C.
Procedure

 S 015-002
 (1)  Do the following steps to get access to the VSCF:
 (a)  
Open the fan cowl panels (AMM 71-11-04).

 (b)  
Open the thrust reversers (AMM 78-31-00).

 (c)  
Open the core cowl panels (AMM 71-11-06).

 S 025-003
 (2)
Disconnect the airplane wire bundle D6 connector on the VSCF.

 S 425-004

 (3)  
Connect the BIT Interrogation module interface cable to the VSCF J6 connector.

 S 425-005

 (4)  
Connect the interface cable from the BIT Interrogation module to the 286 PC Lap Top Computer.

 (5)  
Connect a 28VDC supply to the BIT Interrogation module.

 S 865-007

 (6)  
Apply external power or APU power 28V DC Bus (AMM 24-22-00/201).

 S 425-006
 (a)  Make sure 28VDC is supplied to the BIT Interrogation module.
 S 865-008
 (7)  
Turn the 286 PC lap top computer on. Enter the DOS operating enviornment.

 S 865-009

 (8)  
Select the directory which contains the applicable BIT Interrogation software.

 (9)  
Type in DIAGNOSE. Press ENTER.

 S 865-010
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH -15 THROUGH -20 VSCF ú

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A 737-300/400/500MAINTENANCE MANUAL
 S 865-011
 (10)
 Press the "F1" key to enter the on-line mode.

 S 865-012

 (11)
 Press "F3" key to reset the flight cycle records.

 NOTE: For the 10-61224-19 and -20 VSCF units, this will not clear
____ the NVM. It will only put a clear block in the NVM. The VSCF FAULT light wil not come on because of past faults stored in the NVM.
 S 865-013
 (12)
 For 10-61224-15 and -16 VSCF units only, reset 20 flight cycle records. This will clear the NVM.

 S 865-014

 (13)
 Select the RESET switch on the BIT Interrogration Interface module to reset the VSCF FAULT light.

 S 865-015

 (14)
 Exit the computer program and turn the computer off.

 S 865-016

 (15)
 Turn off the 28VDC power supply.

 S 865-017

 (16)
 Remove electrical power from the airplane (AMM 24-22-00/201).

 S 425-018

 (17)
 Disconnect the test wire bundle from the J6 connector and connect the airplane connector.

 S 715-019

 (18)
 Do the VSCF Disconnect test (AMM 24-11-11/501).

 NOTE: The VSCF Disconnect test is included in the AC Generation
____ test (AMM 24-11-11/501) or the VSCF Load test (AMM 24-11-11/501). The VSCF Disconnect test or the VSCF disconnect part of the AC Generation test or VSCF Load test must be done before the airplane is returned to service.
 S 845-020
 (19) Restore the airplane to normal.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH -15 THROUGH -20 VSCF ú

 24-11-12
 ú ú 01 Page 502 ú Mar 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 VSCF VACUUM BREAK VALVE - REMOVAL/INSTALLATION
______________________________________________
 1.  General_______
 A. This procedure contains two tasks:
 (1)  
The removal of the vacuum break valve from the variable speed constant frequency (VSCF) unit.

 (2)  
The installation of the vacuum break valve on the VSCF. The installation task includes steps to examine the installation for leaks.

 (3)  
The vacuum break valve is located on the upper left corner of the VSCF sight glass. The vacuum break valve replaces the vent cap on airplanes incorporating Sundstrand service bulletin 977J460-24-3.

 (4)  
The vacuum break valve has a fine mesh and the color is grey. The valve prevents vacuum build-up in the VSCF. Removal of the vacuum vent valve is not required to service or check oil level in the VSCF.
　
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