W DOC AIRBUS | TSM A320F

Fuel - Discrepancies Between The Fuel Temperature Warnings/Advisories and The Related Fuel Temperature Indication Given On The FUEL System Display Page

TASK 28-42-00-810-869-A
Fuel - Discrepancies Between The Fuel Temperature Warnings/Advisories and The Related Fuel Temperature Indication Given On The FUEL System Display Page

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
2. Job Set-up Information
 A. Referenced Information
REFERENCE
DESIGNATION
TSM TASK 28-42-00-810-801-A
Fuel Quantity Indication Computer (FQIC) 3QT
TSM TASK 28-42-00-810-805-A
Fuel Quantity/Temperature Probe 22QT1(2), Left(Right) Wing Tank
TSM TASK 28-42-00-810-816-A
Fuel Quantity/Temperature Probe 33QT1(2), Left(Right) Wing Tank
TSM TASK 28-42-00-810-830-A
Fuel Quantity/Temperature Probe 54QT1(2), Left(Right) Wing Tank
TSM TASK 28-42-00-810-884-A
Fuel Quantity/Temperature Probe 92QT1(2), Left(Right) Wing Tank
TSM TASK 28-42-00-810-885-A
Fuel Quantity/Temperature Probe 93QT1(2), Left(Right) Wing Tank
AMM 28-42-34-000-001
Removal of the Fuel Quantity-Indicating Computer (FQIC)
AMM 28-42-34-400-001
Installation of the Fuel Quantity-Indicating Computer (FQIC)
AMM 31-32-00-860-001
Procedure to Get Access to the SYSTEM REPORT/TEST Menu Page
AMM 31-36-00-740-008
Access to the Parameter Call-Up Menus
3. Fault Confirmation
Subtask 28-42-00-865-103-A
A. Table of the circuit breakers used in this procedure:
PANELDESIGNATIONFINLOCATION
** ON A/C ALL
49VUFUEL/FQI/CHAN/11QTA13
121VUFUEL/FQI/CHAN/22QTM27
Subtask 28-42-00-710-110-A ** ON A/C NOT FOR ALL
B. Test
   (1) Apply electrical power to the FQI system.
OR (if the FQIS is already powered).
Reset the FQIC. (Open, then after 5 seconds, close the two C/Bs 1QT and 2QT).
NOTE: This starts the FQIC Bite sequence that continues for approximately 60 seconds. It is divided into two main parts:
  • the first part is the FQIS test during which time XXs are shown on the FQIs for 35 seconds
  • the second part is the FLSS test which continues for approximately 25 seconds more.
   (2) When the BITE test is complete, set the Multipurpose Control and Display Unit (MCDU) to:
     (a) SYSTEM REPORT/TEST AMM 31-32-00-860-001.
     (b) FUEL.
     (c) FQIS STATUS.
NOTE: Temperature General
The Fuel Quantity Indiction System (FQIS) uses four (4) probes to measure the fuel temperature every sixty (60) seconds. There are two (2) fuel quantity/temperature probes in each wing tank. One is in each collector cell, 22QT1(2), and one is in each outer cell, 33QT1(2).
The fuel quantity/temperature probes have diodes which have been selected for improved temperature accuracy.
NOTE: Temperature warnings and advisories are all transmitted on ARINC Label 270 as specified in the table that follows.
TANK LOCATION & DESCRIPTION
TEMPERATURE
BIT LOCATION
L/O CELL HI TEMP. ADVISORY
> 55.0 deg. C
BIT 13
R/O CELL HI TEMP. ADVISORY
> 55.0 deg. C
BIT 19
L/I CELL HI TEMP. ADVISORY
> 45.0 deg. C
BIT 15
R/I CELL HI TEMP. ADVISORY
> 45.0 deg. C
BIT 17
L/O CELL LO TEMP. ADVISORY
< -38.5 deg. C
BIT 14
R/O CELL LO TEMP. ADVISORY
< -38.5 deg. C
BIT 20
L/I CELL LO TEMP. ADVISORY
< -38.5 deg. C
BIT 16
R/I CELL LO TEMP. ADVISORY
< -38.5 deg. C
BIT 18
L/O CELL HI TEMP. WARNING
> 60.0 deg. C
BIT 22
R/O CELL HI TEMP. WARNING
> 60.0 deg. C
BIT 28
L/I CELL HI TEMP. WARNING
> 53.5 deg. C
BIT 24
R/I CELL HI TEMP. WARNING
> 53.5 deg. C
BIT 26
L/O CELL LO TEMP. WARNING
< -43.5 deg. C
BIT 23
R/O CELL LO TEMP. WARNING
< -43.5 deg. C
BIT 29
L/I CELL LO TEMP. WARNING
< -43.5 deg. C
BIT 25
R/I CELL LO TEMP. WARNING
< -43.5 deg. C
BIT 27
Where,
L/O = left outer fuel cell/tank
L/I = left inner fuel cell/tank
R/I = right inner fuel cell/tank
R/O = right outer fuel cell/tank.

