No APU Bleed-Air Pressure, Low or Fluctuating APU Bleed-Air Pressure (with AIDS support) (APS 3200)

TASK 49-00-00-810-937-A
No APU Bleed-Air Pressure, Low or Fluctuating APU Bleed-Air Pressure (with AIDS support) (APS 3200)

1. Possible Causes

BLEED CONTROL VALVE (8051KM)
IGV ACTUATOR (8014KM)
FUEL CONTROL UNIT (8022KM)
ELECTRONIC CONTROL BOX [59KD]
FUEL FLOW DIVIDER (8024KM)
EGT THERMOCOUPLE 1 (8057KM1)
EGT THERMOCOUPLE 2 (8057KM2)
INLET TEMP/INLET PRESSURE SENSOR (8013KM)
LOAD COMPRESSOR DISCHARGE PRESSURE SENSOR (8039KM)
INLET TEMP/INLET PRESSURE SENSOR (8013MD)
FLOW CTL UNIT - PACK 1 [23HB]

2. Job Set-up Information
A. Referenced Information

REFERENCE	DESIGNATION
TSM TASK 49-00-00-810-903-A	Bleed Flow-Transducer Fault (APS 3200)
TSM TASK 49-00-00-810-904-A	APU AUTO SHUT DOWN - SURGE /REVERSE FLOW, Bleed Control Valve Fault (APS3200)
TSM TASK 49-00-00-810-905-A	APU AUTO SHUT DOWN - OVERTEMPERATURE, Inlet Guide Vane Actuator Fault (APS 3200)
TSM TASK 49-00-00-810-905-A-01	APU AUTO SHUT DOWN - OVERTEMPERATURE, Inlet Guide Vane Actuator Fault (with AIDS support) (APS 3200)
TSM TASK 49-00-00-810-908-A	Inlet Pressure/Temperature Sensor Fault (APS 3200)
TSM TASK 49-00-00-810-942-A	Bleed Control Valve Fault (APS 3200)
ESPM 2052210
ESPM 2053210
ESPM 205321A
AMM 21-51-51-000-001	Removal of the Pack Flow-Control Valve/ Pack Flow-Control Unit
AMM 21-51-51-400-001	Installation of the Pack Flow-Control Valve/ Pack Flow-Control Unit
AMM 49-00-00-710-005	Self-Test of the ECB
AMM 49-00-00-790-005	Air Leak Test with closed APU Doors
AMM 49-00-00-860-005	APU Start by External Power
AMM 49-00-00-860-006	APU Shutdown by External Power
AMM 49-11-11-000-003	Removal of the Power Plant (APU) (APS 3200)
AMM 49-11-11-400-003	Installation of the Power Plant (APU) (APS 3200)
AMM 49-20-00-290-001	APU Power Plant Borescope Inspection (APS 3200)
AMM 49-23-17-000-001	Removal of the Inlet Pressure/Temperature Sensor (APS 3200)
AMM 49-23-17-400-001	Installation of the Inlet Pressure/Temperature Sensor (APS 3200)
AMM 49-23-51-000-003	Removal of the Inlet Guide Vane Actuator (APS 3200)
AMM 49-23-51-400-003	Installation of the Inlet Guide Vane Actuator (APS 3200)
AMM 49-32-11-000-002	Removal of the Fuel Control Unit (APS 3200)
AMM 49-32-11-400-002	Installation of the Fuel Control Unit (APS 3200)
AMM 49-32-12-000-002	Removal of the Flow Divider (APS 3200)
AMM 49-32-12-400-002	Installation of the Flow Divider (APS 3200)
AMM 49-51-19-000-002	Removal of the Sensor - Compressor Discharge Pressure (APS 3200)
AMM 49-51-19-400-002	Installation of the Sensor - Compressor Discharge Pressure (APS 3200)
AMM 49-51-53-000-001	Removal of the Bleed Control Valve (APS 3200)
AMM 49-51-53-400-001	Installation of the Bleed Control Valve (APS 3200)
ASM 496102
ASM 496104
AMM 49-61-34-000-002	Removal of the Electronic Control Box (ECB) (APS 3200)
AMM 49-61-34-400-002	Installation of the Electronic Control Box (ECB) (APS 3200)
AMM 49-72-15-000-001	Removal of the Thermocouple (APS 3200)
AMM 49-72-15-400-002	Installation of the Thermocouple (APS 3200)
AMM 71-00-00-710-001	Dry Motoring Check
APU Bleed Parameters during different APU running states

3. Fault Confirmation
Subtask 49-00-00-710-308-B ** ON A/C NOT FOR ALL

WARNING: MAKE SURE THAT THE FWD AVIONICS ACCESS DOOR 811 IS OPEN WITH A WARNING PLACARD ATTACHED TO IT. THE WARNING NOTICE MUST TELL PERSONS NOT TO CLOSE THE DOOR. THIS PREVENTS ACCIDENTAL PRESSURIZATION OF THE AIRCRAFT.

