DOC AIRBUS | TSM A320FL(R) Inner Temperature Sensor 29QJ1(2)
TASK 28-46-00-810-813-A
L(R) Inner Temperature Sensor 29QJ1(2)
A. Referenced Information
3. Fault Confirmation
Subtask 28-46-00-740-062-A ** ON A/C NOT FOR ALL
Subtask 28-46-00-810-062-A ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:29:15 UTC
L(R) Inner Temperature Sensor 29QJ1(2)
WARNING:
OBEY THE FUEL SAFETY PROCEDURES.
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.
1. Possible Causes- FLSCU-1 [7QJ]
- FLSCU-2 [9QJ]
- aircraft wiring
- HARNESS-CHAN A, L WING TK INR [13QT1]
- HARNESS-CHAN A, R WING TK INR [13QT2]
- SENSOR-TEMP, LEFT WING TK INNER CHANNEL A or SENSOR-TEMP, LEFT WING TK INNER CHANNEL A [29QJ1]
- SENSOR-TEMP, RIGHT WING TK INNER CHANNEL A or SENSOR-TEMP, RIGHT WING TK INNER CHANNEL A [29QJ2]
- HARNESS-LEFT WING TANK A [57QT]
- HARNESS-RIGHT WING, TANK A [58QT]
A. Referenced Information
| 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 28-42-00-740-009 | Interrogation of the (SIMMONDS/GOODRICH) FQIS Trouble Shooting Data |
| AMM 28-42-43-000-005 | Removal of the Wing Tank 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 28-42-43-400-005 | Installation of the Wing Tank 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 28-46-17-000-001 | Removal of the Temperature Sensor |
| AMM 28-46-17-400-001 | 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 |
Subtask 28-46-00-740-062-A ** ON A/C NOT FOR ALL
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) INN TEMP SENSOR 29QJ1(2):
Subtask 28-46-00-740-062-B ** ON A/C NOT FOR ALL (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) INN TEMP SENSOR 29QJ1(2):
- is shown, do Para. 4.A.
- is not shown, no troubleshooting work steps are necessary.
NOTE: You can get more data from the:
You can get more Trouble-shooting data from the CFDS(FUEL):
- 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.
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. 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) TEMP SENSOR 29QJ1(2):
4. Fault Isolation(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) TEMP SENSOR 29QJ1(2):
- is shown, do Para. 4.A.
- is not shown, no troubleshooting work steps are necessary.
NOTE: You can get more data from the:
You can get more Trouble-shooting data from the CFDS(FUEL):
- 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 - Trouble-shooting Data AMM 28-42-00-740-009.
NOTE: OPTIONAL TESTING:
If a PSDA321-1 Test Set is available more checks can be done before a decision is made to go into or close up a fuel tank. The Test Set lets you do a GO/NOGO check of the tank mounted components and the tank wiring from the tank wall connectors.
If a PSDA321-1 Test Set is available more checks can be done before a decision is made to go into or close up a fuel tank. The Test Set lets you do a GO/NOGO check of the tank mounted components and the tank wiring from the tank wall connectors.
Subtask 28-46-00-810-062-A ** ON A/C NOT FOR ALL
A. Procedure
(2) Test Equipment.
(a) If a value:
(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 29QJ1(2) at the tank wall connector 4039VC1(2) between pins <H and <X 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 29QJ1(2) as a function of temperature, have been calculated and are given in the table that follows.
(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.
1 If the (test) resistance value:
(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 8D and the tank wall free connector 4039VC1(2)-A, pin <H.
(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 8C and the tank wall free connector 4039VC1(2)-A, pin <X.
(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, 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, 9H).
(f) Do a check AWM 284611 of the aircraft wiring (FLSCU-1 T1 output line) between the FLSCU-1 rack connector AB, pin 4C and the FQIC rack connector AB, 5J or ( AWM 284612 of the aircraft wiring (FLSCU-2 T1 output line) between the FLSCU-2 rack connector AB, pin 4C and the FQIC rack connector AB, 15J).
(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 of the HARNESS-CHAN A, L WING TK INR [13QT1] ( HARNESS-CHAN A, R WING TK INR [13QT2] ) AWM 284611 ( AWM 284612) and replace, if necessary AMM 28-42-43-000-006 and AMM 28-42-43-400-006.
(c) If the harness is serviceable, replace the SENSOR-TEMP, LEFT WING TK INNER CHANNEL A or SENSOR-TEMP, LEFT WING TK INNER CHANNEL A [29QJ1] ( SENSOR-TEMP, RIGHT WING TK INNER CHANNEL A or SENSOR-TEMP, RIGHT WING TK INNER CHANNEL A [29QJ2] ) AMM 28-46-17-000-001 and AMM 28-46-17-400-001.
Subtask 28-46-00-810-062-B ** ON A/C NOT FOR ALL NOTE: Where applicable, to show the difference between the left and right wing installations, the FINs given in this procedure are written as follows:
(1) Do the steps applicable to the test equipment available. - the left wing, no parenthesis, FIN
- the right wing, in parenthesis, (FIN).
