(2)
AMM 32-00-30/201, Landing Gear Door Locks
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
28-21-02
ALL ú ú 14 Page 407 ú Oct 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
(3)
SWPM 20-20-00, Electrical Bond and Ground
(4)
SSM 28-21-03, 28-21-07
(5)
WDM 28-21-22, 28-21-25, 28-21-28, 28-21-31
D.
Access
(1)
Location Zones 135 Wing Landing Gear Well, Left 136 Wing Landing Gear Well, Right 571 Rear Spar to Landing Gear Support Beam, Left 572 Landing Gear Support Beam and Rear Spar to Trailing
Edge, Left 584 Spoiler No. 2, Left 591 Rear Spar to Trailing Edge, Left 671 Rear Spar to Landing Gear Support Beam, Right 672 Landing Gear Support Beam and Rear Spar to Trailing
Edge, Right 684 Spoiler No. 2, Right 691 Rear Spar to Trailing Edge, Right
(2)
Access Panels
571AB Trailing Edge Lower Access Panel
572GB Trailing Edge Lower Access Panel
581EB Flap Drive Access Panel
591AB Outbd Aileron Access Panel
671AB Trailing Edge Lower Access Panel
672GB Trailing Edge Lower Access Panel
681EB Flap Drive Access Panel
691AB Outbd Aileron Access Panel
E.
Procedure
S 164-034
(1)
Prepare these faying surfaces for an electrical surface bond (SWPM 20-20-00):
(a)
Faying surface of the valve unit mounting stud (Fig. 401, View B).
(b)
Faying surface of the refuel valve control unit at the mounting stud (Fig. 401, View B).
(2)
Install the new packings (1 and 2) on the control unit (3).
(3)
Apply a thin layer of petrolatum on the new packings (1 and 2).
S 434-012
S 644-022
S 424-013
CAUTION: MAKE SURE YOU ARE CAREFUL WHEN YOU ENGAGE THE CONTROL UNIT WITH
_______ THE VALVE UNIT PISTON. THE SEALS ON THE VALVE UNIT PISTON ARE EASILY DAMAGED IF YOU ARE NOT CAREFUL.
(4) Move the control unit (3) until it is on the valve unit piston.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
28-21-02
ALL ú ú 09 Page 408 ú Oct 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 824-026
(5)
Align the bolt holes in the control unit (3) with the bolt holes in the valve unit piston.
S 434-014
(6)
Install the bolts (5) and washers (6) (3 locations) to attach the control unit (3) to the valve unit mounting nuts.
S 434-015
(7)
Connect the electrical connector (4) to the control unit (3).
NOTE: Refer to the subsequent table for the equipment numbers.
____
~................................................................. | | Equipment Number | | Location ............................ | | Valve | Connector | ................................................................... | No. 1 Main Tank | V58 | DV58 | | No. 2 Main Tank - Inboard | V81 | DV81 | | No. 2 Main Tank - Outboard | V59 | DV59 | | No. 3 Main Tank - Inboard | V62 | DV62 | | No. 3 Main Tank - Outboard | V82 | DV82 | | No. 4 Main Tank | V63 | DV63 | | Center Wing Tank - Left | V60 | DV60 | | Center Wing Tank - Right | V61 | DV61 | | No. 2 Reserve Tank | V469 | DV469 | | No. 3 Reserve Tank | V470 | DV470 | 2......................................…...........…..............1
S 864-016
(8) Make sure the manual override control is closed and sealed.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
28-21-02
ALL ú ú 05 Page 409 ú Oct 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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 燃油 FUEL 2(37)
