Customer : THY Manual : TSM
Type : A318/A319/A320/A321 Selected applicability : 151-155
Rev. Date : May 01, 2017
28-16-00 PB 201 CONF 00 - FUEL RECIRCULATION
- COOLING - FAULT ISOLATION PROCEDURES
** ON A/C ALL
28-16-00 PB 201 CONF 00 - FUEL RECIRCULATION
- COOLING - FAULT ISOLATION PROCEDURES
TASK 28-16-00-810-801-A
IDG 1(2) Oil Overheating
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 IN-
TRINSICALLY SAFE TEST EQUIPMENT: EN50020, UL913 OR EQUIVALENT). TEST EQUIP-
MENT THAT IS NOT APPROVED CAN CAUSE FIRE OR AN EXPLOSION.
1. Possible Causes
· SENSOR-TEMP, LEFT WING TK OUTER CHANNEL A ( 30QJ1 )
· SENSOR-TEMP, RIGHT WING TK OUTER CHANNEL A ( 30QJ2 )
· SENSOR-TEMP, LEFT WING TK INNER CHANNEL A ( 29QJ1 )
· SENSOR-TEMP, RIGHT WING TK INNER CHANNEL A ( 29QJ2 )
· SENSOR-LOW LEVEL, LEFT WING TK INNER CHANNEL A ( 38QJ1 )
· SENSOR-LOW LEVEL, RIGHT WING TK INNER CHANNEL A ( 38QJ2 )
· SENSOR-HIGH LVL, LEFT WING SURGE TK CHANNEL A ( 28QJ1 )
· SENSOR-HIGH LVL, RIGHT WING SURGE TK CHANNEL A ( 28QJ2 )
· FLSCU-1 ( 7QJ )
· FLSCU-2 ( 9QJ )
· EGIU-1 ( 22XU1 )
· EGIU-2 ( 22XU2 )
· GCU-1 ( 1XU1 )
· GCU-2 ( 1XU2 )
· Fuel Return Valve (FRV)
· aircraft wiring
· VALVE-FUEL DIVERTER AND RETURN ( 4018KS )
· CHECK VALVE-FUEL RECIRCULATION, L ( 122QM )
· CHECK VALVE-FUEL RECIRCULATION, R ( 123QM )
· VALVE-PRESSURE HOLDING, L WING TANK ( 124QM )
· VALVE-PRESSURE HOLDING, R WING TANK ( 125QM )
· fuel recirculation (cooling) pipe
· VALVE-PRESSURE HOLDING ( 218QM )
· VALVE-PRESSURE HOLDING ( 219QM )
2 Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION
No specific AR MULTIMETER - STANDARD
B. Referenced Information
REFERENCE DESIGNATION
(Ref. 24-21-00-810-818-A). Loss of the IDG1 Temperature Indication
Print Date: July 13, 2017 Page 1 of 7
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : THY Manual : TSM
Type : A318/A319/A320/A321 Selected applicability : 151-155
Rev. Date : May 01, 2017
28-16-00 PB 201 CONF 00 - FUEL RECIRCULATION
- COOLING - FAULT ISOLATION PROCEDURES
REFERENCE DESIGNATION
(Ref. 24-21-00-810-819-A). Loss of the IDG2 Temperature Indication
(Ref. 28-46-00-810-812-A). L(R) Surge Tank Overflow Sensor 28QJ1(2)
(Ref. 28-46-00-810-813-A). L(R) Inner Temperature Sensor 29QJ1(2)
** ON A/C 001-049, 054-057, 059-100, 151-199, 601-602, 801-850, 901-901
(Ref. 28-46-00-810-814-A). L(R) Outer Temperature Sensor 30QJ1(2)
** ON A/C ALL
(Ref. 28-46-00-810-815-A). L(R) IDG Shut Off Sensor 38QJ1(2)
(Ref. 28-46-00-810-818-A). FLSCU1(2) 7QJ(9QJ)
Ref. AMM 12-11-28-650-003 Pressure Refuel with Automatic Control
Ref. AMM 12-11-28-650-004 Pressure Refuel with Manual Control
** ON A/C 054-057, 059-100, 151-199, 303-349, 351-399, 401-449, 501-599, 601-602, 651-700, 801-850
Ref. AMM 24-21-00-710-042 Operational Test of the IDG Disconnect and Reconnect (Reset) Func-