When the temperature warning/advisory limit is attained the appropriate bit is set to 1, otherwise these bits are set to 0.

The FUEL L/R INNER/OUTER HI TEMP, temperature warnings are announced by:
  • the master caution light
  • a single chime aural warning
  • the warning message on the upper ECAM display
  • the automatic call of the FUEL system display page. The temperature value of the applicable tank will be shown in amber.

The FUEL L/R INNER/OUTER LO TEMP, temperature warnings are announced by:
  • the warning message on the upper ECAM display
  • the automatic call of the FUEL system display page. The temperature value of the applicable tank will be shown in amber.

The fuel temperature advisories are announced by the automatic call of the FUEL system display page. The temperature value of the applicable tank will be shown pulsing green.

The related bits (in the table before) are set to 0 when the appropriate source is failed.
For each outer cell these bits are also set to 0 when the sensing diode of the corresponding probe number 13 is not in fuel.
This is indicated to ECAM, so that the Outer Cell Temperature Display can be blanked by setting the ARINC Label 270 bits that follow to 1 when the related temperature element is dry (not fully immersed).
  • Bit 11 - Left Outer Cell Temperature State
  • Bit 12 - Right Outer Cell Temperature State.
NOTE: The fuel temperature for each cell is transmitted with the ARINC Labels as follows:
  • Label 176 - Left Outer Cell Fuel Temperature
  • Label 177 - Left Inner Cell Fuel Temperature
  • Label 201 - Right Inner Cell Fuel Temperature
  • Label 202 - Right Outer Cell Fuel Temperature.
For each inner cell, when the sensing diode of the corresponding probe number 2 is dry (not in fuel), the FUEL system display related temperature indiction shows the air temperature.
NOTE: OPTIONAL TESTING
If necessary further trouble shooting can be done with an ARINC reader or AIDS. Refer to the data given.
Subtask 28-42-00-710-110-B ** ON A/C NOT FOR ALL
B. Test
   (1) Apply electrical power to the FQI system.
OR (if the FQIS is already powered).
Reset the FQIC. (Open, then after 10 seconds, close the two C/Bs 1QT and 2QT).
NOTE: This starts the FQIC Bite sequence that continues for approximately 100 seconds. It is divided into two main parts:
  • the first part is the FQIS test during which time XXs are shown on the FQIs for approximately 75 seconds
  • the second part is the FLSS test which continues for approximately 25 seconds more.
   (2) When the BITE test is complete, set the Multi Purpose Control and Display Unit (MCDU) to:
     (a) SYSTEM REPORT/TEST AMM 31-32-00-860-001.
     (b) FUEL.
     (c) FQIS STATUS.
NOTE: Temperature General
The Fuel Quantity Indiction System (FQIS) uses two (2) probes to measure the fuel temperature. There is one (1) fuel quantity/temperature probe in each wing tank collector cell 54QT1(2).
Each of the fuel quantity/temperature probes contains two platinum bead thermistor sensors that function as Resistance Temperature Detectors (RTD).
Each of the temperature sensors is connected to the tank wall connectors by a different wing tank harness.
NOTE: Temperature warnings and advisories are all transmitted on ARINC Label 270 as specified in the table that follows.
TANK LOCATION & DESCRIPTION
TEMPERATURE
BIT LOCATION
SET TO 0
BIT 13
SET TO 0
BIT 19
LEFT WING HI TEMP. ADVISORY
> 46.5 deg. C
BIT 15
RIGHT WING HI TEMP. ADVISORY
> 46.5 deg. C
BIT 17
SET TO 0
BIT 14
SET TO 0
BIT 20
LEFT WING LO TEMP. ADVISORY
< -40.0 deg. C
BIT 16
RIGHT WING LO TEMP. ADVISORY
< -40.0 deg. C
BIT 18
SET TO 0
BIT 22
SET TO 0
BIT 28
LEFT WING HI TEMP. WARNING
> 55.0 deg. C
BIT 24
RIGHT WING HI TEMP. WARNING
> 55.0 deg. C
BIT 26
SET TO 0
BIT 23
SET TO 0
BIT 29
LEFT WING LO TEMP. WARNING
< -45.0 deg. C
BIT 25
RIGHT WING LO TEMP. WARNING
< -45.0 deg. C
BIT 27
When the temperature warning/advisory limit is attained the appropriate bit is set to 1, otherwise these bits are set to 0.

