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 GLOVES WHEN YOU USE THE MEK.  KEEP THE MEK AWAY FROM
 SPARKS, FLAME AND HEAT.  MEK IS A POISONOUS AND FLAMMABLE
 SOLVENT WHICH CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO
 EQUIPMENT.
 (i)  Make sure the space between the strut fairing and the extension
 ring is clean.  If necessary, clean the surface with solvent
 and rub the surface dry.
 (j)  Use a brush or spray to apply 1200 Red primer in the space
 between the strut fairing and the extension ring.
 1)  Allow to the primer to dry for 1 hour.
 (k)  Apply the DC 93-006-1 (aerodynamic) sealant to the space
 between the strut fairing and the extension ring, as shown in
 Fig. 601.  Make the sealant smooth.
 1)  Let the sealant cure for 10 hours.
 NOTE:____ A ten hour cure time is for usual conditions of
 77 |2°F (25 |1°C) and 50 |5% relative humidity.  The
 cure time can be made faster if you flow warm air
 (not more than 120°F [50°C]) along the sealant.  You
 can also make the sealing surfaces warm before you
 apply the sealant.
 Airplane operation is permitted after a cure time of
 4 hours.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 75-32-01
 ALL  ú ú C01.1 Page 610 ú Jul 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
S 416-018-C00

 WARNING:_______ OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
 REVERSERS.  IF YOU DO NOT OBEY THE INSTRUCTIONS WHEN YOU CLOSE
 THE THRUST REVERSER, INJURIES TO PERSONS AND DAMAGE TO
 EQUIPMENT CAN OCCUR.

 (14)
 Close the left thrust reverser half (AMM 78-31-00/201).

 S 416-019-C00

 (15)
 Close the left fan cowl panel half (AMM 71-11-02/201).

 S 796-015-C00

 (16)
 Do Test No. 3 - Leak Check - Idle Power (AMM 71-00-00/501).

 (a)  Make sure that there are no leaks at the VBV open and closed tube connections at the MEC and at the 9 o'clock tube assembly.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 75-32-01
 ALL  ú ú C01 Page 611 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
BLEED VALVE STOP MECHANISM - REMOVAL/INSTALLATION
_________________________________________________
 1.  General
_______
 A.  This procedure includes the removal and installation of the fuel gear motor and stop mechanism of the bleed valve as an assembly.
 B.  When the assembly is removed from the engine, the fuel gear motor can be removed from the stop mechanism.
 C.  A leak test of the fuel fittings for the gear motor follows the
 installation procedure.

 D.  The fuel gear motor and stop mechanism of the bleed valve are found at the 9 o'clock position on the middle box structure of the fan frame.
 TASK 75-32-02-004-001-C00
 2.  Remove the Bleed Valve Stop Mechanism
_____________________________________
 A.  Equipment
 (1)  
856A2501, Wrench - Dual Purpose Ratchet for VBV Manual Operation, CFM

 (2)  
Container - one gallon (4-liter) capacity, for use with fuel

 B.  Consumable Materials
 (1)  Fluid - Preservative Hydraulic, MIL-C-6529, Type III (AMM 70-10-01/201)
 C.  References
 (1)  
AMM 70-10-01/201, Consumable Materials

 (2)  
AMM 71-11-02/201, Fan Cowl Panels

 (3)  
AMM 75-32-00/201, Variable Bleed Valve System

 (4)  
AMM 78-31-00/201, Thrust Reverser System

 D.  Access
 (1)  
Location Zones 506 Engine No. 1 - 9 o'clock position on the fan frame 606 Engine No. 2 - 9 o'clock position on the fan frame
　
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