(2)
Installation of the Generator Drive and Standby Power Module
B. The Generator Drive and Standby Power Module, P5-5, is located on the P5 Overhead Panel in the flight compartment.
2. Remove Generator Drive and Standby Power Module
A. Remove electrical power (Ref 24-22-00/201).
B. Holding module panel in place to prevent falling, loosen the quarter turn fasteners.
CAUTION: Care must be taken to ensure no damage occurs to electrical cables at rear of module.
C. Remove module to gain access to electrical connectors.
D. Disconnect electrical connectors from module.
E. Attach protective covers to the electrical connectors.
3. Install Generator Drive and Standby Power Module
A. Remove electrical power (Ref 24-22-00/201).
B. Remove protective covers from the electrical connectors in the overhead panel bay.
C. Inspect electrical connectors for damage or defects.
(1) Clean or repair electrical connectors if necessary.
NOTE: Observe the CAUTION above when working with the P5-5 Generator Drive and Standby Power Module on the P5 overhead panel. The associated electrical connectors can be cross connected as follows; D2 and D4 with each other and D636 and D1086 can be cross connected with other connectors in the vicinity (WDM 24-10-01, 24-10-02).
D. Connect electrical connectors to the module.
CAUTION: Care must be taken to ensure no damage occurs to electrical cables at rear of module.
E. Place module into position in the overhead panel bay.
F. Tighten quarter turn fasteners on module.
4. Installation Test
A. Disconnect the Generator Constant Speed Drive to simulate failure (Ref 24-11-11/401).
B. Perform the Adjustment Test for the Standby Power System (Ref 24-54-0/501).
5. Restore aircraft to normal configuration
A. Remove electrical power if no longer required (Ref 24-22-0/201).
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May 01/01 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 24-54-11 Page 401
DC POWER DISTRIBUTION - DESCRIPTION AND OPERATION
1. General
A. That portion of the 115-volt ac power on the airplane which is converted to 28 volts dc is used mostly for control purposes and is distributed from the main load control center panels P6-1, P6-4, P18-1, and P18-2. Conversion or rectification is made through five transformer-rectifier units. T-R units No. 1, 2 and 3 are the unregulated silicone type located on shelf E3-1 in the electronic compartment (Fig. 1). Diodes M8 and M113 between the dc tie bus and dc buses No. 1 and 2 prevent current being fed from T-R units No. 1 and 2 to the output side of T-R unit No. 3 (Fig. 2).
B. The 28-volt dc external power bus is fed by a fourth T-R unit within the bus protection panel (Fig. 3), and connects to the dc pin E in the external power receptacle. The external power plug contains a jumper, which connects pin E to F, completing the circuit to the ground power switch (S1). The bus protection panel T-R provides about 5 amperes dc at 28 volts for ground service use thereby eliminating the need for a separate T-R unit for this purpose, and permits operation of contactors and relays without having a battery on the airplane. The fifth T-R unit, designed specifically for charging the airplane storage battery, is located on E3-1 shelf in the lower forward section (Fig. 3). The battery charger is either a pulse-type or limited pulse-type unit capable of supplying 25 amperes continuously. Like the other four T-R units, the charger uses 3-phase 400-Hz input power.
2. DC Power Buses
A. The dc system supplies power to the following load buses: dc buses No. 1 and 2, the battery bus and hot battery bus, the dc standby bus (AT CN-RMI thru CN-RML; CA B2501 thru B2503; IDO 601; OI G-BGTW thru G-BJBJ; ZD G-AVRL thru G-BJCV), the dc electronics buses No. 1 and 2, and the dc external power bus. DC power buses No. 1 and 2 dc buses are isolated from each other preventing a fault on one from affecting the operation of the other. T-R No. 1 and 2 provides dc power for No. 1 and 2 main buses, respectively (Fig. 2). T-R No. 3 is connected in parallel with T-R 1 and 2. A blocking diode in each connecting branch permits only unilateral current flow. In the event either/or both T-R No. 1 and 2 fail, T-R No. 3 provides dc power to the main dc buses.
507
Jan 20/83 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 24-55-0 Page 1
H21743
DC Power Distribution - Power Source Bus Diagram 500
24-55-0 Figure 1 May 15/67
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