The FUEL L/R WING TK HI TEMP, temperature warnings are announced by:
  • the master caution light
  • a single chime aural warning
  • the warning message on the upper ECAM display
  • the automatic call of the FUEL system display page. The temperature value of the applicable tank will be shown in amber.

The FUEL L/R WING TK LO TEMP, temperature warnings are announced by:
  • the warning message on the upper ECAM display
  • the automatic call of the FUEL system display page. The temperature value of the applicable tank will be shown in amber.

The fuel temperature advisories are announced by the automatic call of the FUEL system display page. The temperature value of the applicable tank will be shown pulsing green.

If the fuel temperature data is unavailable due to low fuel state in a tank, or if failed, the temperature warnings and advisories for that tank are inhibited.
Since the outer cell temperature probes are only installed in A319/A320 aircraft the related fuel temperatures are blanked on the FUEL system display page of A321 aircraft. This is transmitted to ECAM on ARINC Label 270 as follows:
  • Bit 11 - Left Outer Cell Temperature State - set to 1
  • Bit 12 - Right Outer Cell Temperature State - set to 1.
NOTE: The fuel temperature for each cell is transmitted with the ARINC Labels as follows:
  • Label 176 - Left Outer Cell Fuel Temperature - Not applicable for standard 2 aircraft - set to zero
  • Label 177 - Fuel TemperatureLeft Wing Tank
  • Label 201 - Fuel Temperature Right Wing Tank
  • Label 202 - Right Outer Cell Fuel Temperature - Not applicable for standard 2 aircraft - set to zero.
NOTE: OPTIONAL TESTING
If necessary further trouble shooting can be done with an ARINC reader or AIDS. Refer to the data given.
Subtask 28-42-00-710-110-C ** ON A/C NOT FOR ALL
B. Test
   (1) Apply electrical power to the FQI system.
OR (if the FQIS is already powered).
Reset the FQIC. (Open, then after 5 seconds, close the two C/Bs 1QT and 2QT).
NOTE: This starts the FQIC Bite sequence that continues for approximately 60 seconds. It is divided into two main parts:
  • the first part is the FQIS test during which time XXs are shown on the FQIs for 35 seconds
  • the second part is the FLSS test which continues for approximately 25 seconds more.
   (2) When the BITE test is complete, set the Multipurpose Control and Display Unit (MCDU) to:
     (a) SYSTEM REPORT/TEST AMM 31-32-00-860-001.
