73-21-04
ALL ú ú N01 Page 607 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
EEC ALTERNATOR (N2 TRANSDUCER) - REMOVAL/INSTALLATION
_____________________________________________________
1. General
_______
A. This procedure removes and installs the EEC alternator (N2 transducer) stator and rotor.
B. The EEC alternator (N2 transducer) stator and rotor have different removal and installation procedures. You must remove the starter to get access to the EEC alternator. You must remove the stator to get access to the rotor.
C. The EEC alternator (N2 transducer) is installed on the aft face of the main gearbox at the 6 o'clock position.
D. You can get access to the EEC alternator (N2 transducer) through the thrust reverser halves.
TASK 73-21-05-004-001-N00
2. Remove the EEC Alternator (N2 Transducer) Stator
________________________________________________
A. Special Tools and Equipment
(1)
PWA 85749 Adapter - Electrical Harness Connector, Pratt & Whitney, Commercial Products Division, 400 Main Street, East Hartford, CT 06108 (optional)
B.
References
(1)
AMm 71-11-04/201, Fan Cowl Panels
(2)
AMM 71-11-06/201, Core Cowl Panels
(3)
AMM 78-31-00/201, Thrust Reverser System
(4)
AMM 80-11-01/401, Starter
(5)
IPC 71-31-51 Fig. 1
(6)
IPC 73-21-05 Fig. 5
(7)
IPC 74-21-01 Fig. 5
(8)
IPC 75-20-01 Fig. 1
(9)
WDM 73-21-15, 73-21-25, 73-21-35, 73-21-45, 77-12-21, 77-12-22, 77-12-23, 77-12-24
(10)
SSM 73-21-01, 77-12-02
C.
Access
(1)
Location Zone 412 Engine 1 - Main Gearbox Aft Face 6 o'clock 422 Engine 2 - Main Gearbox Aft Face 6 o'clock 432 Engine 3 - Main Gearbox Aft Face 6 o'clock 442 Engine 4 - Main Gearbox Aft Face 6 o'clock
(2)
Access Panel 415 and 416 Thrust Reverser Halves - Engine 1 425 and 426 Thrust Reverser Halves - Engine 2 435 and 436 Thrust Reverser Halves - Engine 3 445 and 446 Thrust Reverser Halves - Engine 4
D.
Procedure
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
73-21-05
ALL ú ú N01 Page 401 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
SEE A
SEE D SEE C
LOWER IGNITER PLUG HEAT SHIELD
HYDRAULIC PUMP (REF)
1. HEAT SHIELD PLUG CABLE 3. LOWER EXCITER-TO-IGNITER SEE B A FWD
CLAMP2.
CABLE END
3. EXCITER-TO-IGNITER PLUG CABLE
HEAT SHIELD4.
B Figure 401 (Sheet 1) EEC Igniter Plug and Heat Shield Installation
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
73-21-05
ALL ú ú N01 Page 402 ú Oct 10/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
6. BOLT5. HEAT 7. WASHERSHIELD 8. NUT
9.
SCREW
10.
WASHER
FWD MAIN GEARBOX
9.
SCREW
10.
WASHER
C1
22. BOLT (3 LOCATIONS)
31.
PACKING
32.
DEOILER MAIN GEARBOX OUTLET TUBE
FLANGE M SEE E 24. BOLT
25. NUT 25. NUT
30. BRACKET 26. CLAMP
26.
CLAMP
27.
BOLT
FLANGE N BRACKET
29. MAIN FILTER FWD28. CLAMP OIL TUBE
DEOILER OUTLET TUBE
D
22. BOLT (3 LOCATIONS)
30. BRACKET
23. BRACKET
2
17. STATOR
CABLES E2
1 HYDRAULIC PUMP NOT SHOWN FOR CLARITY.
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 發動機燃油和控制 2(22)
