(b)  
Remove the fuel manifold pressure check adapter.

 (c)  
Install the fuel flow transmitter (AMM 73-31-01/401).

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
(d)  Install lockwire on coupling nuts of the fuel supply line to tabs on the fuel nozzle.
 NOTE: The lockwire pigtail must not be more that 0.75 inch
____ (19 mm) and mut be bent in to the fuel nozzles. This can prevent snags or interference with the shroud connector.
 S 794-008-C00
 (13) ENGINES PRE-CFMI-SB 73-116 (ENGINES WITH FUEL DRAIN MANIFOLDS); Do a check on the shroud connector and drain lines for leakage.
 (a)  
Move the shroud connector of the fuel manifold on to the fuel nozzle and tighten with soft jawed pliers.

 (b)  
Tighten until the connector touches the fuel nozzle face with a maximum of two full threads showing.

 (c)  
Connect the drain line to the shroud fitting.

 (d)  
Attach the hose assembly of the air pressure test to the fuel supply shroud drain line before 6 o'clock strut (Fig. 403).

 (e)  
Apply 20-25 psi (138-173 kPa) dry air or nitrogen to the drain line.

 (f)  
Turn off the pressure supply.

 (g)  
Make sure the pressure does not decrease more than 10 psi (69 kPa) in 2 minutes.

 (h)  
If the pressure decrease more that 10 psig (69 kPa) in 2 minutes, do these steps: 1) Apply leak-tek to shroud connector of the fuel manifold

 (Fig. 401 and 403).
 2) Apply 50-60 psi (345-414 kPa) dry air or nitrogen to the
 drain line.
 3) Look for the source of the leakage.
 4) If the leakage occurs at the shroud connector, do these
 steps:
 a) Remove drain line.
 b) Loosen the shroud connector and move the shroud
 connector rearward.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
FUEL SUPPLY SHROUD DRAIN LINE
VENT CLAMP
VALVE
PRESSURE GAGE SHUTOFFSEE A VALVE
AIR OR DRY NITROGEN PRESSURE SUPPLY
TEST EQUIPMENT SCHEMATIC DIAGRAM
FUEL SUPPLY SHROUD DRAIN LINE
6 O'CLOCK STRUT
FWD
A
Fuel Supply Shroud Drain Line Location Figure 403
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ENGINES PRE-CFMI-SB 73-116 ú

 73-11-04
 (WITH FUEL DRAIN MANIFOLDS)  ú ú C01 Page 423 ú Mar 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
c) Do a check on the O-ring for damage.
 d) Replace the O-ring if it is necessary.
 e) Tighten the shroud connector with soft jawed pliers
 until the connector touches the fuel nozzle face with a
 maximum of two full threads showing.
 f) Connect the drain line.
 g) Apply 50-60 psi (345-414 kPa) dry air or nitrogen to
 the drain line.
 h) Turn off the pressure supply.
 i) Make sure the pressure does not decrease more than
 10 psi (69 kPa) in 2 minutes.
 5) If leakage occurs between the shroud connector and fuel
 supply line, do these steps:
 a) Remove the drain line.
 b) Loosen the shroud connector.
 c) Move the shroud rearward until you can get access to
 the O-ring on the fuel supply line.
　
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