tion - Engine Static
** ON A/C ALL
Ref. AMM 28-00-00-000-001 Removal of the Fuel Pipes
Ref. AMM 28-00-00-400-001 Installation of the Fuel Pipes
** ON A/C 001-049, 054-057, 059-100, 151-199, 601-602, 801-850, 901-901
Ref. AMM 28-16-00-710-002 Operational Check of Fuel Recirculation Check Valve to Ensure Valve
not Failed Open
** ON A/C ALL
Ref. ASM 28-16-01
** ON A/C 001-049, 054-057, 059-100, 151-199, 601-602, 801-850, 901-901
Ref. AMM 28-16-41-000-001 Removal of the Pressure-Holding Valve
Ref. AMM 28-16-41-400-001 Installation of the Pressure-Holding Valve
** ON A/C ALL
Ref. AMM 28-16-42-000-001 Removal of the Fuel Recirculation Check-valve
Ref. AMM 28-16-42-400-001 Installation of the Fuel Recirculation Check-valve
Ref. AWM 28-21-07
Ref. AMM 28-46-34-000-001 Removal of the Fuel-Level Sensing Control-Unit (FLSCU)
Ref. AMM 28-46-34-400-001 Installation of the Fuel-Level Sensing Control-Unit (FLSCU)
Ref. AMM 31-60-00-860-001 EIS Start Procedure
** ON A/C 054-057, 059-100, 151-199, 303-349, 351-399, 401-449, 501-599, 601-602, 651-700, 801-850
Ref. AMM 71-00-00-710-012 Test No.3 : Idle Leak Check
Ref. AMM 73-13-42-000-010 Removal of the Fuel Diverter and Return Valve
Ref. AMM 73-13-42-400-010 Installation of the Fuel Diverter and Return Valve
Ref. AMM 73-13-42-720-010 Functional Test of the Fuel Recirculation Cooling System without Bar-
field Tester and without AIDS
Ref. AMM 73-22-00-740-040 Read Engine Scheduled Maintenance Report (SMR) for Unlimited (As-
terisked) Faults
Ref. AMM 73-25-34-000-041 Removal of the Engine Interface Unit (EIU)
Ref. AMM 73-25-34-400-041 Installation of the Engine Interface Unit (EIU)
Print Date: July 13, 2017 Page 2 of 7
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : THY Manual : TSM
Type : A318/A319/A320/A321 Selected applicability : 151-155
Rev. Date : May 01, 2017
28-16-00 PB 201 CONF 00 - FUEL RECIRCULATION
- COOLING - FAULT ISOLATION PROCEDURES
** ON A/C ALL
3. Fault Confirmation
Subtask 28-16-00-865-050-A
A. Table of the circuit breakers referred to in this procedure:
PANEL DESIGNATION FIN LOCATION
** ON A/C 001-049, 054-057, 059-100, 151-199, 303-349, 351-399, 401-449, 501-599, 601-602, 651-700
121VU FUEL/PUMPS/2/R CTL AND L IND 10QA R29
121VU FUEL/PUMPS/1/L CTL AND R IND 3QA R23
** ON A/C 001-049, 054-057, 059-100, 151-199, 601-602
121VU FUEL/CTR TK/PUMPS1 AND 2/CTL AND 32QA R26
IND
121VU FUEL/CTR TK/PUMPS1 AND 2/CTL AND 31QA R25
IND
** ON A/C 054-057, 059-100, 151-199, 601-602, 801-850
Subtask 28-16-00-710-050-D
B. Test
(1) Do a check of the MAINTENANCE POST FLIGHT REPORT (PFR) for the ECAM WARNING
MESSAGES that follow:
· FUEL L(R) TK PUMP 1 LO PR
· FUEL L(R) TK PUMP 2 LO PR
· FUEL CTR TK PUMP 1(2) LO PR
· FUEL X FEED VALVE FAULT.