     (b) FUEL.
     (c) FQIS STATUS.
NOTE: Temperature General
The Fuel Quantity Indication System (FQIS) uses four (4) probes to measure the fuel temperature every sixty (60) seconds. There are two (2) fuel quantity/temperature probes in each wing tank. One is in each collector cell, 92QT1(2), and one is in each outer cell, 93QT1(2).
The fuel quantity/temperature probes have diodes which have been selected for improved temperature accuracy.
NOTE: Temperature warnings and advisories are all transmitted on ARINC Label 270 as specified in the table that follows.
TANK LOCATION & DESCRIPTION
TEMPERATURE
BIT LOCATION
L/O CELL HI TEMP. ADVISORY
> 55.0 deg. C
BIT 13
R/O CELL HI TEMP. ADVISORY
> 55.0 deg. C
BIT 19
L/I CELL HI TEMP. ADVISORY
> 45.0 deg. C
BIT 15
R/I CELL HI TEMP. ADVISORY
> 45.0 deg. C
BIT 17
L/O CELL LO TEMP. ADVISORY
< -38.5 deg. C
BIT 14
R/O CELL LO TEMP. ADVISORY
< -38.5 deg. C
BIT 20
L/I CELL LO TEMP. ADVISORY
< -38.5 deg. C
BIT 16
R/I CELL LO TEMP. ADVISORY
< -38.5 deg. C
BIT 18
L/O CELL HI TEMP. WARNING
> 60.0 deg. C
BIT 22
R/O CELL HI TEMP. WARNING
> 60.0 deg. C
BIT 28
L/I CELL HI TEMP. WARNING
> 53.5 deg. C
BIT 24
R/I CELL HI TEMP. WARNING
> 53.5 deg. C
BIT 26
L/O CELL LO TEMP. WARNING
< -43.5 deg. C
BIT 23
R/O CELL LO TEMP. WARNING
< -43.5 deg. C
BIT 29
L/I CELL LO TEMP. WARNING
< -43.5 deg. C
BIT 25
R/I CELL LO TEMP. WARNING
< -43.5 deg. C
BIT 27
Where,
L/O = left outer fuel cell/tank
L/I = left inner fuel cell/tank
R/I = right inner fuel cell/tank
R/O = right outer fuel cell/tank.

When the temperature warning/advisory limit is attained the appropriate bit is set to 1, otherwise these bits are set to 0.

The FUEL L/R INNER/OUTER HI TEMP, temperature warnings are announced by:
  • the master caution light
  • a single chime aural warning
  • the warning message on the upper ECAM display
  • the automatic call of the FUEL system display page. The temperature value of the applicable tank will be shown in amber.

The FUEL L/R INNER/OUTER LO TEMP, temperature warnings are announced by:
  • the warning message on the upper ECAM display
  • the automatic call of the FUEL system display page. The temperature value of the applicable tank will be shown in amber.

The fuel temperature advisories are announced by the automatic call of the FUEL system display page. The temperature value of the applicable tank will be shown pulsing green.

