Fuel - ACT 1 Manual Transfer Failure (On The Ground) (802VU ACT Relay Testbox)

TASK 28-28-00-810-802-A-01
Fuel - ACT 1 Manual Transfer Failure (On The Ground) (802VU ACT Relay Testbox)

WARNING: OBEY THE FUEL SAFETY PROCEDURES.

1. Possible Causes

aircraft wiring
FLSCU-1 [7QJ]
SENSOR-HIGH LEVEL, CHANNEL A [20QJ]
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-PANEL (802VU)
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]

2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	MULTIMETER - STANDARD
RIN28108706000	1	TESTBOX-ACT 802VU

B. Referenced Information

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 28-28-00-810-806-A	Fuel - ACT Transfer System Flag/Symbol Failure
TSM TASK 28-46-00-810-822-A	CTR HI LVL Indicator Lamp Does Not Come On When TEST Switch Set To LTS
TSM TASK 28-46-00-810-825-A	CTR HI LVL Manual TEST
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
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
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 28-28-53-000-001	Removal of the ACT Transfer-Valve Actuator
AMM 28-28-53-400-001	Installation of the ACT Transfer-Valve Actuator
AMM 28-28-54-000-001	Removal of the ACT Fuel Inlet Valve Actuator (5QH)
AMM 28-28-54-400-001	Installation of the ACT Fuel Inlet Valve Actuator (5QH)
AMM 28-46-00-710-001	Test of the Tank High-Level Sensing-System
ASM 284601
ASM 326201

3. Fault Confirmation
Subtask 28-28-00-865-081-A ** ON A/C NOT FOR ALL

A. Table of the circuit breakers referred to in this procedure:

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

Subtask 28-28-00-710-086-B ** ON A/C NOT FOR ALL

B. Test
(1) Do the Operational Test of the ACT Manual Transfer System AMM 28-28-00-710-001.

NOTE: If the center tank is full of fuel it will inhibit/stop a manual fuel transfer, because the applicable ACT inlet valve is closed (when the aircraft is on the ground).
In a similar manner a failure to energize the 501PP FUELLING BUS 28VDC, will cause the center tank high level channel LS7 of the sensor 20QJ (in the FLSCU-1 7QJ)) to give a false WET output (not powered - de-energized condition).
It is therefore important to make sure that the REFUEL panel door 192MB/522KB/622KB is open (or if installed the P/BSW-REFUEL/PWR (23QU) is set to on, cockpit refuel selected) during the operational test.

NOTE: You can get more data for 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.

4. Fault Isolation
Subtask 28-28-00-810-107-B ** ON A/C NOT FOR ALL

A. Procedure
(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).

(2) If fault continues:

do the Operation Test of the HI LVL Lights. Refer to the center tank only AMM 28-46-00-710-001.

(3) If the Operational Test of the center tank HI LVL light is correct:

go to step (7).

(4) If during the Operational Test of the center tank HI LVL light it does not come on when the TEST switch held to LTS:

do (Ref. TSM TASK 28-46-00-810-822).

(5) If during the Operational Test of the center tank HI LVL light it fails when in the center rest position and/or when in the TEST position:

do (Ref. TSM TASK 28-46-00-810-825).

(6) Do the test given in Para. 3.B.
(a) Do a continuity test, with a multimeter 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.

All four (4) continuity tests should show a low resistance.
(b) If the test results are:
1 As specified:

go to step (8).

2 Not as specified:
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.

b Repair all the unserviceable wiring and connectors.
c Connect the free connectors 4065VC-A and 4066VC-A to the RELAY-PANEL (802VU).
d Do the test given in Para. 3.B.
(7) Do the FLSCU-1 [7QJ] , CHAN LS7 - SENSOR-HIGH LEVEL, CHANNEL A [20QJ] input to RELAY-PANEL (802VU) trouble-shooting as follows:

NOTE: If there are no reported problems/failures with refuelling the center tank, this shows the correct functionality of the center tank high level sensor channel when the sensor 20QJ is dry. This is because the FLSCU-1 (7QJ), high level channel (LS7) relay contacts feed the center tank refuel valve control circuit and the ACT system in parallel.

(a) If necessary, defuel/transfer the center tank fuel, to decrease its FQI, to a maximum of 6000 kg (13220 lb) AMM 28-25-00-650-001 or AMM 28-25-00-869-001.

NOTE: This is to make sure the center tank high level sensor (20QJ) is dry, and allow an ACT Manual fuel transfer when the aircraft is on the ground.