(2) Do a check of the PFR for the FAULT MESSAGES and Read Engine Scheduled Maintenance Report
Ref. AMM 73-22-00-740-040 for the system messages that follow:
· 24-21-51 IDG1(2) (OVERTEMP) or any other IDG related message
· 28-46-15 FUEL LEVEL SENSING L(R) LO LEVEL SENSOR 38QJ1(2)
· 28-46-16 FUEL LEVEL SENSING L(R) SURGE SENSOR 28QJ1(2)
· 28-46-17 FUEL LEVEL SENSING L(R) INN TEMP SENSOR 29QJ1(2)
· 28-46-17 FUEL LEVEL SENSING L(R) OUT TEMP SENSOR 30QJ1(2)
· 28-46-34 FUEL LEVEL SENSING FLSCU 1(2) 7QJ(9QJ)
· 73-13-42 FUL DIV RET VLV/HC/EEC1(2)
· 73-22-00 HMS-ENG OIL OVTMP1(2)
· 73-22-00 HMS-FUEL OVTMP1(2)
· 73-22-00 HMS-IDG OIL OVTMP1(2)
· 73-22-00 HMS-IDG OVTMP W/RECIRC1(2)
· 73-35-15 FUEL TEMP SENS/HC/EEC1(2)
· 79-21-51 ACOC AIR MOD VLV/HC/EEC1(2)
· 79-32-16 ACOC OIL TEMP TC/HC/EEC1(2)
· 79-40-00 IDG OIL TEMP TC/HC/EEC1(2).
NOTE: Failure of the sensors may not be shown in the fault message as a sensor fault. But the failure
of a sensor could be shown by a failure of the FLSCU 1(2) 7QJ(9QJ).
(3) If any warnings (listed in step (2)) and/or messages (listed in step (3)) are shown, time correlate the
warnings and messages as applicable.
Print Date: July 13, 2017 Page 3 of 7
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : THY Manual : TSM
Type : A318/A319/A320/A321 Selected applicability : 151-155
Rev. Date : May 01, 2017
28-16-00 PB 201 CONF 00 - FUEL RECIRCULATION
- COOLING - FAULT ISOLATION PROCEDURES
(4) Go to the applicable ATA Chapter with these fault symptoms (warnings and/or messages). Do the
trouble shooting procedure related to the failure message before you continue with more steps:
· for SENSOR-TEMP, LEFT WING TK OUTER CHANNEL A ( 30QJ1 ) ( SENSOR-TEMP, RIGHT
WING TK OUTER CHANNEL A ( 30QJ2 ) ) (Ref. TSM 28-46-00-810-814)
· for SENSOR-TEMP, LEFT WING TK INNER CHANNEL A ( 29QJ1 ) ( SENSOR-TEMP, RIGHT
WING TK INNER CHANNEL A ( 29QJ2 ) ) (Ref. TSM 28-46-00-810-813)
· for SENSOR-LOW LEVEL, LEFT WING TK INNER CHANNEL A ( 38QJ1 ) ( SENSOR-LOW
LEVEL, RIGHT WING TK INNER CHANNEL A ( 38QJ2 ) ) (Ref. TSM 28-46-00-810-815)
· for SENSOR-HIGH LVL, LEFT WING SURGE TK CHANNEL A ( 28QJ1 ) ( SENSOR-HIGH LVL,
RIGHT WING SURGE TK CHANNEL A ( 28QJ2 ) ) (Ref. TSM 28-46-00-810-812)
· for FLSCU-1 ( 7QJ ) ( FLSCU-2 ( 9QJ ) ) (Ref. TSM 28-46-00-810-818) .
(5) If necessary reconnect the applicable IDG 1(2) Ref. AMM 24-21-00-710-042 .
(6) Make sure that the C/Bs that follow are closed:
· C/B-FUEL/CTR TK/PUMPS 1 AND 2/CTL AND IND (31QA)
· C/B-FUEL/CTR TK/PUMPS 1 AND 2/CTL AND IND (32QA).
NOTE: If the related DC BUS is not powered and the C/Bs not closed the applicable FLSCU cannot
issue/supply an IDG/FRV open command. This is because a FLSCU will give a false CLOSE
IDG/FRV output when it is not powered (de-energized condition).
(7) Do the EIS Start Procedure (ECAM only) Ref. AMM 31-60-00-860-001 .
(8) On the ECAM control panel, push (in) the FUEL P/BSW.
(9) Make sure that the FUEL page shows on the ECAM lower Display Unit (DU).
(10) Monitor the FUEL system display (lower ECAM DU) and make sure that:
· all the fuel pumps are shown green in-line
· the outer cell temperature is less than 55 deg C
· the inner cell temperature is less than 52.5 deg C
· the inner cell contains more than 270 kg (595.2479 lb) of fuel (IDG Shut Off Sensor 38QJ1(2) wet)
refuel if necessary Ref. AMM 12-11-28-650-003 or Ref. AMM 12-11-28-650-004
· the Crossfeed Valve is open.
NOTE: These fuel conditions will let the IDG cooler fuel be returned to the related wing tank if neces-
sary.