The related bits (in the table before) are set to 0 when the appropriate source is failed.
For each outer cell these bits are also set to 0 when the sensing diode of the corresponding probe number 13 is not in fuel.
This is indicated to ECAM, so that the Outer Cell Temperature Display can be blanked by setting the ARINC Label 270 bits that follow to 1 when the related temperature element is dry (not fully immersed).
  • Bit 11 - Left Outer Cell Temperature State
  • Bit 12 - Right Outer Cell Temperature State.
NOTE: The fuel temperature for each cell is transmitted with the ARINC Labels as follows:
  • Label 176 - Left Outer Cell Fuel Temperature
  • Label 177 - Left Inner Cell Fuel Temperature
  • Label 201 - Right Inner Cell Fuel Temperature
  • Label 202 - Right Outer Cell Fuel Temperature.
For each inner cell, when the sensing diode of the corresponding probe number 2 is dry (not in fuel), the FUEL system display related temperature indiction shows the air temperature.
NOTE: OPTIONAL TESTING
If necessary further trouble shooting can be done with an ARINC reader or AIDS. Refer to the data given.
4. Fault Isolation
Subtask 28-42-00-810-118-A ** ON A/C NOT FOR ALL
A. Procedure
   (1) If the reported warning/advisory discrepancy is (or was) related to:
     (a) The Left Outer Tank
       1 Examine the FQIS STATUS page for the messages, L QTY PROBE 33QT1 and/or FQIC 3QT.
     (b) The Left Inner Tank
       1 Examine the FQIS STATUS page for the messages, L QTY PROBE 22QT1 and/or FQIC 3QT.
     (c) The Right Inner Tank
       1 Examine the FQIS STATUS page for the messages, R QTY PROBE 22QT2 and/or FQIC 3QT.
     (d) The Right Outer Tank
       1 Examine the FQIS STATUS page for the messages, R QTY PROBE 33QT2 and/or FQIC 3QT.
   (2) If the related failure message(s) is/are given on the FQIS STATUS page, do the trouble-shooting Task(s) as follows:
     (a) For FQIC 3QT message, do the Fuel Quantity Indication Computer (FQIC) 3QT (Ref. TSM TASK 28-42-00-810-801).
     (b) For L(R) QTY PROBE 22QT1(2) message, do the Fuel Quantity/Temperature Probe 22QT1(2), Left(Right) Inner Wing Tank (Ref. TSM TASK 28-42-00-810-805).
     (c) For L(R) QTY PROBE 33QT1(2) message, do the Fuel Quantity/Temperature Probe 33QT1(2), Left(Right) Outer Wing Tank (Ref. TSM TASK 28-42-00-810-816).
   (3) If none of these failure messages is given on the FQIS STATUS page. Set the MCDU to the related LAST/PREVIOUS LEG(s) report for the flight leg or incident when the discrepancy/failure was initially, and if necessary, subsequently reported.
NOTE: The FQIS STATUS page shows the aircraft LRUs that are currently failed.
The LAST/PREVIOUS LEG(s) report records previous aircraft LRU failures.
   (4) Examine the selected LAST/PREVIOUS LEG(s) report for the related messages as given in Step (1).
   (5) If this is the first incident of fuel temperature warning/advisory - fuel temperature indication discrepancy and the failure is not present on the ground:
     (a) Record the incident in the aircraft log if not already entered.
       1 Include the details that follow if available (see air/flight crew for some items):
         a Which warning/advisory was/was not shown.
         b The number of times the failure occured.
         c The duration of each occurance.
         d Maximumum (minimum) temperature value (shown on the FUEL system display page) of the tank (cell) related to the incident(s).
         e The fuel temperatures of the other tanks at the time of the incident(s).
         f The Fuel Quantity Indication (FQI) of all tanks (cells) at the time of the incident(s).
         g The FQIC serial number.
         h Print out, and keep for future reference the reports (related to the incident) that follow:
  • LAST LEG
  • PREVIOUS LEG (as applicable).
     (b) No further trouble-shooting is necessary, the related LRUs should remain installed for further monitoring.
   (6) If this is the second incident of fuel temperature warning/advisory - fuel temperature indication discrepancy, do the procedure that follows:
     (a) If the failure is shown (present on the ground) and AIDS is installed, monitor the related temperature warning/advisory bit and the related temperature display ARINC transmissions, Access to the Parameter call-up menus AMM 31-36-00-740-008.
NOTE: See Para. 3.B. for ARINC label and bit identification data.
EQ (Equipment identifier) for FQIC 3QT is 5A (Ref. AMM 313700, P. Block 1, Para. F.).
     (b) If the failure is shown (present on the ground), print out, and keep the reports that follow:
       1 FQIS STATUS.
       2 Input Parameters Page 1, FQIS INPUT PARAMETERS.
       3 Input Parameters Page 2, FQIS PROBE CAPACITANCIES.
     (c) If the failure is shown, or not shown, on the ground:
NOTE: Tag, and attach a copy of all the available related failure data, as given in Step (5), and if applicable Step (6), to the FQIC (3QT).
Subtask 28-42-00-810-118-B ** ON A/C NOT FOR ALL
A. Procedure
   (1) If the reported warning/advisory discrepancy is (or was) related to:
     (a) The Left Wing Tank
       1 Examine the FQIS STATUS page for the messages, L QTY PROBE 54QT1 and/or FQIC 3QT.
     (b) The Right Wing Tank
       1 Examine the FQIS STATUS page for the messages, R QTY PROBE 54QT2 and/or FQIC 3QT.
   (2) If the related failure message(s) is/are given on the FQIS STATUS page, do the trouble-shooting Task(s) as follows:
     (a) For FQIC 3QT message, do the Fuel Quantity Indication Computer (FQIC) 3QT (Ref. TSM TASK 28-42-00-810-801).
     (b) For L(R) QTY PROBE 54QT1(2) message, do the Fuel Quantity/Temperature Probe 54QT1(2), Left(Right) Wing Tank (Ref. TSM TASK 28-42-00-810-830).
   (3) If none of these failure messages is given on the FQIS STATUS page. Set the MCDU to the related LAST/PREVIOUS LEG(s) report for the flight leg or incident when the discrepancy/failure was initially, and if necessary, subsequently reported.
NOTE: The FQIS STATUS page shows the aircraft LRUs that are currently failed.
The LAST/PREVIOUS LEG(s) report records previous aircraft LRU failures.
   (4) Examine the selected LAST/PREVIOUS LEG(s) report for the related messages as given in Step (1).
   (5) If this is the first incident of fuel temperature warning/advisory discrepancy and a message is, or is not, shown:
     (a) Record the incident in the aircraft log if not already entered.
       1 Include the details that follow if available (see air/flight crew for some items).
         a Which warning/advisory was/was not shown.
         b The number of times the failure occured.
         c The duration of each occurance.
         d Maximumum (minimum) temperature value (shown on the FUEL system display page) of the wing tank related to the incident(s).
         e The fuel temperature of the other wing tank at the time of the incident.
         f The Fuel Quantity Indication (FQI) of all tanks at the time of the incident(s).
         g The FQIC serial number.
         h Print out, and keep, for future reference the reports (related to the incident) that follow:
  • LAST LEG
  • PREVIOUS LEG (as applicable).
     (b) No further trouble-shooting is necessary, the related LRUs should remain installed for further monitoring.
   (6) If this is the second incident of fuel temperature warning/advisory - fuel temperature indication discrepancy, do the procedure that follows:
     (a) If the failure is shown (present on the ground) and AIDS is installed, monitor the related temperature warning/advisory bit and the related temperature display ARINC transmissions, Access to the Parameter call-up menus AMM 31-36-00-740-008.
NOTE: See Para. 3.B. for ARINC label and bit identification data.
EQ (Equipment identifier) for FQIC 3QT is 5A (Ref. AMM 313700, P. Block 1, Para. F.).
     (b) If the failure is shown (present on the ground), print out, and keep the reports that follow:
       1 FQIS STATUS.
       2 Input Parameters Page 1, FQIS INPUT PARAMETERS.
       3 Input Parameters Page 2, FQIS PROBE CAPACITANCIES.
