(b)  
METHOD 2;
 Pressurize the pneumatic system upstream of the PRSOV
 (AMM 36-00-00/201).

 S 794-067
 (4)  
Examine the switch installation for leakage.

 S 864-042

 (5)  
Release the pressure in the pneumatic system (AMM 36-00-00/201).

 S 364-068

 (6)  
If there is leakage, make the necessary repair.

 S 864-043

 (7)  
Cycle these circuit breakers on the P6 main power distribution panel

 (a)  
6H32, ENG 1 AIR SUPPLY CONT

 (b)  
6H33, ENG 2 AIR SUPPLY CONT

 (c)  
6H34, ENG 3 AIR SUPPLY CONT

 (d)  
6H35, ENG 4 AIR SUPPLY CONT

 S 744-044
 (8)  
Wait 4 minutes to allow the ASCTU to perform the BITE check.

 S 734-045

 (9)  
Get access to the CMCS: 21 ECS, SUPPLY, EXISTING FAULTS (AMM 45-10-00/201).

 S 734-046

 (10)
 Make sure that none of these applicable faults are present:

 (a)  
CMCS message 36041 - BLEED 1 OVERTEMP SWITCH FAIL

 (b)  
CMCS message 36042 - BLEED 2 OVERTEMP SWITCH FAIL

 (c)  
CMCS message 36043 - BLEED 3 OVERTEMP SWITCH FAIL

 (d)  
CMCS message 36044 - BLEED 4 OVERTEMP SWITCH FAIL

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 G. Put the Airplane to Its Usual Condition
 S 414-022
 (1)  
For the applicable engine, install the access door that follows for the mid-lower forward strut (AMM 54-62-00/201):

 (a)  
452DR

 (b)  
462DR

 (c)  
472DR

 (d)  
482DR

 S 444-025
 (2)  
Do the activation procedure for the thrust reverser (AMM
 78-31-00/201).

 S 864-024

 (3)  
Remove the electrical power if it is not necessary
 (AMM 24-22-00/201).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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 ALL  ú ú 01 Page 408 ú Oct 10/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 BLEED AIR OVERTEMPERATURE SWITCH - ADJUSTMENT/TEST
__________________________________________________
 1.  General
_______
 A.  This procedure contains one task. It does a functional test of the bleed air overtemperature control and indication system. The overtemperature switch itself, however, is not tested in-situ. Therefore, in order to complete this functional test in a timely and practical manner, it is necessary to replace the switch that is removed, with a new switch or a shop tested switch that is known to be in serviceable condition.
 NOTE: The switch that is removed by this test procedure can also be
____ sent to the shop to be tested per the component maintenance manual for serviceability and reinstalled on the airplane again.
 B.  The bleed air overtemperature switch is installed on the right side of the lower forward strut. To get access to the switch it is necessary to remove the access door for the mid-lower forward strut.
 TASK 36-22-01-705-001
 2.  Functional Test for the Bleed Air Overtemperature Switch
________________________________________________________
 A.  References
 (1)
AMM 24-22-00/201, Manual Control

 (2)
AMM 31-61-00/201, Integrated Display System

 (3)
AMM 36-22-01/401, Bleed Air Overtemperature Switch

 (4)
AMM 45-10-00/201, Central Maintenance Computer System

 (5)
AMM 54-62-00/201, Nacelle Strut Access Panels

 (6)
AMM 78-31-00/201, Thrust Reverser

 B.  
Access

 (1)  
Location Zone
 452 Nacelle Strut 1 - Torque Box
　
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本文鏈接地址：747-400 AMM 飛機(jī)維護(hù)手冊(cè) 氣動(dòng)系統(tǒng) PNEUMATIC SYSTEM(171)