71-71-00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
~.............................................................................. | | | PERMITTED LEAKAGE | | | | ......................... | | | | DURING | AFTER | CORRECTIVE | | DRAIN/COMPONENT | LIQUID | OPERATION | SHUTDOWN | ACTION | ................................................................................
| Oil Tank Scupper| Oil | Servicing | Servicing | Make sure oil cap is |
| | | spillage | spillage | correctly installed. |
| | | only. | only. | Examine the oil tank |
| | | | | filler neck for cracks. |
| | | | | Prevent the spillage |
| | | | | when you fill the oil. |
2.................…........…...........…...........…...........................1
*[1] There is a fluid trap to find the component that has a leakage.
*[2] There is one fluid trap for the fuel/oil cooler bypass valve seal and the IDG fuel/oil cooler. This fluid trap helps you find the component that has the leakage.
*[3] If the leakage limit for the hydraulic pump shaft is more than the operation limit, refer to AMM 29-11-00 for the leakage limits.
*[4] A one time flyback limit of 120 drops/min (6.0 cc/min) to the nearest maintenance base capable of replacing the component is permissible.
*[5] Oil leakage of 6 drops/min (0.32 cc/min) or less is permitted and maintenance is not necessary. Oil leakage can be greater than 6 drops/min (0.32 cc/min) at one gearbox seal drain. The engine can continue in service to the next layover at a maintenance station if you obey all these conditions:
-Oil leakage with the engine operating cannot be more than 30 drops/min (1.5 cc/min).
-Current oil consumption (not average) is less than 0.3 qt/hr
(0.28 liter/hr).
-The oil tank is full.
-Only one engine is affected.
-A deferred item is entered in the log to replace the affected drive seal.
-For the deferred period, leakage is checked prior to each departure and consumption is checked after each flight and still meets the limits given above.
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71-71-00
ALL ú ú N01 Page 614 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
D. Put the Airplane Back to its Usual Condition.
S 416-004-N00
(1)
Close the louvered exhaust door (AMM 78-31-00/201).
S 446-003-N00
(2)
Do the activation procedure for the thrust reversers (AMM 78-31-00/201).
TASK 71-71-00-206-011-N00
3. Examine the Strut Drains for Heavy Deposits
___________________________________________
A. Equipment
(1)
Air source - regulated, compressed, 25-35 psi (170-240 kPa)
B.
References
(1)
AMM 71-11-04/201, Fan Cowl Panel
(2)
AMM 71-11-06/201, Core Cowl Panel
(3)
AMM 78-31-00/201, Thrust Reverser System
C.
Access
(1)
Location Zones
411 Engine 1
421 Engine 2
431 Engine 3
441 Engine 4
(2)
Access Panels 413 and 414 Fan Cowl Panels - Engine 1 415 and 416 Thrust Reverser Halves - Engine 1 417 and 418 Core Cowl Panels - Engine 1 423 and 424 Fan Cowl Panels - Engine 2 425 and 426 Thrust Reverser Halves - Engine 2 427 and 428 Core Cowl Panels - Engine 2 433 and 434 Fan Cowl Panels - Engine 3 435 and 436 Thrust Reverser Halves - Engine 3 437 and 438 Core Cowl Panels - Engine 3 443 and 444 Fan Cowl Panels - Engine 4 445 and 446 Thrust Reverser Halves - Engine 4 447 and 448 Core Cowl Panels - Engine 4
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