B.
References
(1)
AMM 06-09-03/201, Body Section 44 Access Doors and Panels
(2)
AMM 24-22-00/201, Manual Control
(3)
AMM 36-00-00/201, Pneumatic System
C.
Access
(1)
Location Zone 191 Left Pressure Transmitter - Fairing, Wing-To-Body, Forward Lower Half, Left
192 Right Pressure Transmitter - Fairing, Wing-To-Body, Forward Lower Half, Right
(2)
Access Panel 191-NL Door - Access, Air-Conditioning - Left Pressure Transmitter
192-JR Door - Access, Air-Conditioning - Right Pressure Transmitter
D. Prepare to Do the System Test
S 865-001
(1)
Supply electrical power (AMM 24-22-00/201).
S 865-002
(2)
Put the two wing ISLN switches, on the P5 Overhead Panel, to the OPEN position.
(3)
Release the pressure in the pneumatic system (AMM 36-00-00/201).
S 865-003
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
36-21-00
ALL ú ú 01 Page 501 ú Feb 10/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 015-004
(4)
Open the applicable Air Conditioning Access Door (AMM 06-09-03/201):
(a)
Open the door 191-NL to get access to the pressure transmitter for the left duct. 1) The transmitter is installed above the forward left corner
of the door.
(b)
Open the door 192-JR to get access to the pressure transmitter for the right duct. 1) The transmitter is installed approximately two feet aft of
the aft right corner of the door.
E. Do the System Test
S 035-005
(1)
Disconnect the sense hose from the pressure transmitter.
(a)
Connect the sense hose to the pressure source.
S 865-006
(2) Pressurize the system to the values shown.
NOTE: When you increase to the subsequent pressure value, do
____ not increase more than the specified pressure. When you decrease to the subsequent pressure value, do not decrease less than the specified pressure.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
36-21-00
ALL ú ú 01 Page 502 ú Feb 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
~................................................................ | APPLIES PRESSURE (PSI) | INDICATION | | (PRESSURE SOURCE) | (EICAS MAINT PAGE) | .................................................................. | 25 | 25 | 3.0 | .................................................................. | 40 | 40 | 3.0 | .................................................................. | 50 | 50 | 3.0 | .................................................................. | 60 | 60 | 3.0 | .................................................................. | 70 | 70 | 3.0 | .................................................................. | 80 | 80 | 3.0 | .................................................................. | 90 | 90 | 3.0 | .................................................................. | 100 | 100 | 3.0 | 2........................….......................................1
S 785-007
(3)
Make sure that the pressure indication on the EICAS MAINT PAGE for the 21 ECS is at the specified pressure.
S 785-008
(4)
Hit the duct pressure transmitter lightly.
(a)
Monitor the pressure indication on the EICAS MAINT PAGE for the 21 ECS.
(b)
Make sure the values do not change more than 1 psi.
S 435-009
(5)
When the test is completed, disconnect the sense hose from the pressure source.
中國航空網 www.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(158)