(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).
(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 inner-cell fuel temperatures shown on the ECAM FUEL page and the input parameter page 1 are the specially selected diodes that are part of the FQIS L(R) fuel-probe 22QT1(2).
In normal operation the ECAM and the FQIS input parameter page 1 temperature values:
(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. In normal operation the ECAM and the FQIS input parameter page 1 temperature values:
- are always available
- show the temperature of the ambient air space if the surface of the fuel goes below the temperature sensor.
(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 29QJ1(2) at the tank wall connector 4039VC1(2) between pins <H and <X 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 29QJ1(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 inner-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 |
(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:
(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). - 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.
1 If the (test) resistance value:
- is in tolerance, do step (8)
- is not in tolerance, do step (10).
(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 8D and the tank wall free connector 4039VC1(2)-A, pin <H.
(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 8C and the tank wall free connector 4039VC1(2)-A, pin <X.
(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, 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, 9H).
(f) Do a check AWM 284611 of the aircraft wiring (FLSCU-1 T1 output line) between the FLSCU-1 rack connector AB, pin 4C and the FQIC rack connector AB, 5J or ( AWM 284612 of the aircraft wiring (FLSCU-2 T1 output line) between the FLSCU-2 rack connector AB, pin 4C and the FQIC rack connector AB, 15J).
(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 of the HARNESS-CHAN A, L WING TK INR [13QT1] ( HARNESS-CHAN A, R WING TK INR [13QT2] ) AWM 284611 ( AWM 284612) and replace, if necessary AMM 28-42-43-000-006 and AMM 28-42-43-400-006.
(c) If the harness is serviceable, replace the SENSOR-TEMP, LEFT WING TK INNER CHANNEL A or SENSOR-TEMP, LEFT WING TK INNER CHANNEL A [29QJ1] ( SENSOR-TEMP, RIGHT WING TK INNER CHANNEL A or SENSOR-TEMP, RIGHT WING TK INNER CHANNEL A [29QJ2] ) AMM 28-46-17-000-001 and AMM 28-46-17-400-001.
A. Procedure
(2) Test Equipment.
(a) If a value:
(4) Get access to the tank wall connector 4039VC1(2)-A (for the wing tank harness 57QT(58QT)) 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 29QJ1(2) at the tank wall connector 4039VC1(2) between pins <H and <X 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 29QJ1(2) as a function of temperature, have been calculated and are given in the table that follows.
(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.
1 If the (test) resistance value:
(9) If the fault continues:
(a) Get access to the tank wall connector 4039VC1(2)-A (for the wing tank harness 57QT(58QT)) 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 8D and the tank wall free connector 4039VC1(2)-A, pin <H.
(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 8C and the tank wall free connector 4039VC1(2)-A, pin <X.
(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 15E 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 13E).
(f) Do a check AWM 284611 of the aircraft wiring (FLSCU-1 T1 output line) between the FLSCU-1 rack connector AB, pin 4C and the FQIC rack connector AC, pin 2J or ( AWM 284612 of the aircraft wiring (FLSCU-2 T1 output line) between the FLSCU-2 rack connector AB, pin 4C and the FQIC rack connector AC, pin 3F).
(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 of the HARNESS-LEFT WING TANK A [57QT] ( HARNESS-RIGHT WING, TANK A [58QT] ) AWM 284611 ( AWM 284612) and replace, if necessary AMM 28-42-43-000-005 and AMM 28-42-43-400-005.
(c) If the harness is serviceable, replace the SENSOR-TEMP, LEFT WING TK INNER CHANNEL A [29QJ1] ( SENSOR-TEMP, RIGHT WING TK INNER CHANNEL A [29QJ2] ) AMM 28-46-17-000-001 and AMM 28-46-17-400-001.
Subtask 28-46-00-810-062-C ** ON A/C NOT FOR ALL NOTE: Where applicable, to show the difference between the left and right wing installations, the FINs given in this procedure are written as follows:
(1) Do the steps applicable to the test equipment available. - the left wing, no parenthesis, FIN
- the right wing, in parenthesis, (FIN).
(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).
(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 fuel temperatures shown on the ECAM FUEL page and the input parameter page 1 is the FQIS L(R) fuel-probe 54QT1(2).
In normal operation the ECAM and the FQIS input parameter page 1 temperature values:
(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. In normal operation the ECAM and the FQIS input parameter page 1 temperature values:
- are always available
- show the temperature of the ambient air space if the surface of the fuel goes below the temperature sensor.
(4) Get access to the tank wall connector 4039VC1(2)-A (for the wing tank harness 57QT(58QT)) 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 29QJ1(2) at the tank wall connector 4039VC1(2) between pins <H and <X 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 29QJ1(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.
| 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 |
(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:
(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). - 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.
