S 715-166-N00
(13) If you replaced the metering tube nipple, do this test again to make sure the indication for the main oil pressure is in the permitted limits.
NOTE: A change in indication of the main oil pressure from engine
____ to engine is permitted if the indications are in the permitted limits.
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71-00-00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
TEST NO. 14 - PT2 SYSTEM LEAK CHECK
___________________________________
TASK 71-00-00-705-167-N00
16. Test No. 14 - PT2 System Leak Check
___________________________________
A. General
(1)
This test does a check of the pressure and leakage of the PT2 system. The PT2 system is pressurized from the EEC inlet total pressure/temperature (PT2/TT2) probe, installed in the inlet cowl, to (and include) the EEC.
(2)
No leaks in the PT2 system are permitted. You must repair all leaks.
B.
Standard Tools and Equipment
(1)
Air Source - Compressed Dry Filtered and
Regulated, 0-15 psi (0-100 kPa)
(2)
Gauge - Pressure, 0-15 psi (0-100 kPa) range
|1% accuracy
(3)
Mats - Protection, Rubber Manufacturers
Association Grade SC43, Neoprene Sponge,
1 inch (25 mm) thick, approximately 3 X
4 feet (90 X 120 cm) with the warning
streamers attached (three are necessary)
(4)
A710491 - Adapter, PT2 Probe
(5)
Valve - Shutoff
(6)
Tube - Flexible, Tygon, 0.250 inch (6.350 mm)
ID
C.
Consumable Materials
(1)
G00835 Leak Check - Bubble Type (Soap and water
solution is optional)
D.
References
(1)
AMM 71-11-04/201, Fan Cowl Panels
E.
Access
(1)
Location Zones
411 Engine 1 - Inlet Cowl 1 o'clock
412 Engine 1 - Fan Case 2 o'clock
421 Engine 2 - Inlet Cowl 1 o'clock
422 Engine 2 - Fan Case 2 o'clock
431 Engine 3 - Inlet Cowl 1 o'clock
432 Engine 3 - Fan Case 2 o'clock
441 Engine 4 - Inlet Cowl 1 o'clock
442 Engine 4 - Fan Case 2 o'clock
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
TEST NO. 14 - PT2 SYSTEM LEAK CHECK
___________________________________
(2)
Access Panels
411AR PT2/TT2 Probe Access Door - Engine 1
414 Right Fan Cowl Panel - Engine 1
421AR PT2/TT2 Probe Access Door - Engine 2
424 Right Fan Cowl Panel - Engine 2
431AR PT2/TT2 Probe Access Door - Engine 3
434 Right Fan Cowl Panel - Engine 3
441AR PT2/TT2 Probe Access Door - Engine 4
444 Right Fan Cowl Panel - Engine 4
F.
Procedure
S 945-169-N00
(1)
Put the protection mats in the inlet cowl.
S 485-167-N00
(2)
Assemble the compressed air source, pressure gauge, shutoff valve,
flexible tube, and PT2 Probe Adapter (Fig. 514).
NOTE: Make sure the round gasket on the PT2 Probe Adapter fits 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：747-400 AMM 飞机维护手册 动力装置 POWER PLANT 1(94)
