DOC AIRBUS | TSM A320FFault of the Power Transfer Unit (PTU)
TASK 29-23-00-810-801-A
Fault of the Power Transfer Unit (PTU)
1. Possible Causes
A. Referenced Information
3. Fault Confirmation
Subtask 29-23-00-710-051-A ** ON A/C NOT FOR ALL
Subtask 29-23-00-810-051-A
Subtask 29-23-00-860-050-A
[Rev.8 from Aug 2018]
2026.04.04 04:29:28 UTC
Fault of the Power Transfer Unit (PTU)
1. Possible Causes
- HYDR. PRESSURE TRANSMITTER [3065GN]
- HYDR. PRESSURE TRANSMITTER [1065GN]
P/BSW HYD/PTU/AUTO (1802GL) - TIME RELAY [3816GX]
- MANIFOLD,PTU [1113GM]
- MANIFOLD,PTU [3015GM]
- RELAY-LDG CTL [1805GL]
- wiring
- C/B-HYDRAULIC/SOL VALVES/G/Y/PTU [1801GL]
- RELIEF VALVE G SYS [1063GM]
- RELIEF VALVE Y SYS [3063GM]
- MANIFOLD,HP [1111GM]
MANIFOLD HP (3014GM) - SDAC-1 [1WV1]
- SDAC-2 [1WV2]
A. Referenced Information
| REFERENCE | DESIGNATION |
|---|---|
| AMM 24-41-00-861-002 | Energize the Aircraft Electrical Circuits from the External Power |
| AMM 24-41-00-862-002 | De-energize the Aircraft Electrical Circuits Supplied from the External Power |
| AMM 29-11-14-000-001 | Removal of the HP Manifold of the Green Hydraulic System |
| AMM 29-11-14-400-001 | Installation of the HP Manifold of the Green Hydraulic System |
| AMM 29-11-15-000-001 | Removal of the Power Transfer Unit (PTU) Manifold of the Green Hydraulic System |
| AMM 29-11-15-400-001 | Installation of the Power Transfer Unit (PTU) Manifold of the Green Hydraulic System |
| AMM 29-11-32-000-001 | Removal of the Pressure Relief Valve of the Green Hydraulic System |
| AMM 29-11-32-400-001 | Installation of the Pressure Relief Valve of the Green Hydraulic System |
| AMM 29-13-14-000-001 | Removal of the HP Manifold of the Yellow Hydraulic System |
| AMM 29-13-14-400-001 | Installation of the HP Manifold of the Yellow Hydraulic System |
| AMM 29-13-15-000-001 | Removal of the Power Transfer Unit (PTU) Manifold of the Yellow Hydraulic System |
| AMM 29-13-15-400-001 | Installation of the Power Transfer Unit (PTU) Manifold of the Yellow Hydraulic System |
| AMM 29-13-32-000-001 | Removal of the Pressure Relief Valve of the Yellow Hydraulic System |
| AMM 29-13-32-400-001 | Installation of the Pressure Relief Valve of the Yellow Hydraulic System |
| AMM 29-23-00-860-002 | Connection of the Isolation Coupling of the Power Transfer Unit (PTU) |
| ASM 292301 | |
| AMM 29-23-41-000-001 | Removal of the Green/Yellow Power Transfer Unit |
| AMM 29-23-41-400-001 | Installation of the Green/Yellow Power Transfer Unit |
| ASM 292401 | |
| AMM 29-32-11-000-001 | Removal of the Hydraulic Pressure Transducer |
| AMM 29-32-11-000-003 | Removal of the Hydraulic Pressure Transducer |
| AMM 29-32-11-400-001 | Installation of the Hydraulic Pressure Transducer |
| AMM 29-32-11-400-003 | Installation of the Hydraulic Pressure Transducer |
| AMM 31-55-34-000-001 | Removal of the SDAC |
| AMM 31-55-34-400-001 | Installation of the SDAC |
| AMM 31-60-00-860-001 | EIS Start Procedure |
| AMM 71-00-00-710-003 | Engine Automatic Start |
| AMM 71-00-00-710-028 | Engine Shutdown |
Subtask 29-23-00-710-051-A ** ON A/C NOT FOR ALL
A. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
(2) Make sure that the PTU P/BSW is set to the AUTO position (OFF light is off).
(3) Make sure that the cargo compartment doors are not in operation with the Yellow electric pump.
(4) Make sure that the isolation coupling of the PTU is connected AMM 29-23-00-860-002.
(5) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
AMM 31-60-00-860-001.
(6) Do an automatic start of the two engines AMM 71-00-00-710-003.