A. Test

NOTE: Examine and record all indications shown on the APU system page (lower ECAM display unit) under the different mode conditions (specially the EGT and the BLEED pressure), during the test.

(1) Do the self test of the ECB AMM 49-00-00-710-005.

NOTE: If the self test gives a maintenance message, do the related trouble shooting procedure first before you continue with this test.

(2) Start and operate the APU AMM 49-00-00-860-005:

NOTE: On the AIR COND section on the overhead panel 30VU, make sure that the ENG 1 BLEED and the ENG 2 BLEED pushbutton switches are in the OFF position.

record the EGT on the APU page (lower ECAM display unit).

(3) On the AIR COND section on the overhead panel 30VU, push the APU BLEED pushbutton switch to ON.

record the EGT and the BLEED pressure on the APU page (lower ECAM display unit).

(4) On the AIR COND section on the overhead panel 30VU, push the PACK 1 pushbutton switch to on (the OFF legend is off).

record the BLEED pressure on the APU page (lower ECAM display unit).

(5) On the AIR COND section on the overhead panel 30VU, push the PACK 1 pushbutton switch to OFF (the OFF legend is on).

record the BLEED pressure on the APU page (lower ECAM display unit).

(6) On the AIR COND section on the overhead panel 30VU, push the PACK 2 pushbutton switch to on (the OFF legend is off).

record the BLEED pressure on the APU page (lower ECAM display unit).

(7) On the AIR COND section on the overhead panel 30VU, push also the PACK 1 pushbutton switch to on (the PACK 1 and PACK 2 OFF legends are off).

record the BLEED pressure on the APU page (lower ECAM display unit).

(8) On the AIR COND section on the overhead panel 30VU, push the PACK 1 and the PACK 2 pushbutton switches to OFF (the OFF legends are on).

record the BLEED pressure on the APU page (lower ECAM display unit).

(9) Do the dry motoring of the engine 1 AMM 71-00-00-710-001,

record the BLEED pressure on the APU page (lower ECAM display unit).

(10) Do the dry motoring of the engine 2 AMM 71-00-00-710-001.

record the BLEED pressure on the APU page (lower ECAM display unit).

(11) Do the APU shutdown AMM 49-00-00-860-006.

4. Fault Isolation
Subtask 49-00-00-810-264-B ** ON A/C NOT FOR ALL

A. If the self test gives the maintenance message:

BLEED CTL VLV (8051KM) (Ref. TSM TASK 49-00-00-810-904) if APU Autoshutdown,
BLEED CTL VLV (8051KM) (Ref. TSM TASK 49-00-00-810-942) if no APU Autoshutdown,
BLEED FLOW XDCR (8039KM) (Ref. TSM TASK 49-00-00-810-903),
INLET TEMP/PRESS SNSR (8013KM) (Ref. TSM TASK 49-00-00-810-908),
INLET GUIDE VANE ACTR (8014KM) (Ref. TSM TASK 49-00-00-810-905),

Subtask 49-00-00-810-266-B ** ON A/C NOT FOR ALL

B. If:
.there is no or low bleed pressure,
.the APU self test gives no maintenance message,
.the EGT does not rise and no increase in BLEED (PSI) pressure on the APU system page.

NOTE: Aircraft configuration:

the PACK 1 and 2 pushbutton switches are off,
the APU BLEED valve pushbutton switches is ON.

check the bleed control valve position during the APU operation.

(1) If the bleed control valve is not open:

replace the BLEED CONTROL VALVE (8051KM) AMM 49-51-53-000-001 and AMM 49-51-53-400-001.

Subtask 49-00-00-810-267-B ** ON A/C NOT FOR ALL

C. If:
.there is no or low bleed pressure,
.the APU self test gives no maintenance message,
.the EGT rises and the BLEED (PSI) pressure is low on the APU system page.

NOTE: Aircraft configuration:

the PACK 1 and 2 pushbutton switches are off,
the APU BLEED valve pushbutton switches is ON.

do a check of the bleed control valve position and the movement of the IGVs, during the APU operation.

(1) If the bleed control valve is not fully open:

replace the BLEED CONTROL VALVE (8051KM) AMM 49-51-53-000-001 and AMM 49-51-53-400-001.

(2) If the load control valve is fully open and the IGVs does not move:

replace the IGV ACTUATOR (8014KM) AMM 49-23-51-000-003 and AMM 49-23-51-400-003.

(a) If the fault continues:

replace the APU (4005KM) AMM 49-11-11-000-003 and AMM 49-11-11-400-003.

(b) If the fault continues:

do a check of the aircraft bleed system for leaks.

Subtask 49-00-00-810-268-A ** ON A/C NOT FOR ALL

D. If:
(1) IGV and EGT are out of range

do a check of the APU Bleed Ducts for cracks or leaks AMM 49-00-00-790-005.
If the fault continues:
replace the FUEL CONTROL UNIT (8022KM) AMM 49-32-11-000-002 and AMM 49-32-11-400-002.

