(3)
From the terminal box, the signals are sent via the EEC wiring harness to the EEC, and then to the EIU's for display on EICAS.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
77-21-00
ALL ú ú N01 Page 5 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
EGT (TT4.95) THERMOCOUPLE PROBE (4 PLACES)
Exhaust Gas Temperature Indicating System Simplified Schematic
Figure 3
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
77-21-00
ALL ú ú N01 Page 6 ú Apr 10/89
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
EXHAUST GAS TEMPERATURE INDICATING SYSTEM - ADJUSTMENT/TEST
___________________________________________________________
1. General
_______
A. This procedure includes the task to do an operational test of the exhaust gas temperature (EGT) indicating system.
B. Do the test if you replace one of these components:
(1)
EGT probe
(2)
EGT cable
(3)
EGT terminal box
(4)
EGT housing.
C.
To do the test, you must operate the engines.
TASK 77-21-00-715-004-N00
2. Operational Test - Exhaust Gas Temperature Indicating System (Fig. 501)
____________________________________________________________
A. References
(1) AMM 24-22-00/201, Manual Control
CABIN ALTITUDE AUTOTHROT DISC OUTFLOW VLV L
(11 LINES)
CON IGNITION SEATBELTS RECALL STATUS PG 1
FL250 246-324KTS
DOWN GEAR
587 587 97 623
F L 5
A
P
SEE A S
12 12DUCT PRESS
7500CAB ALT +250RATE TOTAL FUEL345.0 LBSX
LDG ALT 200 5.6~PAUTO TEMP +10c 1000
MAIN EICAS DISPLAY
A
Exhaust Gas Temperature Indication
Figure 501
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
77-21-00
ALL ú ú N01 Page 501 ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
(2)
AMM 31-61-00/501, Integrated Display System
(3)
AMM 32-09-02/201, Air/Ground Relays
(4)
AMM 71-00-00/201, Power Plant
B. Access
(1) Location Zone
221 Control Cabin, LH
222 Control Cabin, RH
C. Preconditions
S 865-006-N00
(1) These conditions are necessary for this task:
(a)
Electrical power on (AMM 24-22-00/201).
(b)
Integrated Display System serviceable (AMM 31-61-00/501).
(c)
Airplane must be in the Ground Mode (AMM 32-09-02/201).
(d)
The engine must be operational (AMM 71-00-00/201).
D. Do a Test of the EGT Indicating System.
S 715-001-N00
(1) Operate the engines at the same power.
(a)
Start the engines (AMM 71-00-00/201).
(b)
Make sure these engine indications become stable and are approximately the same value: 1) N1 2) N2 3) EPR
S 215-002-N00
(2)
Make sure the EGT indication on the main EICAS display is approximately the same for each engine.
(3)
Stop the engines (AMM 71-00-00/201).
S 865-003-N00
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
77-21-00 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 发动机指示 ENGINE INDICATING(25)
