S 864-063-N00
(5)
For the applicable engine, remove the DO-NOT-CLOSE tags and close
this circuit breakers:
(a)
P6 Main Power Distribution Panel
1) 6G01, FUEL SHUTOFF VALVE ENG 1
2) 6G15, SCU ALT PWR ENG 1
3) 6G23, ENG SCU 1
4) 6L10, FUEL CONT VALVE ENG 1
5) 6G02, FUEL SHUTOFF VALVE ENG 2
6) 6G16, SCU ALT PWR ENG 2
7) 6G24, ENG SCU 2
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
73-21-01
ALL ú ú N03 Page 412 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
8) 6L11, FUEL CONT VALVE ENG 2
9) 6G03, FUEL SHUTOFF VALVE ENG 3
10) 6G17, SCU ALT PWR ENG 3
11) 6G25, ENG SCU 3
12) 6L12, FUEL CONT VALVE ENG 3
13) 6G04, FUEL SHUTOFF VALVE ENG 4
14) 6G18, SCU ALT PWR ENG 4
15) 6G26, ENG SCU 4
16) 6L13, FUEL CONT VALVE ENG 4
S 864-065-N00
(6) Remove the DO-NOT-OPERATE tag from the FUEL CONTROL switch.
S 864-068-N00
(7) For the applicable engine, remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) P6 Main Power Distribution Panel
1) 6F01, IGN 1 ENG 1
2) 6G19, STBY IGN ENG 1
3) 6K19, IGN 2 ENG 1
4) 6F02, IGN 1 ENG 2
5) 6G20, STBY IGN ENG 2
6) 6K20, IGN 2 ENG 2
7) 6F03, IGN 1 ENG 3
8) 6G21, STBY IGN ENG 3
9) 6K21, IGN 2 ENG 3
10) 6F04, IGN 1 ENG 4
11) 6G22, STBY IGN ENG 4
12) 6K22, IGN 2 ENG 4
S 714-084-N00
(8) Do the test of the fuel metering unit that is shown in the Power Plant Test Reference Table (AMM 71-00-00/501).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
73-21-01
ALL ú ú N03 Page 413 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
EEC INLET TOTAL PRESSURE/TEMPERATURE (PT2/TT2) PROBE -
______________________________________________________ REMOVAL/INSTALLATION
____________________
1. General_______
A. This procedure gives the instructions to remove and install the EEC inlet total pressure/temperature (PT2/TT2) probe T867.
B. The PT2/TT2 probe is installed in the air stream of the inlet cowl at the 1 o'clock position.
C. You can get access to the PT2/TT2 probe through the access panel on the top of the inlet cowl.
TASK 73-21-03-004-001-N00
2. Remove the EEC Inlet Total Pressure/Temperature (PT2/TT2) Probe (Fig. 401)_______________________________________________________________
A. References
(1)
IPC 71-11-01 Fig. 1
(2)
WDM 30-34-11, 30-34-21, 30-34-31, 30-34-41, 73-21-76, 73-21-77
(3)
SSM 30-34-01, 30-34-02, 30-34-03, 30-34-04, 73-21-03
B.
Access
(1)
Location Zone
411 Engine 1 - Inlet Cowl 1 o'clock
421 Engine 2 - Inlet Cowl 1 o'clock
431 Engine 3 - Inlet Cowl 1 o'clock
441 Engine 4 - Inlet Cowl 1 o'clock
(2)
Access Panel
411AR PT2/TT2 Probe Access Door - Engine 1
421AR PT2/TT2 Probe Access Door - Engine 2
431AR PT2/TT2 Probe Access Door - Engine 3
441AR PT2/TT2 Probe Access Door - Engine 4
C.
Procedure
S 864-002-N00
(1)
For the applicable engine, open these circuit breakers and install the DO-NOT-CLOSE tags:
(a)
P6 Main Power Distribution Panel
1) 6G15 SCU ALT PWR ENG 1
2) 6G23 ENG SCU 1
3) 6H19 PROBE HEAT ENG 1
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
73-21-03
ALL ú ú N05 Page 401 ú Jun 10/92
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 发动机燃油和控制 2(11)
