Failure of the L Static Probe (PHC1) A320

1.Possible Causes:

-PROBE-L STATIC, 1 (7DA1)

-PHC-1 (6DA1)

-ADIRU-1 (1FP1)

-wiring from the PHC 1 (6DA1) to the L static probe 1 (7DA1)

-wiring

2. Job Set-up Information

A. Referenced Information

REFERENCEDESIGNATION
Ref. AMM 30-31-00-710-001Operational Test of the Probe Ice Protection
Ref. ASM 30-31-01
Ref. AMM 30-31-34-000-002Removal of the Probe Heat Computer (PHC)
Ref. AMM 30-31-34-400-002Installation of the Probe Heat Computer (PHC)
Ref. AMM 34-11-16-000-001Removal of the Static Probe
Ref. AMM 34-11-16-400-002Installation of the Static Probe
Ref. AMM 34-12-34-000-001Removal of the ADIRU
Ref. AMM 34-12-34-400-001Installation of the ADIRU
Ref. ASM 34-13-02

3. Fault Confirmation

SUBTASK 30-31-00-710-058-A

A. Test

(1) Do the operational test of the probe ice protection Ref. AMM 30-31-00-710-001.

4. Fault Isolation

SUBTASK 30-31-00-810-054-A

A. If the test gives the maintenance message L STATIC PROBE 7DA1:

— do a check of the resistance between pin 2 and pin 1.

(1) If the resistance is more than 13 ohms (open circuit) or less than 10 ohms (short circuit):

(a) Replace the PROBE-L STATIC, 1 (7DA1), Ref. AMM 34-11-16-000-001 and Ref. AMM 34-11-16-400-002.

(2) If the resistance is between 10 ohms and 13 ohms:

(a) Replace the PHC-1 (6DA1), Ref. AMM 30-31-34-000-002 and Ref. AMM 30-31-34-400-002.

(b) If the fault continues:

— do a check and repair the wiring from the PHC 1 (6DA1) to the L static probe 1 (7DA1), pin A/D to pin 2 Ref. ASM 30-31-01.

(3) If the fault continues:

(a) Disconnect connector A from PHC 1 and remove ADIRU 1 Ref. AMM 34-12-34-000-001.

(b) Do a check of the probe signal wiring Ref. ASM 34-13-02 between PHC 1 pin A/Y and ADIRU 1 pin AA/4H.

1 If there is no continuity:

— Repair the wiring and

— Install ADIRU 1 Ref. AMM 34-12-34-400-001.

2 If there is continuity:

— Replace ADIRU-1 (1FP1) Ref. AMM 34-12-34-400-001.

SUBTASK 30-31-00-710-059-A

B. Do the operational test given in Para. 3.

Read me first

All instructions and limitations given in those documents that relate to the resetting of systems both on the ground and in the air must be respected. No reset should be attempted without a thorough appreciation of the technical ramifications. No more than one computer should be reset at any one time. No reset should be attempted in flight unless specifically permitted by the QRH. Maintenance messages remaining after a reset require engineering investigation.

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