(7) Remove main deck cargo handling transformer rectifier unit from bulkhead.
TASK 24-32-06-404-019
3. Install Main Deck Cargo Handling Transformer Rectifier Unit (Fig. 401)
___________________________________________________________
A. References
(1)
AIPC 24-41-06, Fig. 2
(2)
WDM 24-54-91
(3)
SSM 24-54-08
B.
Access
(1)
Location Zone 116 Area Between Nose Gear Well and Fuselage, RH
C.
Procedure
S 424-010
(1)
Position main deck cargo handling transformer rectifier unit onto bulkhead aligning bolt holes.
S 434-011
(2)
Install four bolts securing TRU to bulkhead. Tighten bolts.
S 034-012
(3)
Remove nuts securing terminal block cover to terminal block.
S 034-013
(4)
Remove five terminal block screws from terminal block.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH MAIN DECK ú
24-32-06
CARGO HANDLING ú ú 02 Page 403 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 434-020
CAUTION:_______ ENSURE EACH TERMINAL LEAD IS CONNECTED TO PROPER TERMINAL STUD
ON MAIN DECK CARGO HANDLING TRANSFORMER RECTIFIER UNIT.
INCORRECT INSTALLATION WILL RESULT IN CIRCUIT MALFUNCTION
AND/OR DAMAGE TO EQUIPMENT.
MAKE SURE ROUND WASHERS ARE INSTALLED BETWEEN TERMINAL NUT AND
LEAD. DO NOT INSTALL ANY WASHERS BENEATH LEADS AS THIS WILL
RESULT IN LOCALIZED RESISTANCE OF TERMINALS.
(5)
Connect five terminal leads to terminal block and secure with terminal block screws. Tighten screws.
S 434-016
(6)
Install terminal block cover to terminal block on TRU and secure with nuts. Tighten nuts.
S 864-017
(7)
Remove DO-NOT-CLOSE identifier and close circuit breaker as follows for the main deck cargo handling TRU:
(a)
P415, Power Distribution Center - Right 1) 415G16, MAIN DECK CARGO HDLG TRU
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24-32-06
CARGO HANDLING ú ú 02 Page 404 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
1.
2.
3.
4.
A
747-400 MAINTENANCE MANUAL
DC STANDBY POWER SYSTEM - DESCRIPTION AND OPERATION
___________________________________________________
General
_______
A. A dc standby power system is provided to supply nominal 24 volt dc power to selected flight critical loads for 30 minutes minimum in the event of complete loss of primary dc power. This system is supplied by two 40 ampere hour nickel-cadmium batteries (main and APU battery), associated battery chargers, various control relays, the main and APU battery hot buses, and main and APU battery buses.
B. The main and APU batteries also supply dc loads necessary for ground operation when ac power is not provided.
C. For a description of standby 115-volt ac power generation, refer to
24-29-00/001.DC Voltage Sense Relay (Fig. 1)
______________________
A. The dc voltage sense relay monitors the 28 volt dc on the main dc bus 3 and allows the battery transfer relay to transfer this voltage to the main and APU battery bus loads when the system is operating normally.
Single TRU Operation Relay (Fig. 2)
__________________________
A. The single TRU operation relay is used by the BCUs to control the battery transfer relay, which removes the 28 volt main bus 3 power from the main and APU battery bus loads when in single TRU operation.
Operation
_________
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本文鏈接地址：747-400 AMM 飛機維護手冊 ELECTRICAL POWER 電源 2(80)
