TSM A320F | L(R) Outer Temperature Sensor 30QJ1(2)

REFERENCE	DESIGNATION
TSM TASK 28-46-00-810-818-A	FLSCU1(2) 7QJ(9QJ)
ESPM 2053210
AMM 28-10-00-910-001	Safety Procedures When You Do Work in a Fuel Tank
AMM 28-10-00-910-002	Access to the Fuel Tanks and the Work Areas
AMM 28-42-00-740-003	Interrogation of the FQIS Input Parameters Pages
AMM 28-42-00-740-007	Interrogation of the (SMITHS INDUSTRIES) FQIS Trouble Shooting Data
AMM 28-42-43-000-003	Removal of the Wing-Tank Outer-Cell Group A Harness
AMM 28-42-43-000-006	Removal of the Wing-Tank Inner-Cell Group A Harness
AMM 28-42-43-000-008	Removal of the Wing Tank Fuel Quantity Indicating Probe Fused/Shorting Plug Connectors
AMM 28-42-43-400-003	Installation of the Wing Tank Outer-Cell Group A Harness
AMM 28-42-43-400-006	Installation of the Wing-Tank Inner-Cell Group A Harness
AMM 28-46-00-00-
AMM 28-46-00-740-001	Functional (BITE) Test
ASM 284604
AWM 284611
AWM 284612
AMM 28-46-17-000-002	Removal of the Temperature Sensor
AMM 28-46-17-400-002	Installation of the Temperature Sensor
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)
TSM TASK 28-46-00-03	TANK LEVEL SENSING - TASK SUPPORTING DATA

A. Test
(1) Do the Functional (BITE) Test (of the FLSS) AMM 28-46-00-740-001.
(2) Examine the FLSS STATUS page on the MCDU.
(3) If the page shows messages for one or more of the other sensors and/or the FLSCU-1(2), do (Ref. TSM TASK 28-46-00-810-818).
(4) If the message 284617 L(R) OUT TEMP SENSOR 30QJ1(2):

is shown, do Para. 4.A.
is not shown, no troubleshooting work steps are necessary.

NOTE: You can get more data from the:

Aircraft Maintenance Manual (AMM) AMM 28-46-00-00-
Trouble Shooting Manual (TSM) Task Supporting Data 28-46-00-03 TSM TASK 28-46-00-03
Aircraft Schematic Manual (ASM) ASM 284604.

You can get more trouble-shooting data from the CFDS(FUEL):

Input Parameters Page 3 AMM 28-42-00-740-003 together with the Fuel Temperature Level Sensors Operating (Changeover) Values 28-46-00-03 TSM TASK 28-46-00-03
FLSCU Trouble-shooting Data AMM 28-42-00-740-007.

NOTE: OPTIONAL TESTING:
If a PSD A320-2 Fuel Level Sensing Test Set is available more tests can be done before a decision is made to go into or close up a fuel tank. The Test Set lets you test the tank mounted components and the tank wiring from the tank wall connectors.

A. Procedure

NOTE: Where applicable, to show the difference between the left and right wing installations, the FINs given in this procedure are written as follows:

the left wing, no parenthesis, FIN
the right wing, in parenthesis, (FIN).

(1) Do the steps applicable to the test equipment available.
(2) Test Equipment.

WARNING: WHEN YOU DO WORK ON THE FUEL SYSTEM WIRING, YOU MUST USE TEST EQUIPMENT THAT IS APPROVED (REFER TO INTERNATIONAL OR NATIONAL SPECIFICATIONS FOR INTRINSICALLY SAFE TEST EQUIPMENT: EN50020, UL913 OR EQUIVALENT). TEST EQUIPMENT THAT IS NOT APPROVED CAN CAUSE FIRE OR AN EXPLOSION.

(a) If there is:

approved test equipment available, do step (3)
no approved test equipment available, do step (8).

(3) At the ECAM FUEL page look at the applicable L(R) wing-tank outer-cell fuel temperature.
(a) If a value:

is shown, make a record of the temperature
is not shown, get the temperature from the input parameter page 1 AMM 28-42-00-740-003 and record the temperature.