(8) Make sure that the HYD page is shown on the system display of the ECAM.
(9) Look for fault indications on the upper ECAM DU and the lower ECAM DU.
(10) Stop the engines AMM 71-00-00-710-028.
Subtask 29-23-00-710-051-C ** ON A/C NOT FOR ALL (1) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
(2) Make sure that the PTU P/BSW is set to the AUTO position (OFF light is off).
(3) Make sure that the cargo compartment doors are not in operation with the Yellow electric pump.
(4) Make sure that the isolation coupling of the PTU is connected AMM 29-23-00-860-002.
(5) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
AMM 31-60-00-860-001.
(6) Do an automatic start of the two engines AMM 71-00-00-710-003.
NOTE: If the second engine start is done less than 40 sec after the operation of the cargo doors (with the Yellow electric pump):
(7) On the ECAM control panel on the center pedestal, push the HYD pushbutton switch. - The HYD PTU FAULT message possibly comes on at the upper ECAM DU.
(8) Make sure that the HYD page is shown on the system display of the ECAM.
(9) Look for fault indications on the upper ECAM DU and the lower ECAM DU.
(10) Stop the engines AMM 71-00-00-710-028.
A. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
(2) Make sure that the PTU P/BSW is set to the AUTO position (OFF light is off).
(3) Make sure that the cargo compartment doors are not in operation with the Yellow electric pump.
(4) Make sure that the isolation coupling of the PTU is connected AMM 29-23-00-860-002.
(5) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
AMM 31-60-00-860-001.
(6) Do an automatic start of the two engines AMM 71-00-00-710-003.
(8) Make sure that the HYD page is shown on the system display of the ECAM.
(9) Look for fault indications on the upper ECAM DU and the lower ECAM DU.
(10) Stop the engines AMM 71-00-00-710-028.
4. Fault Isolation(1) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
(2) Make sure that the PTU P/BSW is set to the AUTO position (OFF light is off).
(3) Make sure that the cargo compartment doors are not in operation with the Yellow electric pump.
(4) Make sure that the isolation coupling of the PTU is connected AMM 29-23-00-860-002.
(5) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
AMM 31-60-00-860-001.
(6) Do an automatic start of the two engines AMM 71-00-00-710-003.
NOTE: If the second engine start is done less than 40 sec after the operation of the cargo doors (with the Yellow electric pump):
(7) On the ECAM control panel on the center pedestal, push the HYD pushbutton switch. - The HYD PTU FAULT message possibly comes on at the upper ECAM DU.
(8) Make sure that the HYD page is shown on the system display of the ECAM.
(9) Look for fault indications on the upper ECAM DU and the lower ECAM DU.
(10) Stop the engines AMM 71-00-00-710-028.
Subtask 29-23-00-810-051-A
A. Fault Isolation
(1) If after start of the second engine:
(b) Do the test in Para. 3 A.
(2) If the fault continues do the step that follows.
(3) If after start of the second engine:
(b) Do the test in Para. 3 A.
(4) If the fault continues do the step that follows.
(5) If after start of the second engine:
(6) If the fault continues do Para B.
Subtask 29-23-00-810-053-E (1) If after start of the second engine:
- The HYD Y ELEC PUMP LO PR on the upper ECAM DU is shown
(b) Do the test in Para. 3 A.
(2) If the fault continues do the step that follows.
(3) If after start of the second engine:
- The HYD PTU FAULT on the upper ECAM DU is shown
- The pressure difference in the hydraulic systems is more than 650 psi.
(b) Do the test in Para. 3 A.
(4) If the fault continues do the step that follows.
(5) If after start of the second engine:
- The HYD PTU FAULT on the upper ECAM DU is shown
- The pressure difference in the hydraulic systems is more than 650 psi.
(6) If the fault continues do Para B.
B. If after start of the second engine:
(a) Make sure that:
(3) If there is 28 VDC:
(a) Replace theP/BSW HYD/PTU/AUTO (1802GL) .
(b) Do the test in the Para. Fault Confirmation.
(4) If the fault continues:
(a) Do a check for 28 VDC at the TIME RELAY [3816GX] connector B1 ASM 292401.
(5) If there is 28 VDC:
(a) Replace the TIME RELAY [3816GX] .
(b) Do the test in the Para. Fault Confirmation.
(6) If the fault continues:
(a) Do a check and repair the wiring of the cargo compartment door operation system.
(7) Do the test in the Para. Fault Confirmation.
(8) If the fault continues:
(a) Replace the applicable MANIFOLD,PTU [1113GM] AMM 29-11-15-000-001 and AMM 29-11-15-400-001 or the MANIFOLD,PTU [3015GM] AMM 29-13-15-000-001 and AMM 29-13-15-400-001.