(b) Disconnect the free connector 4065VC-A from the RELAY-PANEL (802VU).
(c) Do a continuity test, with a multimeter ASM 282501 and ASM 282803 as follows:

connect the multimeter internal battery positive (+) lead to the free connector 4065VC-A, pin <C
connect the multimeter internal battery negative (-) lead to a suitable ground.

NOTE: This procedure is necessary because there is a diode in the circuit under test.

This test should show a low resistance.
(d) If the test result:
1 Is as specified

go to step (9).

2 Is not as specified:
a Do a check of the aircraft wiring ASM 282501 and ASM 282803 between:

the FLSCU-1 (7QJ) rack connector AA, pin 8C and the free connector 4065VC-A, pin <C, via diode module 80VD, pins 14 (-) and 29 (+), (CTR TK HI LVL sensor output to the ACT system).

b Do a check of the diode and replace if necessary.
c Repair all the unserviceable wiring and connectors.
d Connect the free connector 4065VC-A to the RELAY-PANEL (802VU).
e Do the test given in Para. 3.B.
(8) Do the LGCIU-1 [5GA1] input to RELAY-PANEL (802VU) trouble-shooting as follows:
(a) Do a continuity test, with a multimeter ASM 282803 and ASM 326201 between the free connector 4065VC-A, pin V and a suitable ground.
This test should show a low resistance.
(b) If the test result:
1 Is as specified:

go to step (10).

2 Is not as specified:
a Do a check of the aircraft wiring ASM 282803 and ASM 326201 between:

the free connector 4065VC, pin V and the LGCIU-1 (5GA1) rack connector AB, pin 7A (FLIGHT/GROUND line).

b Repair all the unserviceable wiring and connectors.
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).

e Do the test given in Para. 3.B.
(9) 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 see if 28VDC is available at the free connector 4065VC-A, pin <G.
(b) If the 28VDC:
1 Is available:

go to step (11).

2 Is not available:
a Do a check of ASM 282801 and replace if necessary:

the C/B-ACT1/CTL & SPLY [9QH] .

b Do a check of the aircraft wiring ASM 282801 between:

the free connector 4065VC-A, pin <G and the C/B-ACT1/XFR VALVE/AUTO CTL (9QH), terminal 2.

c Repair all the unserviceable wiring and connectors.
d Do the test given in Para. 3.B.
(10) 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 see if 28VDC is available at the free connector 4066VC-A, pin P.
(c) If the 28VDC:
1 Is available:

go to step (12).

2 Is not available:
a Do a check of AWM 282802 and replace if necessary:

the SWITCH-INDICATOR, ACT [24QH]
the C/B-ACT XFR VALVE MAN CTL [30QH] .

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.

c Repair all the unserviceable wiring and connectors.
d Do the test given in Para. 3.B.
(11) 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 see if 28VDC is available at the free connector 4066VC-A, pin N.
(c) If the 28VDC:
1 Is available:

go to step (13).

2 Is not available:
a Do a check of AWM 282802 and replace if necessary the:

the CONTACTOR-ACT PUMP SUPPLY [26QH] .

b Do a check of the aircraft wiring AWM 282802 between:

the free connector 4066VC-A, pin N and the CONTACTOR-ACT PUMP SUPPLY (26QH), terminal 3.

c Repair all the unserviceable wiring and connectors.
d Do the test given in Para. 3.B.
(12) 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:

the related fuel level sense system input from the ACT 2
the set sequence relay (18QH) control circuits.

(b) The free connectors 4065VC-A, and 4066VC-A are connected to their related receptacles on the RELAY-PANEL (802VU).
(c) The P/BSW-FUEL/ACT/AUTO (24QH) is set to FWD (pushed) in.
(13) 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	(16)
FUEL INLET VALVE, ACT 1	5QH1	OPEN	(27)

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.

(14) If the ACT manual transfer flag/symbol is not shown, but the actuators in the table are in the correct position and fuel is seen to transfer (by examination of the ACT and center tank fuel quantities):

do the ACT Transfer System Flag/Symbol Failure (Ref. TSM TASK 28-28-00-810-806).

(15) 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 obvious signs of damage:

the actuator supply cables, and end connectors 6QH-A, and 6QH-B
the actuator electrical receptacles.

