(a) Observe that TRANSFER BUS OFF, BUS OFF, and GEN OFF BUS lights on P5 illuminate.
(2)
Shut down engine (Ref 71-09-100, Operating Procedure).
(3)
Place BAT switch on P5 to OFF.
501
24-22-0 Page 204 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/81
5C8 Manual Control Component Location
Feb 20/85 Figure 1 (Sheet 1) 24-22-0
Page 205
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
H21390
Manual Control Component Location 501
24-22-0 Figure 1 (Sheet 2) Nov 15/80
Page 206
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
DC GENERATION SYSTEM - DESCRIPTION AND OPERATION
1. General
A. A portion of the 3-phase 400-cycle power on the aircraft is converted to 28-volt direct current by means of three unregulated silicone transformer-rectifier (T-R) units. This 28-volt dc power is required for the electrical system control circuits and for various dc components. A battery is used as a standby power supply for certain essential circuits and for short period dc loads when no basic power source is available. The standby power system obtains 115-volt single-phase 400-cycle power by converting battery power through a static inverter located in the lower forward compartment. Full wave rectifiers are located at various places in the aircraft to convert single-phase 115-volt ac power to 115 volts dc to supply receptacles used for electrical shavers.
B. The three T-R units are located in the electronic compartment on shelf E3-1. (See figure 1.) T-R units No. 1 and No. 2 receive 3-phase, 115 volts ac from the No. 1 and No. 2 transfer busses respectively. (See figure 2.) T-R unit No. 3 is fed from the No. 2 generator bus, and provides dc through a dc tie bus to the 28-volt dc busses No. 1 and No. 2. The three T-R units have an output rating of 50 amperes at 28 volts dc.
2. Storage Battery
A. A nickel-cadmium storage battery is located in the lower forward compartment to the right of the electric compartment access door. (See figure 1.) The battery receives power from a charger located on shelf E3-1 of the electrical rack adjacent to T-R unit No. 3. During normal operation the charger input is from the ground service bus through a circuit breaker and the APU start interlock relay R39. (See figure 2.) Should generator transfer relay-1 (ALT) R3 be energized, 3-phase power is transferred from generator bus-1 to generator bus-2 and the battery charger transfer relay R89 will also transfer 3-phase power from ground service to the No. 2 main bus. This provides an alternate power source for the battery charger should No. 1 generator bus fail. Since the ground service relay R6, in its relaxed position, connects the ground service bus to the No. 1 generator bus, the battery may be charged from all four 3-phase 400-cycle sources. Refer to 24-41-0.
500
Aug 15/72 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 24-31-0 Page 1
H21445
DC Power System Component Location 580
24-31-0 Figure 1 May 15/79
Page 2
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
EFFECTIVITY
H55108
5C8 DC Power Generation Circuit
Feb 20/85 Figure 2 (Sheet 1) 24-31-0
Page 3
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
EFFECTIVITY
CA ALL EXCEPT B-2501 THRU B2503
H77440
DC Power Generation Circuit 5C8
24-31-0 Figure 2 (Sheet 2) Jun 20/86
Page 4
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
EFFECTIVITY
CA B2504, B2505 BEFORE INCORPORATING SB 24-1040
5C8 DC Power Generator Circuit
Jun 20/86 Figure 2 (Sheet 3) 24-31-0
Page 4A/4B
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
EFFECTIVITY
CA ALL EXCEPT B2501 THRU B2505; B2504 THRU B2505 AFTER INCORP SB 24-1040
5C8 DC Power Generator Circuit
Jun 20/86 Figure 2 (Sheet 4) 24-31-0
Page 5
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