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FUEL FILTER BYPASS WARNING SYSTEM - ADJUSTMENT/TEST
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 1.  General
_______
 A.  The fuel filter is found between the heat exchanger for fuel/oil and the high pressure stage of the fuel pump. The fuel filter stops ice and unwanted particles in the fuel. This is so that they cannot cause damage to the high pressure stage of the fuel pump and the MEC. If the filter becomes clogged, a bypass valve releases the fuel to the high pressure stage of the fuel pump.
 B.  The lights that follow:
 -
the amber warning light for FILTER BYPASS

 -
the left and right MASTER CAUTION lights

 -
the FUEL light
 will come on when:

 

 -there is an almost blocked filter condition
 -the pressure decrease across the filter increases above the switch setting.
 C.  A system test of the differential pressure switch is given in task 2. The test is to make sure of correct pressure switch operation after a warning light for FILTER BYPASS comes on. The test is also done after replacement of the differential pressure switch. No operational test is given since there must be an unusual (plugged) filter condition for the system to operate.
 TASK 73-34-00-705-001-C00
 2.  Fuel Filter Bypass Warning System Test
______________________________________
 A.  Equipment
 (1)
Container - 2-gallon (8-liter) capacity, use with fuel

 (2)
Pressure gage - 0-15 psi min, |1% precision

 (3)
Fuel/Oil Pressure Switch Test Equipment, C79001-1 (Optional)

 B.  Consumable Materials
 (1) Pressurized gas - dry air, 0-15 psi (0-100 kPa)
 C.  References
 (1)
AMM 24-22-00/201, Electrical Power

 (2)
AMM 33-15-00/501, Master Warning and Caution Lights

 (3)
AMM 71-11-02/201, Fan Cowl Panels

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 73-34-00
 ALL  ú ú C01 Page 501 ú Nov 15/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
(4)  AMM 78-31-00/201, Thrust Reverser System
 D. Access
 (1)  
Location Zones 506 Engine No. 1 - 7 o'clock position above the upper drain line support block of the fan case

 606  Engine No. 2 - 7 o'clock position above the upper drain line support block of the fan case

 (2)  
Access Panels
 5746L Engine No. 1 - Left Fan Cowl Panel
 5846R Engine No. 2 - Left Fan Cowl Panel

 

 E. Prepare for the Fuel Filter Bypass System Test
 S 865-002-C00
 (1)  
Supply electrical power to the applicable engine (AMM 24-22-00/201).

 S 865-003-C00

 (2)  
Make sure these circuit breakers are closed (Fig. 501):

 (a)  P6-3 Load Control Center
 1) INDICATOR MASTER DIM BUS BAT
 2) INDICATOR MASTER DIM BUS NO. 1 DC
 3) INDICATOR MASTER DIM BUS NO. 2 DC
 4) INDICATOR MASTER DIM BUS SECT 1
 5) INDICATOR MASTER DIM BUS SECT 2
 6) INDICATOR MASTER DIM BUS SECT 3
 7) INDICATOR MASTER DIM BUS SECT 4
 8) INDICATOR MASTER DIM BUS SECT 5
 9) INDICATOR MASTER DIM BUS SECT 6

 S 865-004-C00
 (3)  Make sure this circuit breaker is closed:
 (a)  P6-3 Load Control Center
 1) PANEL & INSTR 28V PRIMARY DIM & TEST

 S 865-005-C00
 (4)  Make sure these circuit breakers are closed:
 (a)  P6-3 Load Control Center
 1) MASTER CAUTION ANNUNCIATOR No. 1
 2) MASTER CAUTION ANNUNCIATOR BAT

 F. Do the Fuel Filter Warning System Test
 S 015-006-C00
 (1)  Open the left fan cowl panel (AMM 71-11-02/201).
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 73-34-00
 ALL  ú ú C02 Page 502 ú Mar 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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