     (c) If the failure is shown, or not shown, on the ground:
NOTE: Tag, and attach a copy of all the available related failure data, as given in Step (5), and if applicable Step (6), to the FQIC (3QT).
Subtask 28-42-00-810-118-C ** ON A/C NOT FOR ALL
A. Procedure
   (1) If the reported warning/advisory discrepancy is (or was) related to:
     (a) The Left Outer Tank
       1 Examine the FQIS STATUS page for the messages, L QTY PROBE 93QT1 and/or FQIC 3QT.
     (b) The Left Inner Tank
       1 Examine the FQIS STATUS page for the messages, L QTY PROBE 92QT1 and/or FQIC 3QT.
     (c) The Right Inner Tank
       1 Examine the FQIS STATUS page for the messages, R QTY PROBE 92QT2 and/or FQIC 3QT.
     (d) The Right Outer Tank
       1 Examine the FQIS STATUS page for the messages, R QTY PROBE 93QT2 and/or FQIC 3QT.
   (2) If the related failure message(s) is/are given on the FQIS STATUS page, do the trouble-shooting Task(s) as follows:
     (a) For FQIC 3QT message, do the Fuel Quantity Indication Computer (FQIC) 3QT (Ref. TSM TASK 28-42-00-810-801).
     (b) For L(R) QTY PROBE 92QT1(2) message, do the Fuel Quantity/Temperature Probe 92QT1(2), Left(Right) Inner Wing Tank (Ref. TSM TASK 28-42-00-810-884).
     (c) For L(R) QTY PROBE 93QT1(2) message, do the Fuel Quantity/Temperature Probe 93QT1(2), Left(Right) Outer Wing Tank (Ref. TSM TASK 28-42-00-810-885).
   (3) If none of these failure messages is given on the FQIS STATUS page. Set the MCDU to the related LAST/PREVIOUS LEG(s) report for the flight leg or incident when the discrepancy/failure was initially, and if necessary, subsequently reported.
NOTE: The FQIS STATUS page shows the aircraft LRUs that are currently failed.
The LAST/PREVIOUS LEG(s) report records previous aircraft LRU failures.
   (4) Examine the selected LAST/PREVIOUS LEG(s) report for the related messages as given in Step (1).
   (5) If this is the first incident of fuel temperature warning/advisory - fuel temperature indication discrepancy and the failure is not present on the ground:
     (a) Record the incident in the aircraft log if not already entered.
       1 Include the details that follow if available (see air/flight crew for some items):
         a Which warning/advisory was/was not shown.
         b The number of times the failure occured.
         c The duration of each occurance.
         d Maximumum (minimum) temperature value (shown on the FUEL system display page) of the tank (cell) related to the incident(s).
         e The fuel temperatures of the other tanks at the time of the incident(s).
         f The Fuel Quantity Indication (FQI) of all tanks (cells) at the time of the incident(s).
         g The FQIC serial number.
         h Print out, and keep for future reference the reports (related to the incident) that follow:
  • LAST LEG
  • PREVIOUS LEG (as applicable).
     (b) No further trouble-shooting is necessary, the related LRUs should remain installed for further monitoring.
   (6) If this is the second incident of fuel temperature warning/advisory - fuel temperature indication discrepancy, do the procedure that follows:
     (a) If the failure is shown (present on the ground) and AIDS is installed, monitor the related temperature warning/advisory bit and the related temperature display ARINC transmissions, Access to the Parameter call-up menus AMM 31-36-00-740-008.
NOTE: See Para. 3.B. for ARINC label and bit identification data.
EQ (Equipment identifier) for FQIC 3QT is 5A (Ref. AMM 313700, P. Block 1, Para. F.).
     (b) If the failure is shown (present on the ground), print out, and keep the reports that follow:
       1 FQIS STATUS.
       2 Input Parameters Page 1, FQIS INPUT PARAMETERS.
       3 Input Parameters Page 2, FQIS PROBE CAPACITANCIES.
     (c) If the failure is shown, or not shown, on the ground:
NOTE: Tag, and attach a copy of all the available related failure data, as given in Step (5), and if applicable Step (6), to the FQIC (3QT).
[Rev.8 from Aug 2018] 2026.04.04 04:29:09 UTC
"WTRUIB" 2025