1 If the (test) resistance value:
- is in tolerance, do step (8)
- is not in tolerance, do step (10).
(9) If the fault continues:
(a) Get access to the tank wall connector 4039VC1(2)-A (for the wing tank harness 57QT(58QT)) 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 8D and the tank wall free connector 4039VC1(2)-A, pin <H.
(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 8C and the tank wall free connector 4039VC1(2)-A, pin <X.
(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 15E 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 13E).
(f) Do a check AWM 284611 of the aircraft wiring (FLSCU-1 T1 output line) between the FLSCU-1 rack connector AB, pin 4C and the FQIC rack connector AC, pin 2J or ( AWM 284612 of the aircraft wiring (FLSCU-2 T1 output line) between the FLSCU-2 rack connector AB, pin 4C and the FQIC rack connector AC, pin 3F).
(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 of the HARNESS-LEFT WING TANK A [57QT] ( HARNESS-RIGHT WING, TANK A [58QT] ) AWM 284611 ( AWM 284612) and replace, if necessary AMM 28-42-43-000-005 and AMM 28-42-43-400-005.
(c) If the harness is serviceable, replace the SENSOR-TEMP, LEFT WING TK INNER CHANNEL A [29QJ1] ( SENSOR-TEMP, RIGHT WING TK INNER CHANNEL A [29QJ2] ) AMM 28-46-17-000-001 and AMM 28-46-17-400-001.
A. Procedure
(2) Test Equipment.
(a) If a value:
(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 29QJ1(2) at the tank wall connector 4039VC1(2) between pins <H and <X 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 29QJ1(2) as a function of temperature, have been calculated and are given in the table that follows.
(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.
1 If the (test) resistance value:
(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 8D and the tank wall free connector 4039VC1(2)-A, pin <H.
(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 8C and the tank wall free connector 4039VC1(2)-A, pin <X.
(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, 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, 9H).
(f) Do a check AWM 284611 of the aircraft wiring (FLSCU-1 T1 output line) between the FLSCU-1 rack connector AB, pin 4C and the FQIC rack connector AB, 5J or ( AWM 284612 of the aircraft wiring (FLSCU-2 T1 output line) between the FLSCU-2 rack connector AB, pin 4C and the FQIC rack connector AB, 15J).
(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 of the HARNESS-CHAN A, L WING TK INR [13QT1] ( HARNESS-CHAN A, R WING TK INR [13QT2] ) AWM 284611 ( AWM 284612) and replace, if necessary AMM 28-42-43-000-006 and AMM 28-42-43-400-006.
(c) If the harness is serviceable, replace the SENSOR-TEMP, LEFT WING TK INNER CHANNEL A [29QJ1] ( SENSOR-TEMP, RIGHT WING TK INNER CHANNEL A [29QJ2] ) AMM 28-46-17-000-001 and AMM 28-46-17-400-001.
NOTE: Where applicable, to show the difference between the left and right wing installations, the FINs given in this procedure are written as follows:
(1) Do the steps applicable to the test equipment available. - the left wing, no parenthesis, FIN
- the right wing, in parenthesis, (FIN).
(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).
(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 inner-cell fuel temperatures shown on the ECAM FUEL page and the input parameter page 1 are the specially selected diodes that are part of the FQIS L(R) fuel-probe 92QT1(2).
In normal operation the ECAM and the FQIS input parameter page 1 temperature values:
(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. In normal operation the ECAM and the FQIS input parameter page 1 temperature values:
- are always available
- show the temperature of the ambient air space if the surface of the fuel goes below the temperature sensor.
(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 29QJ1(2) at the tank wall connector 4039VC1(2) between pins <H and <X 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 29QJ1(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 inner-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 |
(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:
(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). - 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.
1 If the (test) resistance value:
- is in tolerance, do step (8)
- is not in tolerance, do step (10).
(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 8D and the tank wall free connector 4039VC1(2)-A, pin <H.
(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 8C and the tank wall free connector 4039VC1(2)-A, pin <X.
(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, 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, 9H).
(f) Do a check AWM 284611 of the aircraft wiring (FLSCU-1 T1 output line) between the FLSCU-1 rack connector AB, pin 4C and the FQIC rack connector AB, 5J or ( AWM 284612 of the aircraft wiring (FLSCU-2 T1 output line) between the FLSCU-2 rack connector AB, pin 4C and the FQIC rack connector AB, 15J).
(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 of the HARNESS-CHAN A, L WING TK INR [13QT1] ( HARNESS-CHAN A, R WING TK INR [13QT2] ) AWM 284611 ( AWM 284612) and replace, if necessary AMM 28-42-43-000-006 and AMM 28-42-43-400-006.
(c) If the harness is serviceable, replace the SENSOR-TEMP, LEFT WING TK INNER CHANNEL A [29QJ1] ( SENSOR-TEMP, RIGHT WING TK INNER CHANNEL A [29QJ2] ) AMM 28-46-17-000-001 and AMM 28-46-17-400-001.