Control Drum and Shaft Assembly Installation  563 
76-11-31  Figure 401 (Sheet 1)  Jan 20/83 
Page 404 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

506  Control Drum and Shaft Assembly Installation 
Feb 15/69  Figure 401 (Sheet 2)  76-11-31 
Page 405 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

E.  Position spacer (30A) and coverplate (30) on reverser follow-up shaft (32) with coverplate against strut lower firewall surface. Insert three screws through support bracket, strut firewall, and coverplate and secure with washers and locknuts (28, 29).
NOTE:  The thrust reverser follow-up shaft lower bearing (31), if removed during drum and shaft assembly removal, must be installed on thrust reverser follow-up shaft prior to installation of spacer and coverplate.
F.  Position lower support bracket (14) on strut lower firewall around engine start and thrust shafts. Insert five screws through support bracket, strut firewall, and low support bracket and secure with washers and locknuts (15, 16).
G.  Position engine thrust push-pull cable bracket over push-pull cable support bracket studs (13).
H.  Position engine thrust crank (17) on splined portion of engine thrust shaft (34) with indexing (wide) tooth and valley mated.
I.  Retain thrust crank using washer (18) and nut (19). Tighten nut to 200 to 500 pound-inches and lockwire to thrust crank (17).
J.  Position engine start push-pull cable bracket over push-pull cable support bracket studs (13).
K.  Place spacer (20) on lower end of engine start shaft (33).
L.  Position engine start crank (21) on splined portion of start shaft (33) with indexing (wide) tooth and valley mated.
M.  Retain spacer (20) and start crank (21) on start shaft using washer (22) and locknut (23). Tighten locknut to 100 to 140 pound-inches.
N.  Position spacer (27) on lower end of thrust reverser follow-up shaft (32).
O.  Position follow-up crank (26) on splined portion of follow-up shaft (32) with indexing (wide) tooth and valley mated.
P.  Retain spacer (27) and follow-up crank (26) on follow-up shaft using washer (25) and lock-nut (24). Tighten locknut to 100 to 140 pound-inches.
500 
76-11-31 Page 406  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 15/68 

Q.  Secure engine push-pull cable brackets to push-pull cable support bracket studs (13) using two washers and locknuts.
R.  Connect hydraulic lines (7) to thrust reverser directional valve.
S.  Install four engine control cables on their respective drums using new cotter pins (35) to retain cables (detail A). Remove identification tags from cables and install removed cable guards (11).
T.  Adjust and test engine control system for applicable engine (Ref 76-11-0, Adjustment/Test).
5.  Restore Airplane to Normal Configuration
A.  Install access door No. 6301 or 6401 in wing leading edge above wing-to-engine fairing (Ref Chapter 12, Access Doors and Panels).
B.  Unclamp start and thrust levers on control stand.
C.  Ensure that turnbuckle locking clips are installed in four control cable turnbuckles located in wing leading edge.
D.  Remove leading edge flap locks (Ref 27-81-0 MP).
WARNING:  LEADING EDGE FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.
506 
Jan 20/82  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  76-11-31 Page 407 

ENGINE START SHAFT - REMOVAL/INSTALLATION
1. General
A.  The engine start shaft may be removed from the control drum and shaft assembly by removing the engine start crank from the start shaft below the strut firewall, and then lifting the start shaft out thru the top of the drum and shaft assembly. The engine need not be removed for this procedure.
B.  Replacement of shaft bearings is anticipated to be the primary maintenance required on this component. Following start shaft removal, the bearings may be examined for condition, and if necessary, replaced prior to shaft reinstallation.
2.  Prepare to Remove Engine Start Shaft
A.  Remove 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

B.  Extend flaps and install leading edge flap locks (Ref 27-81-0 MP).
　
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