(11) Do the power plant Idle Leak Check Ref. AMM 71-00-00-710-012 .
(12) On the ECAM control panel, push (in) the ELECT P/BSW.
(13) On the ELECT system display (lower ECAM DU), monitor the IDG 1 and IDG 2 oil temperatures.
(14) If any of IDG conditions that follow are shown, go to Para. 4.A:
· an IDG 1(2) OIL OVHT message, and
· the IDG 1(2) Oil Temperature shows pulsing green (more than the specified limit), or
· the IDG 1(2) Oil Temperature shows amber (high), or
(15) If the IDG 1(2) Oil Temperature is more than IDG 2(1) and there is no ATA 24 maintenance message:
NOTE: The difference between these values can be caused by a fault in the EGIU-1 ( 22XU1 ) (
EGIU-2 ( 22XU2 ) ) or GCU-1 ( 1XU1 ) ( GCU-2 ( 1XU2 ) ).
(a) Do the Fault Isolation steps in the trouble shooting procedure:
· For IDG 1 do the Loss of the IDG1 Temperature Indication procedure (Ref. TSM 24-21-00-
810-818)
Print Date: July 13, 2017 Page 4 of 7
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : THY Manual : TSM
Type : A318/A319/A320/A321 Selected applicability : 151-155
Rev. Date : May 01, 2017
28-16-00 PB 201 CONF 00 - FUEL RECIRCULATION
- COOLING - FAULT ISOLATION PROCEDURES
· For IDG 2 do the Loss of the IDG2 Temperature Indication procedure (Ref. TSM 24-21-00-
810-819) .
(b) If the fault continues, go to Para. 4.A.
** ON A/C ALL
4. Fault Isolation
** ON A/C 054-057, 059-100, 151-199, 601-602, 801-850
Subtask 28-16-00-810-050-D
A. Procedure
(1) If the failure is related to IDG-1, remove the Engine Interface Unit (EIU) 1KS1 Ref. AMM 73-25-34-
000-041 .
(2) If the failure is related to IDG-2, remove the EIU 1KS2 Ref. AMM 73-25-34-000-041 .
(3) Use a MULTIMETER - STANDARD, to do a test Ref. ASM 28-16-01 to see if there is a ground at the
EIU rack connector 1KS1(2)-AA, pin 2A.
NOTE: This step checks the input to the EIU, of the fuel logic for the IDG cooling, from the related
FLSCU-1(2) 7QJ(9QJ).
(4) If there is a ground on pin 2A of the rack connector 1KS1(2)-AA, go to step (6) (unserviceable).
NOTE: This shows that the EIU does not get an open command, for the valve-fuel diverter and return,
from the FLSS, 28-46-00.
(5) If there is no ground on pin 2A of the rack connector 1KS1(2)-AA (serviceable):
NOTE: This is the correct logic output from the FLSS, 28-46-00 for the conditions (inputs) given in
Para. 3.B.(11) and will let the valve-fuel diverter and return open if required.
(a) Install the EIU 1KS1(1KS2) removed in step (1) or (2) Ref. AMM 73-25-34-400-041 .
(b) Do a check of the applicable VALVE-FUEL DIVERTER AND RETURN ( 4018KS ) Ref.
AMM 73-13-42-720-010 and replace, if necessary, Ref. AMM 73-13-42-000-010 and Ref.
AMM 73-13-42-400-010 .
(c) If the fault continues:
1 Go to Para. 3.B. and do the examination of the fault symptoms again for a possible
alternative entry point(s).
2 Go to Para. 4.B. - Fuel Recirculation (Cooling) Pipe Trouble-shooting.
(6) Remove the related FLSCU Ref. AMM 28-46-34-000-001 .
(7) If the ground seen in step (4):
(a) Is still shown (with the FLSCU removed):
1 Do a check of the aircraft wiring (IDG fuel logic output wire) Ref. ASM 28-16-01 between:
· the related FLSCU rack connector AA, pin 4D and the related EIU rack connector AA, pin
2A.
2 Repair all the unserviceable wiring and connectors.
3 Install the FLSCU removed in step (6) Ref. AMM 28-46-34-400-001 .
4 Do the test given in step (3).
Print Date: July 13, 2017 Page 5 of 7
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : THY Manual : TSM
Type : A318/A319/A320/A321 Selected applicability : 151-155
Rev. Date : May 01, 2017
28-16-00 PB 201 CONF 00 - FUEL RECIRCULATION
- COOLING - FAULT ISOLATION PROCEDURES
5 Install the EIU removed in step (1) or (2) Ref. AMM 73-25-34-400-041 .
6 Do the test given in Para. 3.B.
(b) Is not shown (with the FLSCU removed):
1 Replace the FLSCU-1 ( 7QJ ) ( FLSCU-2 ( 9QJ ) ) with a serviceable item and install Ref.
AMM 28-46-34-400-001 .