NOTE: The source of the wing-tank outer-cell fuel temperatures shown on the ECAM FUEL page and input parameter page 1 are the specially selected diodes that are part of the FQIS L(R) fuel-probe 33QT1(2).

In normal operation if the L(R) outer-cell is empty:

the related ECAM indiction shows blank
the related FQIS input parameter page 1 value is always available but will show the air temperature when the cell is empty.

(b) Make sure that the time interval between the temperature check (in step (3)(a)) and the resistance test (in step (6)(a)) is short. Example, five minutes. If there is a longer time interval, do a check of the temperature (again) after the resistance test.
(4) Get access to the tank wall connector 4039VC1(2)-A (for the wing tank harness 13QT1(2)) AMM 28-42-43-000-008.
(5) Disconnect the free connector 4039VC1(2)-A from the receptacle 4039VC1(2).
(6) Do the test that follows:
(a) Do a resistance check of the FLSS temperature sensor 30QJ1(2) at the tank wall connector 4039VC1(2) between pins <B and F AWM 284611 ( AWM 284612).
1 Make a record of the value you got during the test.
(7) The FLSS temperature sensor resistance is 999.9 ohms at 0 deg.C (32.00 deg.F) with a positive change with temperature of 3.88 ohms per deg.C (2.16 ohms per deg.F).

The resistance values, for the FLSS temperature sensor 30QJ1(2) as a function of temperature, have been calculated and are given in the table that follows.

NOTE: The resistance value of the temperature sensor is directly proportional to the ambient fuel (or air) temperature in the wing-tank outer-cell.

TEMP deg.C	TEMP deg.F	R OHMS
50	122.0	1194.9
49	120.2	1191.0
48	118.4	1187.1
47	116.6	1183.2
46	114.8	1179.3
45	113.0	1175.4
44	111.2	1171.5
43	109.4	1167.6
42	107.6	1163.7
41	105.8	1159.8
40	104.0	1155.9
39	102.2	1152.0
38	100.4	1148.1
37	98.6	1144.2
36	96.8	1140.3
35	95.0	1136.4
34	93.2	1132.5
33	91.4	1128.6
32	89.6	1124.7
31	87.8	1120.8
30	86.0	1116.9
29	84.2	1113.0
28	82.4	1109.1
27	80.6	1105.2
26	78.8	1101.3
25	77.0	1097.4
24	75.2	1093.5
23	73.4	1089.6
22	71.6	1085.7
21	69.8	1081.8
20	68.0	1077.9
19	66.2	1074.0
18	64.4	1070.1
17	62.6	1066.2
16	60.8	1062.3
15	59.0	1058.4
14	57.2	1054.5
13	55.4	1050.6
12	53.6	1046.7
11	51.8	1042.8
10	50.0	1038.9
9	48.2	1035.0
8	46.4	1031.1
7	44.6	1027.2
6	42.8	1023.3
5	41.0	1019.4
4	39.2	1015.5
3	37.4	1011.6
2	35.6	1007.7
1	33.8	1003.8
0	32.0	999.9
- 1	30.2	996.0
- 2	28.4	992.1
- 3	26.6	988.2
- 4	24.8	984.3
- 5	23.0	980.4
- 6	21.2	976.5
- 7	19.4	972.6
- 8	17.6	968.7
- 9	15.8	964.8
-10	14.0	960.9
-11	12.2	957.0
-12	10.4	953.1
-13	8.6	949.2
-14	6.8	945.3
-15	5.0	941.4
-16	3.2	937.5
-17	1.4	933.6
-18	- 0.4	929.7
-19	- 2.2	925.8
-20	- 4.0	921.9

(a) Find the temperature that you recorded in step (3)(a) in the table.
(b) Read (and record) the resistance value R OHMS for that temperature in the table.
(c) Do a calculation to include a tolerance of minus 22 and plus 27 ohms to the resistance value (R OHMS) you got from the table. This will give you a range of permitted resistance.

Example,

at 10 deg.C (50.00 deg.F)

the tolerance range = (R OHMS minus 22) to (R OHMS plus 27)

= (1038.9 minus 22) to (1038.9 plus 27)

= 1016.9 to 1065.9 ohms.

