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C.  It is anticipated that replacement of shaft bearings will be the primary maintenance required on the drum and shaft assembly. The assembly is designed to permit shaft-bearing replacement on the airplane. Should only bearing replacement be desired, refer to 76-11-41 for the start shaft, 76-11-51 for the thrust shaft, and 76-11-61 for the thrust reverser follow-up shaft. These sections provide removal/installation procedures for the respective shafts, during which bearing replacement may be performed.
D.  Removal of the drum and shaft assembly is accomplished by removing some of the cranks and hardware beneath the firewall, unbolting the support bracket from the wing front spar, and lifting the major portion of the assembly out thru the access opening in the wing leading edge.
E.  The illustrations accompanying this procedure show the No. 1 engine drum and shaft assembly. The No. 2 engine drum and shaft assembly is similar and the procedure is valid for both installations.
2.  Prepare to Remove Engine Control Drum and Shaft Assembly
A.  Remove the following access door in wing leading edge above wing-to-engine fairing (Ref Chapter 12, Access Doors and Panels).
(1)  
No. 6301 in left wing

(2)  
No. 6401 in right wing

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Jun 20/83  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  76-11-31 Page 401 

B.  Extend flaps and install leading edge flap locks (Ref 27-81-0 MP).
WARNING:  REFER TO 27-81-0 MP FOR LOCK INSTALLATION PROCEDURE. FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.

C.  Clamp appropriate thrust lever against aft stop on control stand.
D.  Clamp appropriate start lever in CUTOFF position.
E.  Gaining access thru extended leading edge flaps, remove turnbuckle-locking clips of two thrust cables and two start cables of applicable engine in wing leading edge. Loosen the four engine control cables using the turnbuckles.
3.  Remove Engine Control Drum and Shaft Assembly
A.  Remove four cable end fitting cotter pins (35) from engine start and thrust drums (Fig. 401). Remove and tag cables to identify function and location. Remove cable guards (11) as required to free cables.
B.  Deleted.
C.  Depressurize thrust reverser hydraulic system. Disconnect hydraulic lines (7) connecting to thrust reverser directional valve.
D.  Remove locknut (24) and washer (25) retaining follow-up crank (26).
E.  Push follow-up crank (26) down off splined portion of thrust reverser follow-up shaft (32) and swing crank out of way.
NOTE:  Spacer (27) will fall free when follow-up crank (26) is removed from follow-up shaft (32).
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76-11-31 Page 402  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jan 20/82 

F.  Remove three screws, washers, and locknuts (28, 29) securing coverplate (30) to firewall and remove coverplate and spacer (30A).
NOTE:  Thrust reverser follow-up shaft lower bearing (31) may fall free when coverplate (30) and spacer (30A) are removed. If bearing is loose on shaft, remove to prevent falling out during removal of drum and shaft assembly.
G.  Remove washers and locknuts securing push-pull cable brackets to support bracket studs (13). Rotate engine thrust crank (17) and start crank (23) to disengage push-pull cables from support bracket studs.
H.  Remove locknut (23) and washer (22) retaining engine start crank (21) and remove start crank from engine start shaft (33). Spacer (20) above start crank will fall free when start crank is removed.
I.  Cut lockwire and remove nut (19) and washer (18) from engine thrust shaft (34). Remove engine thrust crank (17) from thrust shaft.
J.  Remove five screws, washers, and locknuts (15, 16) securing lower support bracket (14) to firewall and remove bracket.
K.  Remove lockwire, four bolts and washers (5) attaching support bracket (4) to wing front spar.
L.  Grasp drum and shaft assembly by the support bracket and carefully lift assembly out of airplane.
4.  Install Engine Control Drum and Shaft Assembly
A.  This installation procedure assumes the drum and shaft assembly was removed using the preceding removal procedure. Thus the assembly will consist of the engine thrust and start shafts and the thrust reverser follow-up shaft installed in the support bracket less only the components installed beneath the strut firewall. The thrust reverser directional valve should be installed.
B.  Position drum-and-shaft assembly over strut firewall at wing front spar. Thrust reverser follow-up shaft should be forward.
C.  Carefully lower drum and shaft assembly through two holes in strut firewall.
D.  Secure support bracket (4) to wing front spar using four attaching bolts and washers (5). Install lockwire on bolts through support bracket lockwire holes.
　
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