NOTE: If the ground lead on the W6 cable at the EGT
____ Thermocouple Terminal Box is damaged or missing, you must repair the cable per Unison SB 420081-73-46 or replace it.
(c)
Tighten the screws to 16-22 pound-inches
(1.8-2.5 newton-meters).
(d)
Install lockwire to the screws.
S 417-012-N00
(10)
Close the core cowl panels (AMM 71-11-06/201).
S 867-021-N00
(11)
For the applicable engine, remove the DO-NOT-CLOSE tags and close these circuit breakers on the main power distribution panel, P6:
(a)
6G15 SCU ALT PWR ENG 1
(b)
6G23 ENG SCU 1
(c)
6G16 SCU ALT PWR ENG 2
(d)
6G24 ENG SCU 2
(e)
6G17 SCU ALT PWR ENG 3
(f)
6G25 ENG SCU 3
(g)
6G18 SCU ALT PWR ENG 4
(h)
6G26 ENG SCU 4
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
77-21-02
ALL ú ú N02 Page 706 ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
EXHAUST GAS TEMPERATURE (TT4.95) THERMOCOUPLE CABLE TERMINAL BOX -
__________________________________________________________________ REMOVAL/INSTALLATION
____________________
1. General________
A. This procoedure includes two tasks. One task is the removal of the exhaust gas temperature (EGT) thermocouple cable terminal box. The other task is the installation of the terminal box.
B. The terminal box is installed at the 5 o'clock position on the turbine exhaust case.
C. You must open the right core cowl panel to get access to the terminal box.
TASK 77-21-04-004-018-N00
2. Exhaust Gas Temperature (TT4.95) Thermocouple Cable Terminal Box Removal________________________________________________________________________ (Fig. 401)
A. References
(1)
AMM 71-11-06/201, Core Cowl Panels
(2)
IPC 77-21-04 Fig. 01
B.
Access
(1)
Location Zone 412 Engine 1 - Turbine Exhaust Case 5 o'clock 422 Engine 2 - Turbine Exhaust Case 5 o'clock 432 Engine 3 - Turbine Exhaust Case 5 o'clock 442 Engine 4 - Turbine Exhaust Case 5 o'clock
(2)
Access Panel
418 Right Core Cowl Panel - Engine 1
428 Right Core Cowl Panel - Engine 2
438 Right Core Cowl Panel - Engine 3
448 Right Core Cowl Panel - Engine 4
C.
Procedure
S 864-051-N00
(1) For the applicable engine, open these circuit breakers on the main power distribution panel, P6, and install the DO-NOT-CLOSE tags:
(a)
6G15 SCU ALT PWR ENG 1
(b)
6G23 ENG SCU 1
(c)
6G16 SCU ALT PWR ENG 2
(d)
6G24 ENG SCU 2
(e)
6G17 SCU ALT PWR ENG 3
(f)
6G25 ENG SCU 3
(g)
6G18 SCU ALT PWR ENG 4
(h)
6G26 ENG SCU 4
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
77-21-04
ALL ú ú N02 Page 401 ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
FLANGE P
FLANGE S
FLANGE T SEE A
TURBINE EXHAUST CASE
EGT (TT4.95)
THERMOCOUPLE CABLE
2. EEC HARNESS GROUND LEAD (2 LOCATIONS) 3. NUT - ALUMEL STUD
EGT (TT4.95) THERMOCOUPLE 4. NUT - CHROMEL STUD
CABLE TERMINAL (2 LOCATIONS)
BOX
SEE B
5. SCREW
(2 LOCATIONS) FWD
A
GROUND
1. NUT TERMINAL
(4 LOCATIONS)
6. COVER
7. SCREW
FLANGE P (2 LOCATIONS)
BRACKET
8. SCREW (2 LOCATIONS)
9. OUTER CLAMP HALF
13. EGT (TT4.95) THERMOCOUPLE
10. RIGHT EGT (TT4.95) CABLE TERMINAL
THERMOCOUPLE BOX
CABLE HALF
11. LEFT EGT (TT4.95) THERMOCOUPLE CABLE HALF12. INNER CLAMP HALF
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機(jī)維護(hù)手冊(cè) 發(fā)動(dòng)機(jī)指示 ENGINE INDICATING(47)