(d) Repair all the unserviceable cables and connectors.
(e) Close the C/Bs if they were found open in (a) and (b).
(f) Do the test given in Para. 3.B.
(16) If the fault continues:

disconnect the electrical supply cable connector 6QH-A from the ACTUATOR-FUEL XFR VALVE, ACT (6QH).

(17) Push the P/BSW-FUEL/ACT/AUTO (24QH) (ACT XFR system to Manual) in.
(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.

(18) Do a test, with a MULTIMETER - STANDARD, ASM 282803 to see if the 28VDC supply is available at the connector 6QH-A between the pins as shown in the table that follows.

ACTUATOR SIGNAL LINE	CONNECTOR 6QH-A PIN
MOTOR 1 OPEN 28VDC SUPPLY	A
MOTOR 1 GROUND	E

(19) Disconnect the electrical supply cable connector 6QH-B from the ACTUATOR-FUEL XFR VALVE, ACT (6QH).
(20) Do a test, with a multimeter, AWM 282802 to see if 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

(21) If the 28VDC supply at:
(a) The two connectors during, steps (19) and (21) are as specified:
1 Replace the ACTUATOR-FUEL TRANSFER VALVE, ACT [6QH] AMM 28-28-53-000-001 and AMM 28-28-53-400-001.
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.

(b) Connector 6QH-A (MOTOR 1) step (19), is not as specified, go to step (23).

NOTE: The 28VDC open supply via 6QH-A is directly related to the ACT manual transfer relay control and changes the transfer valve actuator motor No. 1 close supply connection to the open line.

NOTE: The 28VDC open supply via 6QH-B is supplied from the ACT manual transfer pump contactor control.

(22) 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).

(b) Repair all the unserviceable wiring and connectors.
(c) Do the test given in Para. 3.B.
(23) 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 (24).

(a) Do the test given in the Para. 3.B.

If the fault continues, go to step (25).

(24) If the fault continues:
(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] .

1 Do a check of the RELAY-PANEL (802VU) wiring ASM 282803 and ASM 282501 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 4065VC, pin <Q is shown as 4065VC-<Q
the RELAY-XFR VALVE CTL, ACT (21QH), terminal B1 is shown as RL 21QH-B1.

CONNECTOR-PIN	RELAY-TERMINAL	TO
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

2 Repair all the unserviceable wiring and connectors.
3 Do the test given in Para. 3.B.
(25) 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).

(b) Repair all the unserviceable wiring and connectors.
(c) Do the test given in Para. 3.B.
(26) If the fault continues:

NOTE: If you have replaced the relay panel 802VU in step (23), 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 (12).

(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
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.
(27) 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 the items that follow for signs of damage:

the actuator supply cable and end connector 5QH1-A
the actuator electrical receptacle.
the ACT aircraft to tank break receptacle 7619VC1, and free connector 7619VC1-A.

(c) Repair all unserviceable cables and connectors.
(d) Close the C/B-ACT1/XFR VALVE/AUTO CTL (9QH) if it was open in (a).
(e) Do the test given in Para. 3.B.
(28) If the fault continues:
(a) 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.

(b) Do a check of the RIN28108706000 TESTBOX-ACT 802VU, for the Inlet Valve Act. ACT1 (5QH1) (CMD) OPEN (green) light.
1 If the light does not come on:

Do step (31).

2 If the light comes on:

NOTE: The output command from the RELAY-PANEL (802VU) to the ACTUATOR-FUEL INLET VALVE ACT 1 (5QH1) is correct.

- Do the next step.
(29) Disconnect the electrical supply cable connector 5QH1-A from the ACTUATOR-FUEL INLET VALVE (5QH1).
(a) Do a test, with a multimeter, ASM 282801 to see if the 28VDC is available at the connector 5QH1-A between the pins as shown in the table that follows.

ACTUATOR SIGNAL LINE	CONNECTOR 5QH1-A PIN
MOTOR OPEN 28VDC SUPPLY	A
MOTOR GROUND	E

(30) If the 28VDC supply voltage is:
(a) As specified in step (29)(b):
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 (29)(b):
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 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).

2 Repair all the unserviceable wiring and connectors.
3 Do the test given in Para. 3.B.
(31) If the fault continues:

NOTE: If you have replaced the relay panel 802VU in step (23), 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] .

(b) Do a check of the RELAY-PANEL (802VU) wiring ASM 282801 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 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
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-B1	4065VC-<C

1 Repair all the unserviceable wiring and connectors.
2 Do the test given in Para. 3.B.

[Rev.8 from Aug 2018] 2026.04.04 04:28:49 UTC