2 Do a check of the aircraft wiring (that is common to FLSCU-1 and FLSCU-2) Ref. ASM 28-
16-01 and Ref. AWM 28-21-07 between:
· the FLSCU-1 rack connector AA, pin 14C and the FLSCU-2 rack connector AA, pin 14D
· the FLSCU-1 rack connector AA, pin 14D and the FLSCU-2 rack connector AA, pin 14C
· the FLSCU-1 rack connector AA, pin 12D and the actuator-crossfeed valve free connector
5QE-A, pin B
· the FLSCU-2 rack connector AA, pin 12D and the actuator-crossfeed valve free connector
5QE-A, pin B.
3 For a IDG 1 failure, do a check of the aircraft wiring Ref. ASM 28-16-01 and Ref. AWM
28-21-07 between:
· the FLSCU-1 rack connector AA, pin 13C and the PRESS SW-FUEL PUMP No. 1, L
WING TK connector 23QA-A, pin C
· the FLSCU-1 rack connector AA, pin 13D and the PRESS SW-FUEL PUMP No. 2, L
WING TK connector 27QA-A, pin C
· the FLSCU-1 rack connector AA, pin 12C and the ground DC2 at 606VG
· the FLSCU-1 rack connector AA, pin 1D and the C/B-FUEL/CTR TK/L&R XFR/CTL & IND
(1QL).
4 For a IDG 2 failure, do a check of the aircraft wiring Ref. ASM 28-16-01 between: and Ref.
AWM 28-21-07 between:
· the FLSCU-2 rack connector AA, pin 13C and the PRESS SW-FUEL PUMP No. 1, R
WING TK connector 24QA-A, pin C
· the FLSCU-2 rack connector AA, pin 13D and the PRESS SW-FUEL PUMP No. 2, R
WING TK connector 28QA-A, pin C
· the FLSCU-2 rack connector AA, pin 12C and the ground DC1 at 600VG
· the FLSCU-2 rack connector AA, pin 1D and the C/B-FUEL/CTR TK/L&R XFR/CTL & IND
(2QL).
5 Repair all the unserviceable wiring and connectors.
6 Install the FLSCU removed in step (6) Ref. AMM 28-46-34-400-001 .
7 Do the test given in step (3).
8 Install the EIU removed in step (1) or (2) Ref. AMM 73-25-34-400-041 .
9 Do the test given in Para. 3.B.
** ON A/C 001-049, 054-057, 059-100, 151-199, 601-602, 801-850, 901-901
Subtask 28-16-00-810-059-A
B. Procedure - Fuel Recirculation (Cooling) Pipe Trouble-shooting
(1) Do the Operational Test of the Fuel Recirculation Check Valve 122QM (123QM) Ref. AMM 28-16-00-
710-002 .
(2) If necessary, replace the CHECK VALVE-FUEL RECIRCULATION, L ( 122QM ) ( CHECK VALVE-
FUEL RECIRCULATION, R ( 123QM ) ) Ref. AMM 28-16-42-000-001 and Ref. AMM 28-16-42-400-
001 .
Print Date: July 13, 2017 Page 6 of 7
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : THY Manual : TSM
Type : A318/A319/A320/A321 Selected applicability : 151-155
Rev. Date : May 01, 2017
28-16-00 PB 201 CONF 00 - FUEL RECIRCULATION
- COOLING - FAULT ISOLATION PROCEDURES
(3) If necessary, replace the VALVE-PRESSURE HOLDING, L WING TANK ( 124QM ) ( VALVE-
PRESSURE HOLDING, R WING TANK ( 125QM ) ) Ref. AMM 28-16-41-000-001 and Ref. AMM 28-
16-41-400-001 .
(4) Do the test given in Para. 3.B.
(5) If the fault continues, do a check of the fuel recirculation (cooling) pipe for damage or blockage and
replace, if necessary, Ref. AMM 28-00-00-000-001 and Ref. AMM 28-00-00-400-001 .
(6) Do the test given in Para. 3.B.
End of document
Print Date: July 13, 2017 Page 7 of 7
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
