76-11-04
 ALL  ú ú C03 Page 232 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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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 ////////////////////////
STRUT DRUM CONTROL BOX - REMOVAL/INSTALLATION
_____________________________________________
 1.  General
_______
 A.  This procedure has two tasks. They are the removal and the installation of the strut drum control box.
 B.  This procedure applies to the left and right installation. Differences are written in the procedure.
 TASK 76-11-05-004-001-C00
 2.  Strut Drum Control Box Removal (Fig. 401)
______________________________
 A.  Equipment
 (1)  Rig Pin Assembly - F70207-8. Component of F70207-93 Rig Pin Kit. Optional: MS20392-4C pin (or equivalent 0.311 (+0.000/-0.002)-inch diameter, 3-inch long rod or bolt)
 B.  References
 (1)  
AMM 12-31-71/201, Wing Upper Surface Access Doors and Panels

 (2)  
AMM 27-81-00/201, Leading Edge Flaps and Slats

 (3)  
AMM 76-11-04/201, Engine Control Cables

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

 C.  Access
 (1)  
Location Zones
 507/607 Strut
 504/604 Thrust Reverser - Left
 505/605 Thrust Reverser - Right

 (2)  
Access Panels
 6301L/6401R Leading Edge Access Panel

 D.  Procedure
 S 044-002-C00
 WARNING: DO THE DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE
_______ THRUST REVERSER. THE ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
 (1)  
Do the deactivation procedure for the thrust reverser for ground maintenance (AMM 78-31-00/201).

 S 864-029-C00

 (2)  
Extend the flaps and install the leading edge flap locks (AMM 27-81-00/201).

 S 014-004-C00

 (3)  
Remove the access panel No. 6301 (engine No. 1) or 6401 (engine No. 2) from the upper aft surface of the nacelle strut (AMM 12-31-71/201).

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 76-11-05
 ALL  ú ú C01 Page 401 ú Jul 15/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
SEE A
CABLE QUADRANT 
(ENGINE NO. 1 SHOWN,- BOLT AND WASHER 
TIA/TIB CABLE  SEE  B  FOR ENGINE NO. 2)  (4 LOCATIONS)
BALL TERMINAL 
"PT PWR" RIG PIN 
HOLE (UNDER SEAL) 

THRUST CONTROL
PUSH-PULL CABLE
STRUT DRUM CABLE TERMINAL
CONTROL BOX RETAINER SCREWS
THRUST REVERSER FEEDBACK PUSH-PULL CABLESCABLE QUADRANT
"PT PWR" RIG PIN  FWD
A
HOLE (UNDER SEAL)
T2A CABLE
T2B CABLE
(ENGINE NO.2)
B

Strut Drum Control Box Installation Figure 401
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 76-11-05
 ALL  ú ú C01 Page 402 ú Mar 15/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
S 034-005-C00
 (4)  Turn the turnbuckles in the wing leading edge to release the tension in T()A and T()B cables for the applicable engine.
 NOTE: See AMM 76-11-04/201 for turnbuckle locations.
____
 S 034-006-C00
 (5)  Disconnect the thrust control cable(s) from the control box quadrant as follows:
 (a)  
ON ENGINE NO. 1; Cut the lockwire and remove the T1A/T1B cable from the quadrant.

 (b)  
　
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