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CAUTION: DO NOT APPLY A PRESSURE OF MORE THAN 15 PSIG (103.4 KPA) TO
_______ THE PT2 SYSTEM. MAKE SURE THE AIR REGULATOR IS SET LOW BEFORE YOU SUPPLY AIR TO THE PT2 SYSTEM. A HIGH PRESSURE CAN CAUSE DAMAGE TO THE EEC.
(3) Pressurize the PT2 system to a maximum pressure of 10 psig
(68.9 kPag).
NOTE: Apply the pressure at a rate of 2.0 psig (13.8 kPag) in
____
1 minute.
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(4)
Close the shutoff valve to isolate the PT2 system.
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(5)
If the pressure decreases, do the steps that follow:
(a)
Open the right fan cowl panel (AMM 71-11-04/201).
(b)
Keep a 10 psig (68.8 kPag) pressure to the PT2 system.
(c)
Apply the leak check fluid to the PT2 line to find the leak.
(d)
If a leak is not found, do the steps that follow:
(e)
Remove the screws which attach the access door for the PT2/TT2 probe to the inlet cowl.
(f)
Remove the access door.
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////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
SEE
PT2 System Leak Check Component Location
Figure 514 (Sheet 1)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
SEE C
ELECTRONIC ENGINE CONTROL (EEC)
INLET COWL
FWD
EEC PT2 EEC PT2
HOSE (AFT) HOSE (FORWARD)
C
PT2 System Leak Check Component Location
Figure 514 (Sheet 2)
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////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
SEE D
SCREW (8 LOCATIONS)
PT2/TT2 PROBE ACCESS DOOR
INLET COWL
EEC PT2 LINE
EEC INLET
TOTAL PRESSURE/
TEMPERATURE (PT2/TT2)
PROBE
D
PT2 System Leak Check Component Location
Figure 514 (Sheet 3)
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TEST NO. 14 - PT2 SYSTEM LEAK CHECK
___________________________________
(g)
Apply the leak check fluid to the PT2 line connection at the PT2/TT2 probe to find the leak.
(h)
Repair or replace the PT2 tube as it is necessary.
(i)
Do the test again to make sure the repair has corrected all the leaks in the PT2 system.
(j)
Close the right fan cowl panel (AMM 71-11-04/201).
(k)
Install the access door for the PT2/TT2 probe with the screws if it was removed.
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(6)
Remove the air source from the engine.
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(7)
Remove the protection mats from the inlet cowl.
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本文链接地址：747-400 AMM 飞机维护手册 动力装置 POWER PLANT 1(95)