NOTE: The tolerance given above is made from the three items as follows:

plus or minus 2 ohms for the FLSS temperature sensor component
plus 5 or minus 0 ohms for the aircraft wiring
plus or minus 20 ohms for the equivalent accuracy of the temperature values supplied by the FQIS.

(d) Compare the (test) resistance value you recorded in step (6)(a)1_ with the resistance value you got from the table plus and minus the tolerances in step (7)(c).
1 If the (test) resistance value:

is in tolerance, do step (8)
is not in tolerance, do step (10).

(8) Replace the FLSCU-1 [7QJ] ( FLSCU-2 [9QJ] ) AMM 28-46-34-000-001 and AMM 28-46-34-400-001.
(9) If the fault continues:
(a) Get access to the tank wall connector 4039VC1(2)-A (for the wing tank harness 13QT1(2)) AMM 28-42-43-000-008.
(b) Disconnect the free connector 4039VC1(2)-A from the receptacle 4039VC1(2).
(c) Do a check AWM 284611, and AWM 284612 of the aircraft wiring (sensor input line - H) between the FLSCU-1(2) rack connector AB, pin 7D and the tank wall free connector 4039VC1(2)-A, pin <B.
(d) Do a check AWM 284611, and AWM 284612 of the aircraft wiring (sensor input line - L) between the FLSCU-1(2) rack connector AB, pin 7C and the tank wall free connector 4039VC1(2)-A, pin F.
(e) Do a check AWM 284611 of the aircraft wiring (FLSCU-1 BITE 4 test command line) between the FLSCU-1 rack connector AA, pin 15D and the FQIC rack connector AB, pin 7K or ( AWM 284612 of the aircraft wiring (FLSCU-2 BITE 4 test command line) between the FLSCU-2 rack connector AA, pin 15D and the FQIC rack connector AB, pin 9H).
(f) Do a check AWM 284611 of the aircraft wiring (FLSCU-1 T2 output line) between the FLSCU-1 rack connector AB, pin 4D and the FQIC rack connector AB, pin 5K or ( AWM 284612 of the aircraft wiring (FLSCU-2 T2 output line) between the FLSCU-2 rack connector AB, pin 4D and the FQIC rack connector AB, pin 15K).
(g) Repair all the unserviceable wiring and connectors ESPM 2053210.
(h) Connect the free connector 4039VC1(2)-A to the receptacle 4039VC1(2).
(i) Do the test given in Para. 3.A.
(10) If the fault continues or if there is no continuity (the measured resistance value is out of tolerance) in step (7)(d):
(a) Drain, open and vent the tank AMM 28-10-00-910-001 and AMM 28-10-00-910-002.
(b) Do a wiring check AWM 284611 ( AWM 284612) of the harnesses that follow and replace, if necessary:

the HARNESS-CHAN A, L WING TK INR [13QT1] ( HARNESS-CHAN A, R WING TK INR [13QT2] ) AMM 28-42-43-000-006 and AMM 28-42-43-400-006
the HARNESS-CHAN A, L WING TK OUTR [15QT1] ( HARNESS-CHAN A, R WING TK OUTR [15QT2] ) AMM 28-42-43-000-003 and AMM 28-42-43-400-003.

(c) If the harnesses 13QT1(2) and 15QT1(2) are serviceable, replace the SENSOR-TEMP, LEFT WING TK OUTER CHANNEL A [30QJ1] ( SENSOR-TEMP, RIGHT WING TK OUTER CHANNEL A [30QJ2] ) AMM 28-46-17-000-002 and AMM 28-46-17-400-002.

A. Procedure

NOTE: Where applicable, to show the difference between the left and right wing installations, the FINs given in this procedure are written as follows:

the left wing, no parenthesis, FIN
the right wing, in parenthesis, (FIN).

(1) Do the steps applicable to the test equipment available.
(2) Test Equipment.

WARNING: WHEN YOU DO WORK ON THE FUEL SYSTEM WIRING, YOU MUST USE TEST EQUIPMENT THAT IS APPROVED (REFER TO INTERNATIONAL OR NATIONAL SPECIFICATIONS FOR INTRINSICALLY SAFE TEST EQUIPMENT: EN50020, UL913 OR EQUIVALENT). TEST EQUIPMENT THAT IS NOT APPROVED CAN CAUSE FIRE OR AN EXPLOSION.

