL OVERRIDE, ACT [17QH]
- the RELAY-SEQUENCE [18QH] .
NOTE: The circuit connections shown in the table are abbreviated, for example:
- the connector 4065VC, pin <H is shown as 4065VC-<H
- 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 ! |
| !-----------------------------------------------------------------------------! |
| ! 4065VC-<H ---------------------------------- RL 19QH-C1 ! |
| ! RL 19QH-C2 ----------------- RL 35QU-B3 ! |
| ! RL 35QU-B2 ----------------- RL 39QU-C2 ! |
| ! RL 39QU-C3----------------------------------- 4065VC-<G ! |
| ! RL 19QH-X1 ----------------- RL 39QU-C2 ! |
| ! 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-A1 ----------------- RL 17QH-B2 ! |
| ! RL 17QH-B3 ---------------------------------- 4065VC-<M ! |
| ! RL 17QH-B3 ---------------------------------- 4065VC-<T ! |
| ----------------------------------------------------------------------------- |
1 Repair all the unserviceable wiring and connectors.
2 Do the test given in Para. 3.B.