53 lines
2.3 KiB
Markdown
53 lines
2.3 KiB
Markdown
---
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created: 2023-12-19T18:04
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updated: 2023-12-19T18:51
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---
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\*\* ON A/C FSN 601-629, 631-650, 751-850, 853-855, 858-900
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TASK 36-11-00-810-A16-A
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Engine 1 Bleed Manifold Pressure Sensor Drift Measurement
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##### 3\. Fault Confirmation
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###### A. Test(s)
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(1) Do the drift test of the pressure sensor to clear the latched fault Ref. AMM 36-11-00-740-805.
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(2) Make sure that both the engines were not in operation for a minimum of 60 seconds.
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(3) Make sure the APU pushbutton was selected OFF for a minimum of 60 seconds.
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(4) On the SD BLEED page, make sure that ENG 1 precooler inlet pressure is less than 5 psig.
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(5) On the SD ENG page, make sure that ENG 1 nacelle temperature is above -20 deg.C.
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(6) Wait for a minimum of 40 seconds.
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(7) Do the ground scanning test Ref. AMM 36-11-00-740-809:
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(a) If the test result is ok, continue on para 4.B.
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(b) If the test result gives maintenance message DRIFT TRANSF-PRESS XDCR (7HA1)/ SENSE LINE, continue on para 4.A.
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##### 4\. Fault Isolation
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###### A. If the fault symptom is identified by the maintenance message DRIFT TRANSF-PRESS XDCR(7HA1)/ SENSE LINE:
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(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.
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(2) Do the test given in the paragraph Fault Confirmation.
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###### B. If the fault continues:
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(1) Do a leak check of the sense line Ref. AMM 36-11-00-790-807.
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| Action | Result |
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|--------|--------|
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| 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). |
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(2) If the check is not satisfactory, do the step that follows:
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- 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.
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###### C. After the subsequent flight, make sure that the fault does not continue.
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!\[\[screenshot.png\]\]
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!\[\[screenshot 1.png\]\]
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!\[\[screenshot 2.png\]\]
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!\[\[screenshot 3.png\]\] |