(a) If there is:

approved test equipment available, do step (3)
no approved test equipment available, do step (8).

(3) At the ECAM FUEL page look at the applicable L(R) wing-tank outer-cell fuel temperature.
(a) If a value:

is shown, make a record of the temperature
is not shown, get the temperature from the input parameter page 1 AMM 28-42-00-740-003 and record the temperature.

NOTE: The source of the wing-tank outer-cell fuel temperatures shown on the ECAM FUEL page and input parameter page 1 are the specially selected diodes that are part of the FQIS L(R) fuel-probe 93QT1(2).

In normal operation if the L(R) outer-cell is empty:

the related ECAM indiction shows blank
the related FQIS input parameter page 1 value is always available but will show the air temperature when the cell is empty.

(b) Make sure that the time interval between the temperature check (in step (3)(a)) and the resistance test (in step (6)(a)) is short. Example, five minutes. If there is a longer time interval, do a check of the temperature (again) after the resistance test.
(4) Get access to the tank wall connector 4039VC1(2)-A (for the wing tank harness 13QT1(2)) AMM 28-42-43-000-008.
(5) Disconnect the free connector 4039VC1(2)-A from the receptacle 4039VC1(2).
(6) Do the test that follows:
(a) Do a resistance check of the FLSS temperature sensor 30QJ1(2) at the tank wall connector 4039VC1(2) between pins <B and F AWM 284611 ( AWM 284612).
1 Make a record of the value you got during the test.
(7) The FLSS temperature sensor resistance is 999.9 ohms at 0 deg.C (32.00 deg.F) with a positive change with temperature of 3.88 ohms per deg.C (2.16 ohms per deg.F).

The resistance values, for the FLSS temperature sensor 30QJ1(2) as a function of temperature, have been calculated and are given in the table that follows.

NOTE: The resistance value of the temperature sensor is directly proportional to the ambient fuel (or air) temperature in the wing-tank outer-cell.

TEMP deg.C	TEMP deg.F	R OHMS
50	122.0	1194.9
49	120.2	1191.0
48	118.4	1187.1
47	116.6	1183.2
46	114.8	1179.3
45	113.0	1175.4
44	111.2	1171.5
43	109.4	1167.6
42	107.6	1163.7
41	105.8	1159.8
40	104.0	1155.9
39	102.2	1152.0
38	100.4	1148.1
37	98.6	1144.2
36	96.8	1140.3
35	95.0	1136.4
34	93.2	1132.5
33	91.4	1128.6
32	89.6	1124.7
31	87.8	1120.8
30	86.0	1116.9
29	84.2	1113.0
28	82.4	1109.1
27	80.6	1105.2
26	78.8	1101.3
25	77.0	1097.4
24	75.2	1093.5
23	73.4	1089.6
22	71.6	1085.7
21	69.8	1081.8
20	68.0	1077.9
19	66.2	1074.0
18	64.4	1070.1
17	62.6	1066.2
16	60.8	1062.3
15	59.0	1058.4
14	57.2	1054.5
13	55.4	1050.6
12	53.6	1046.7
11	51.8	1042.8
10	50.0	1038.9
9	48.2	1035.0
8	46.4	1031.1
7	44.6	1027.2
6	42.8	1023.3
5	41.0	1019.4
4	39.2	1015.5
3	37.4	1011.6
2	35.6	1007.7
1	33.8	1003.8
0	32.0	999.9
- 1	30.2	996.0
- 2	28.4	992.1
- 3	26.6	988.2
- 4	24.8	984.3
- 5	23.0	980.4
- 6	21.2	976.5
- 7	19.4	972.6
- 8	17.6	968.7
- 9	15.8	964.8
-10	14.0	960.9
-11	12.2	957.0
-12	10.4	953.1
-13	8.6	949.2
-14	6.8	945.3
-15	5.0	941.4
-16	3.2	937.5
-17	1.4	933.6
-18	- 0.4	929.7
-19	- 2.2	925.8
-20	- 4.0	921.9

(a) Find the temperature that you recorded in step (3)(a) in the table.
(b) Read (and record) the resistance value R OHMS for that temperature in the table.
(c) Do a calculation to include a tolerance of minus 22 and plus 27 ohms to the resistance value (R OHMS) you got from the table. This will give you a range of permitted resistance.

