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created: 2023-12-19T18:04
updated: 2023-12-19T18:51
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\*\* ON A/C FSN 601-629, 631-650, 751-850, 853-855, 858-900

TASK 36-11-00-810-A16-A

Engine 1 Bleed Manifold Pressure Sensor Drift Measurement

##### 3\. Fault Confirmation

###### A. Test(s)

(1) Do the drift test of the pressure sensor to clear the latched fault Ref. AMM 36-11-00-740-805. 
(2) Make sure that both the engines were not in operation for a minimum of 60 seconds. 
(3) Make sure the APU pushbutton was selected OFF for a minimum of 60 seconds. 
(4) On the SD BLEED page, make sure that ENG 1 precooler inlet pressure is less than 5 psig. 
(5) On the SD ENG page, make sure that ENG 1 nacelle temperature is above -20 deg.C. 
(6) Wait for a minimum of 40 seconds. 
(7) Do the ground scanning test Ref. AMM 36-11-00-740-809: 
(a) If the test result is ok, continue on para 4.B. 
(b) If the test result gives maintenance message DRIFT TRANSF-PRESS XDCR (7HA1)/ SENSE LINE, continue on para 4.A.

##### 4\. Fault Isolation

###### A. If the fault symptom is identified by the maintenance message DRIFT TRANSF-PRESS XDCR(7HA1)/ SENSE LINE:

(1) Replace the XDCR-BLEED TRANSFER PRESS, ENG 1 (7HA1) Ref. AMM 36-11-15-000-802 and Ref. AMM 36-11-15-400-802. 
(2) Do the test given in the paragraph Fault Confirmation.

###### B. If the fault continues:

(1) Do a leak check of the sense line Ref. AMM 36-11-00-790-807.

| Action | Result |
|--------|--------|
| On the TEST SET - ENGINE BLEED (98L36103002000): <br /><br />\- Open the shutoff valve.<br />\- Slowly pressurize the system from 10 psi (0.69 bar) to 90 psi (6.21 bar) with the regulator valve of the TEST SET | On the TEST SET:<br />\- The digital pressure gage shows the pressure. <br /><br />On the SD: <br />\- The status page shows the supplied pressure which must agree with the value of the digital pressure gage plus or minus 2 psi (0.14 bar). |

(2) If the check is not satisfactory, do the step that follows:

- Replace the sense line of the bleed transferred pressure-transducer  Ref. AMM 36-11-49-000-823 Ref. AMM 36-11-49-400-823 and Ref. AMM 36-11-49-000-832 Ref. AMM 36-11-49-400-832.

###### C. After the subsequent flight, make sure that the fault does not continue.

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