(9) If the fault continues:
(a) Do a check for 28VDC at the RELAY-LDG CTL [1805GL] connector A/A1 ASM 292301.
(10) If there is 28VDC:
(a) Do a check and repair the wiring between the RELAY-LDG CTL [1805GL] connector A/A2 and the C/B-HYDRAULIC/SOL VALVES/G/Y/PTU [1801GL] ASM 292301.
(b) Do the test in the Para. Fault Confirmation.
(11) If the fault continues:
(a) Replace the applicable RELIEF VALVE G SYS [1063GM] , AMM 29-11-32-000-001 and AMM 29-11-32-400-001
or the
RELIEF VALVE Y SYS [3063GM] , AMM 29-13-32-000-001 and AMM 29-13-32-400-001.
(b) Do the test in the Para. fault Confirmation.
(12) If the fault continues:
(a) Replace the MANIFOLD,HP [1111GM] , AMM 29-11-14-000-001 and AMM 29-11-14-400-001.
or the
MANIFOLD HP (3014GM) , AMM 29-13-14-000-001 and AMM 29-13-14-400-001.
(13) If the fault continues:
(a) Interchange the SDAC-1 [1WV1] and SDAC-2 [1WV2] AMM 31-55-34-000-001 and AMM 31-55-34-400-001.
(14) If the fault is removed:
(a) Replace the SDAC-1 [1WV1] AMM 31-55-34-000-001 and AMM 31-55-34-400-001.
Subtask 29-23-00-710-052-A - The HYD PTU FAULT on the upper ECAM DU is shown
- The hydraulic system of the second engine is not pressurized.
- The VALVEBLOCK, PTU (3112GL) connector A/A and the connector A/B
- The VALVEBLOCK, PTU (1112GL) connector A/A and the connector A/B ASM 292301.
(a) Make sure that:
- The wheel chocks are in position at the main landing gears
- The SW PARK BRK CTL (73GG) is set to off
- The Nose L/G is compressed
- A towing arm is not installed.
(3) If there is 28 VDC:
(a) Replace the
(b) Do the test in the Para. Fault Confirmation.
(4) If the fault continues:
(a) Do a check for 28 VDC at the TIME RELAY [3816GX] connector B1 ASM 292401.
(5) If there is 28 VDC:
(a) Replace the TIME RELAY [3816GX] .
(b) Do the test in the Para. Fault Confirmation.
(6) If the fault continues:
(a) Do a check and repair the wiring of the cargo compartment door operation system.
(7) Do the test in the Para. Fault Confirmation.
(8) If the fault continues:
(a) Replace the applicable MANIFOLD,PTU [1113GM] AMM 29-11-15-000-001 and AMM 29-11-15-400-001 or the MANIFOLD,PTU [3015GM] AMM 29-13-15-000-001 and AMM 29-13-15-400-001.
(9) If the fault continues:
(a) Do a check for 28VDC at the RELAY-LDG CTL [1805GL] connector A/A1 ASM 292301.
(10) If there is 28VDC:
(a) Do a check and repair the wiring between the RELAY-LDG CTL [1805GL] connector A/A2 and the C/B-HYDRAULIC/SOL VALVES/G/Y/PTU [1801GL] ASM 292301.
(b) Do the test in the Para. Fault Confirmation.
(11) If the fault continues:
(a) Replace the applicable RELIEF VALVE G SYS [1063GM] , AMM 29-11-32-000-001 and AMM 29-11-32-400-001
or the
RELIEF VALVE Y SYS [3063GM] , AMM 29-13-32-000-001 and AMM 29-13-32-400-001.
(b) Do the test in the Para. fault Confirmation.
(12) If the fault continues:
(a) Replace the MANIFOLD,HP [1111GM] , AMM 29-11-14-000-001 and AMM 29-11-14-400-001.
or the
(13) If the fault continues:
(a) Interchange the SDAC-1 [1WV1] and SDAC-2 [1WV2] AMM 31-55-34-000-001 and AMM 31-55-34-400-001.
(14) If the fault is removed:
(a) Replace the SDAC-1 [1WV1] AMM 31-55-34-000-001 and AMM 31-55-34-400-001.
C. Do the fault confirmation procedure as given in Para. 3. to make sure that operation is correct.
5. Close-upSubtask 29-23-00-860-050-A
A. Aircraft Maintenance Configuration.
(1) Make sure that the aircraft electrical circuits are de-energized AMM 24-41-00-862-002.
(1) Make sure that the aircraft electrical circuits are de-energized AMM 24-41-00-862-002.