(a)
DS1590, BLEED AIR OVERPRESSURE SWITCH, engine 1
(b)
DS1591, BLEED AIR OVERPRESSURE SWITCH, engine 2
(c)
DS1592, BLEED AIR OVERPRESSURE SWITCH, engine 3
(d)
DS1593, BLEED AIR OVERPRESSURE SWITCH, engine 4
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
36-21-03
ALL ú ú 02 Page 502 ú Oct 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 425-051
(2)
Put a cap on the electrical connectors.
S 715-073
(3)
After a time delay of 60 to 65 seconds,
(a)
Make sure bit 12 is set to 0 on the CDU.
(b)
After an additional 0 to 5 seconds, make sure the applicable (engine 1, 2, 3, or 4) bleed SYS FAULT light comes on.
S 965-107
CAUTION: MAKE SURE THE ELECTRICAL CONNECTORS ARE NOT DIRTY BEFORE THEY
_______ ARE CONNECTED. SOLID OR LIQUID CONTAMINATIONS IN THE ELECTRICAL CONNECTORS CAN CAUSE DAMAGE TO THE EQUIPMENT.
(4) Remove the existing overpressure switch and replace with a new or shop tested serviceable switch (AMM 36-21-03/401).
NOTE: The overpressure switch must be either new or shop tested
____
and in serviceable condition.
S 435-132
(5)
Reconnect the electrical connector to the applicable overpressure switch that follows:
(a)
DS1590, BLEED AIR OVERPRESSURE SWITCH, engine 1
(b)
DS1591, BLEED AIR OVERPRESSURE SWITCH, engine 2
(c)
DS1592, BLEED AIR OVERPRESSURE SWITCH, engine 3
(d)
DS1593, BLEED AIR OVERPRESSURE SWITCH, engine 4
S 715-102
(6)
Wait 70 seconds.
(7)
Make sure bit 12 is set to 1 on the CDU.
S 715-074
NOTE: When bit 12 is set to 1, there is no overpressure condition.
____
S 205-133
(8)
Make sure that the SYS FAULT lights for all four engines on the bleed overhead panel does not come on.
E.
Put the Airplane to Its Usual Condition
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
36-21-03
ALL ú ú 02 Page 503 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 415-053 WARNING: YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO REMOVE THE
_______
LE FLAP SAFETY LOCKS. THE LE FLAPS CAN MOVE QUICKLY IF YOU DO NOT DO THE STEPS CORRECTLY. THIS CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(1) Do this task: "Safety Lock Removal and Leading Edge Flap Activation: (AMM 27-81-00/201).
(2) S 865-052Do this task: "Leading Edge Flap Retraction: (AMM 27-81-00/201).
S 865-016
(3)
Remove the electrical power if it is not necessary (AMM 24-22-00/201).
S 865-097
(4)
Put the ENGINE BLEED switches to the desired positions.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
36-21-03
ALL ú ú 02 Page 504 ú Oct 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
1.
2.
3.
4.
A
747-400 MAINTENANCE MANUAL
ENGINE BLEED AIR TEMPERATURE INDICATING SYSTEM - DESCRIPTION AND OPERATION
__________________________________________________________________________
General
_______
A. The air temperature in each system's engine bleed ducts is monitored by a temperature sensor. An overtemperature switch is installed in each system to show overheat conditions.
B. The SYS FAULT light on the engine bleed control module will come on when an overtemperature condition occurs. A BLEED (1/2/3/4) OVHT advisory message will also come into view on EICAS. To monitor the bleed air temperature in the pneumatic ducts, it is necessary to look at the 21 ECS EICAS MAINT PAGES (AMM 45-10-00/201).
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 氣動系統 PNEUMATIC SYSTEM(167)
