2.3 KiB
created, updated
| created | updated |
|---|---|
| 2023-12-19T18:04 | 2023-12-19T18:51 |
** 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): - Open the shutoff valve. - 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: - The digital pressure gage shows the pressure. On the SD: - 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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