Example,

at 10 deg.C (50.00 deg.F)

the tolerance range = (R OHMS minus 22) to (R OHMS plus 27)

= (1038.9 minus 22) to (1038.9 plus 27)

= 1016.9 to 1065.9 ohms.

NOTE: The tolerance given above is made from the three items as follows:

plus or minus 2 ohms for the FLSS temperature sensor component
plus 5 or minus 0 ohms for the aircraft wiring
plus or minus 20 ohms for the equivalent accuracy of the temperature values supplied by the FQIS.

(d) Compare the (test) resistance value you recorded in step (6)(a)1_ with the resistance value you got from the table plus and minus the tolerances in step (7)(c).
1 If the (test) resistance value:

is in tolerance, do step (8)
is not in tolerance, do step (10).

(8) Replace the FLSCU-1 [7QJ] ( FLSCU-2 [9QJ] ) AMM 28-46-34-000-001 and AMM 28-46-34-400-001.
(9) If the fault continues:
(a) Get access to the tank wall connector 4039VC1(2)-A (for the wing tank harness 13QT1(2)) AMM 28-42-43-000-008.
(b) Disconnect the free connector 4039VC1(2)-A from the receptacle 4039VC1(2).
(c) Do a check AWM 284611, and AWM 284612 of the aircraft wiring (sensor input line - H) between the FLSCU-1(2) rack connector AB, pin 7D and the tank wall free connector 4039VC1(2)-A, pin <B.
(d) Do a check AWM 284611, and AWM 284612 of the aircraft wiring (sensor input line - L) between the FLSCU-1(2) rack connector AB, pin 7C and the tank wall free connector 4039VC1(2)-A, pin F.
(e) Do a check AWM 284611 of the aircraft wiring (FLSCU-1 BITE 4 test command line) between the FLSCU-1 rack connector AA, pin 15D and the FQIC rack connector AB, pin 7K or ( AWM 284612 of the aircraft wiring (FLSCU-2 BITE 4 test command line) between the FLSCU-2 rack connector AA, pin 15D and the FQIC rack connector AB, pin 9H).
(f) Do a check AWM 284611 of the aircraft wiring (FLSCU-1 T2 output line) between the FLSCU-1 rack connector AB, pin 4D and the FQIC rack connector AB, pin 5K or ( AWM 284612 of the aircraft wiring (FLSCU-2 T2 output line) between the FLSCU-2 rack connector AB, pin 4D and the FQIC rack connector AB, pin 15K).
(g) Repair all the unserviceable wiring and connectors ESPM 2053210.
(h) Connect the free connector 4039VC1(2)-A to the receptacle 4039VC1(2).
(i) Do the test given in Para. 3.A.
(10) If the fault continues or if there is no continuity (the measured resistance value is out of tolerance) in step (7)(d):
(a) Drain, open and vent the tank AMM 28-10-00-910-001 and AMM 28-10-00-910-002.
(b) Do a wiring check AWM 284611 ( AWM 284612) of the harnesses that follow and replace, if necessary:

the HARNESS-CHAN A, L WING TK INR [13QT1] ( HARNESS-CHAN A, R WING TK INR [13QT2] ) AMM 28-42-43-000-006 and AMM 28-42-43-400-006
the HARNESS-CHAN A, L WING TK OUTR [15QT1] ( HARNESS-CHAN A, R WING TK OUTR [15QT2] ) AMM 28-42-43-000-003 and AMM 28-42-43-400-003.

(c) If the harnesses 13QT1(2) and 15QT1(2) are serviceable, replace the SENSOR-TEMP, LEFT WING TK OUTER CHANNEL A [30QJ1] ( SENSOR-TEMP, RIGHT WING TK OUTER CHANNEL A [30QJ2] ) AMM 28-46-17-000-002 and AMM 28-46-17-400-002.