(2)  
Access Panel
 113AL Forward Equipment Area Access

 C.  Prepare for the Removal
 S 864-002
 (1)  Open these circuit breakers on the main power distribution panel, P6, and attach a DO-NOT-CLOSE tag:
 (a)  
6D10, INV PWR TRU

 (b)  
6L11, INV PWR BAT

 S 034-003
 (2)  
Do these steps to disconnect the inverter:

 (a)
Open the access door to the forward equipment area.

 (b)  
Remove the electrical connector from the inverter.

 (c)  
Remove the terminal cover from the inverter.

 (d)  
Identify the wires on the terminals for the installation.

 (e)  
Remove the wires from the terminals.

 (3)  
Remove the inverter (AMM 20-10-01/401).

 S 024-004
 TASK 24-33-03-404-005
 3.  Install the Static Inverter (Fig. 401)___________________________
 A.  References
 (1)  AMM 20-10-01/401, E/E Rack Mounted Components
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 24-33-03
 ALL  ú ú 01 Page 401 ú May 28/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757 MAINTENANCE MANUAL
FORWARD EQUIPMENT CENTER, ACCESS 113AL
STATIC INVERTER, M217
SEE A
FORWARD EQUIPMENT CENTER LOCATION
MAIN BATTERY CHARGER (REF)
FORWARD EQUIPMENT CENTER
A
Static Inverter Installation Figure 401
STATIC INVERTER
ELECTRICAL CONNECTOR
TERMINAL COVER
INPUT TERMINALS
FWD
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 24-33-03
 ALL  ú ú 01 Page 402 ú May 28/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

 (2)  
AMM 24-22-00/201, Electrical Power - Control

 (3)  
AMM 31-41-00/201, EICAS - Maintenance Practices

 B. Access
 (1)  
Location Zones
 113 Area Forward of NLG Wheel Well (Left)
 211/212 Flight Compartment

 (2)  
Access Panel
 113AL Forward Equipment Area Access

 C. Install the Static Inverter
 S 424-006
 (1)  
Install the inverter (AMM 20-10-01/401).

 S 434-007

 (2)  
Do these steps to connect the inverter:

 (a)  
Connect the wires to the terminals.

 (b)  
Tighten the self-locking nut on the + (positive) terminal of the static inverter to 140 +/- 5 inch-pounds.

 (c)  
Tighten the self-locking nut on the - (negative) terminal of the static inverter to 70 +/- 5 inch-pounds.

 (d)  
Install the terminal cover on the terminals.

 (e)  
Connect the electrical connector to the inverter.

 S 864-009
 (3)  Remove the DO-NOT-CLOSE tags and close these circuit breakers on the main power distribution panel, P6:
 (a)  
6D10, INV PWR TRU

 (b)  
6L11, INV PWR BAT

 D. Do a Test of the Inverter Installation
 S 864-008
 (1)  
Supply electrical power (AMM 24-22-00/201).

 S 714-012

 (2)  
Do a test of the static inverter, as follows:

 (a)  Push the ELEC HYD switch on the EICAS MAINT panel on the right side panel, P61.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 24-33-03
 ALL  ú ú 01 Page 403 ú Jan 28/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：757 AMM 飛機維護手冊 電源 ELECTRICAL POWER 2(67)