If the fault continues:

do a check and repair the wiring from the ELECTRONIC CONTROL BOX [59KD] AB/11F,3J,10H ,11H to the FUEL CONTROL UNIT (8022KM) P19/1,2,3,4 ASM 496104 ESPM 2052210 ESPM 2053210 ESPM 205321A.

If the fault continues:

replace the FUEL FLOW DIVIDER (8024KM) AMM 49-32-12-000-002 and AMM 49-32-12-400-002.

If the fault continues:

replace the EGT THERMOCOUPLE 1 (8057KM1) and EGT THERMOCOUPLE 2 (8057KM2) AMM 49-72-15-000-001 and AMM 49-72-15-400-002.

If the fault continues:

replace the ELECTRONIC CONTROL BOX [59KD] AMM 49-61-34-000-002 and AMM 49-61-34-400-002.

If the fault continues:

do a borescope inspection of the APU AMM 49-20-00-290-001.

Subtask 49-00-00-810-269-B ** ON A/C NOT FOR ALL

E. If:
.the bleed pressure is low with both packs in operation,
.the APU self test gives no maintenance message.

NOTE: Aircraft configuration:

the PACK 1 and 2 pushbutton switches are on,
the APU BLEED valve pushbutton switches is ON.

replace the BLEED CONTROL VALVE (8051KM) AMM 49-51-53-000-001 and AMM 49-51-53-400-001.

(1) If the fault continues:

replace the INLET TEMP/INLET PRESSURE SENSOR (8013KM) AMM 49-23-17-000-001 and AMM 49-23-17-400-001.
replace the LOAD COMPRESSOR DISCHARGE PRESSURE SENSOR (8039KM) AMM 49-51-19-000-002 and AMM 49-51-19-400-002.

(2) If the fault continues:

replace the ELECTRONIC CONTROL BOX [59KD] AMM 49-61-34-000-002 and AMM 49-61-34-400-002.

Subtask 49-00-00-810-270-A ** ON A/C NOT FOR ALL

F. If:
The LCIT value differs from Ambient Temperature of more than 10 deg.C (50.00 deg.F), do a check for APU hot gas ingestion
If the fault continues:

replace the INLET TEMP/INLET PRESSURE SENSOR (8013KM) AMM 49-23-17-000-001 and AMM 49-23-17-400-001.

If the fault continues:

do a check and repair of the wiring from the ELECTRONIC CONTROL BOX [59KD] AB/D3,E6 to the INLET TEMP/INLET PRESSURE SENSOR (8013MD) P22/6,5 ASM 496102 ESPM 2052210 ESPM 2053210 ESPM 205321A.

If the fault continues:

replace the ELECTRONIC CONTROL BOX [59KD] AMM 49-61-34-000-002 and AMM 49-61-34-400-002.

Subtask 49-00-00-810-271-B ** ON A/C NOT FOR ALL

G. If:
.the bleed pressure is low with both engines in operation,
.the bleed pressure is also low in ECS mode,
.the APU self test gives no maintenance message.

replace the BLEED CONTROL VALVE (8051KM) AMM 49-51-53-000-001 and AMM 49-51-53-400-001.

(1) If the fault continues:

replace the INLET TEMP/INLET PRESSURE SENSOR (8013KM) AMM 49-23-17-000-001 and AMM 49-23-17-400-001.
replace the LOAD COMPRESSOR DISCHARGE PRESSURE SENSOR (8039KM) AMM 49-51-19-000-002 and AMM 49-51-19-400-002.

(2) If the fault continues:

replace the ELECTRONIC CONTROL BOX [59KD] AMM 49-61-34-000-002 and AMM 49-61-34-400-002.

(3) If the fault continues:

do a check of the aircraft bleed system for leaks.

Subtask 49-00-00-810-272-B ** ON A/C NOT FOR ALL

H. If:
.the bleed pressure fluctuates during MES motoring test,

NOTE: The N2 speed of the engine must not more than 25%.

.the APU self test gives no maintenance message.

NOTE: Aircraft configuration:

the PACK 1 and 2 pushbutton switches are OFF,
the APU BLEED valve pushbutton switches is ON,
both engines BLEED pushbutton switches are off,
MES motoring test with one engine.

replace the BLEED CONTROL VALVE (8051KM) AMM 49-51-53-000-001 and AMM 49-51-53-400-001.

Subtask 49-00-00-810-366-D ** ON A/C NOT FOR ALL

I. If.
. a low APU bleed pressure cannot be confirmed,
. there is a pilot/maintenance report of a low APU pressure during Engine 1 start:

replace FLOW CTL UNIT - PACK 1 [23HB]
AMM 21-51-51-000-001 and AMM 21-51-51-400-001.

Subtask 49-00-00-720-053-A ** ON A/C NOT FOR ALL

J. Do the test given in Para. 3.

[Rev.8 from Aug 2018] 2026.04.04 04:34:26 UTC