W DOC AIRBUS | TSM A320F

Bleed Shutoff due to Reverse Flow Condition (131-9(A))

TASK 49-00-81-810-856-A
Bleed Shutoff due to Reverse Flow Condition (131-9(A))

1. Possible Causes
  • BLEED SHUTOFF DUE TO REVERSE FLOW CONDITION
  • blockade of the APU inlet
  • contamination/damage of the electrical connector P18
  • SURGE CONTROL VALVE (P18)
  • contamination/damage of the electrical connector P24
  • DIFFERENTIAL PRESSURE TRANSDUCER (P24)
  • contamination/damage of the electrical connector P23
  • TOTAL PRESSURE TRANSDUCER (P23)
  • flow sensor assembly and associated lines
  • aircraft wiring
  • ELECTRONIC CONTROL BOX [59KD]
  • SURGE CONTROL VALVE (8058KM)
  • DIFFERENTIAL PRESSURE TRANSDUCER (8043KM)
  • TOTAL PRESSURE TRANSDUCER (8044KM)
2. Job Set-up Information
 A. Referenced Information
REFERENCE
DESIGNATION
TSM TASK 49-00-81-810-871-A
Surge Control Valve (P18) Fault (131-9(A))
AMM 49-00-00-860-008
APU Start by External Power
AMM 49-51-16-000-002
Removal of the Transducer - Differential Pressure (131-9(A))
AMM 49-51-16-400-002
Installation of the Transducer - Differential Pressure (131-9(A))
AMM 49-51-17-000-002
Removal of the Transducer - Total Pressure (131-9(A))
AMM 49-51-17-400-002
Installation of the Transducer - Total Pressure (131-9(A))
AMM 49-51-52-000-003
Removal of the Surge Control Valve (131-9(A))
AMM 49-51-52-400-003
Installation of the Surge Control Valve (131-9(A))
ASM 496104
AMM 49-61-34-000-003
Removal of the Electronic Control Box (ECB) (131-9(A))
AMM 49-61-34-400-003
Installation of the Electronic Control Box (ECB) (131-9(A))
3. Fault Confirmation
Subtask 49-00-81-710-060-A ** ON A/C NOT FOR ALL
A. Read-out of ECB Trouble-Shooting Data
   (1) Put the APU MASTER SW to the ON position.
   (2) Get access to the APU LAST LEG/PREVIOUS LEG report.
   (3) Push the '>' adjacent to the related CFDS failure message:
  • the MCDU menu shows
    BLEED SHUTOFF DUE TO REVERSE FLOW CONDITION
   (4) Do a check in the APU LAST LEG/PREVIOUS LEG report for the associated Fault Message:
SURGE CONTROL VALVE P18
   (5) Fault Confirmation Procedure
     (a) Start the APU and apply Bleed Air for 20 seconds, minimum AMM 49-00-00-860-008.
     (b) Get access to the APU GND SCANNING menu.
4. Fault Isolation
Subtask 49-00-81-810-057-A ** ON A/C NOT FOR ALL
A. If the APU GND SCANNING menu gives the maintenance message:

SCV P18 / PRESS XDCR P24 / PRESS XDCR P23

associated with Fault Code Number (FCN) 89 or 91

  • do a check for blockade of the APU inlet .
   (1) If the APU inlet is blocked:
  • do a repair/cleaning.
   (2) If the APU inlet is clear:
  • do a check for contamination/damage of the electrical connector P18 of the SURGE CONTROL VALVE (P18).
     (a) If the electrical connector P18 is contaminated or damaged.
  • do a repair/cleaning.
     (b) If the electrical connector P18 is OK.
     (c) If the fault continues:
  • do a check for contamination/damage of the electrical connector P24 of the DIFFERENTIAL PRESSURE TRANSDUCER (P24).
     (d) If the electrical connector P24 is contaminated or damaged.
  • do a repair/cleaning.
     (e) If the electrical connector P24 is OK.
     (f) If the fault continues:
  • do a check for contamination/damage of the electrical connector P23 of the TOTAL PRESSURE TRANSDUCER (P23).
     (g) If the electrical connector P23 is contaminated or damaged.
  • do a repair/cleaning.
     (h) If the electrical connector P23 is OK.
       1 If the fault continues:
  • do a check of the flow sensor assembly and associated lines .
       2 If the fault continues:
  • do check/repair of the aircraft wiring between
    ECB (59KD) 59KD-AB/A2,A3 and the TOTAL PRESSURE TRANSDUCER (P23) P23/3,4
    ECB (59KD) 59KD-AB/B2,B3 and the DIFFERENTIAL PRESSURE TRANSDUCER (P23) P24/3,4
    ECB (59KD) 59KD-AB/G6 and the SURGE CONTROL VALVE (P18) P18/8
    ASM 496104.
         a If the fault continues:
Subtask 49-00-81-810-057-B ** ON A/C NOT FOR ALL
A. If the APU GND SCANNING menu gives the maintenance message:

SCV (8058KM) / PRESS XDCRS (8043KM)/(8044KM)

associated with Fault Code Number (FCN) 89 or 91

  • do a check for blockade of the APU inlet .
   (1) If the APU inlet is blocked:
  • do a repair/cleaning.
   (2) If the APU inlet is clear:
  • do a check for contamination/damage of the electrical connector P18 of the SURGE CONTROL VALVE (8058KM).
     (a) If the electrical connector P18 is contaminated or damaged.
  • do a repair/cleaning.
     (b) If the electrical connector P18 is OK.
     (c) If the fault continues:
  • do a check for contamination/damage of the electrical connector P24 of the DIFFERENTIAL PRESSURE TRANSDUCER (8043KM9.
     (d) If the electrical connector P24 is contaminated or damaged.
  • do a repair/cleaning.
     (e) If the electrical connector P24 is OK.
     (f) If the fault continues:
  • do a check for contamination/damage of the electrical connector P23 of the TOTAL PRESSURE TRANSDUCER (8044KM).
     (g) If the electrical connector P23 is contaminated or damaged.
  • do a repair/cleaning.
     (h) If the electrical connector P23 is OK.
       1 If the fault continues:
  • do a check of the flow sensor assembly and associated lines .
       2 If the fault continues:
  • do check/repair of the aircraft wiring between
    ECB (59KD) 59KD-AB/A2,A3 and the TOTAL PRESSURE TRANSDUCER (8044KM) P23/3,4
    ECB (59KD) 59KD-AB/B2,B3 and the DIFFERENTIAL PRESSURE TRANSDUCER (8043KM) P24/3,4
    ECB (59KD) 59KD-AB/G6 and the SURGE CONTROL VALVE (8058KM) P18/8
    ASM 496104.
         a If the fault continues:
Subtask 49-00-81-710-061-A ** ON A/C NOT FOR ALL
B. Do the test as in Para. 3.A.(4).
[Rev.8 from Aug 2018] 2026.04.04 04:34:36 UTC
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