adjustment within 1/2 turn of rod end.
CAUTION: DO NOT DISTURB VENDOR INSTALLED LOCKWIRE.
2)  Loosen fine adjustment jamnut and adjust (rotate) fine adjustment hex until holes in rod end and thrust crank are aligned to allow free insertion of bolt. Do not exceed 0.84 inch maximum between cable retainer and fine adjustment hex after adjustment.
3)  Use lockwire to check that inspection hole in rod end is completely covered. Install bolt retainer around crank fork and under bolthead. Insert bolt through aligned holes in rod end and thrust crank. Bolt shall fit freely prior to attaching nut.
4)  Install locknut on rod end connecting bolt with washer. Tighten nut 50 to 70 pound-inches and bend retainer tab over bolthead (Fig. 504).
545 
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H32156
553  Start and Thrust Push-Pull Cable Disconnects 
May 01/99  Figure 504 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  76-11-0 Page 509 

5) Tighten jamnut against fine adjustment hex (Fig. 504).
6) Tighten jamnut against lower rod end on airplanes affected by 3) above.
7) Secure fine adjustment hex and jamnut(s) by installing lockwire as shown.

(g)  
Remove rig pin from engine thrust drum.

(h)  
On GJ B-2509, B-2510,
adjust thrust lever position transmitter (LVDT) (Ref 22-31-81 A/T).

(i)  
Remove rig pin from the right start crank extension.

(j)  
Perform engine thrust control system test procedure.

(5)  Adjust the engine thrust rod.
(a)  
Install a Type 1 rig pin through the engine thrust quadrant (Fig. 503).

(b)  
Disconnect the thrust push-pull cable at the left thrust crank (Fig. 504).

(c)  
Put the thrust crank for the fuel control unit in the idle position, install the Type 2 rig pin (Fig. 505, Detail C).

(d)  
Remove the nut, washer and bolt securing the thrust rod to the right thrust crank (Fig. 505, Detail A).

(e)  
Install the thrust control rig pin bracket (Fig. 505, Detail A).

(f)  
Install a Type 3 rig pin through the right thrust crank, thrust rod and the thrust control rig pin bracket, adjust the thrust rod (Fig. 505, Detail A).

(g)  
If the Type 3 rig pin cannot be freely installed through the right thrust crank, thrust rod and the thrust control rig pin bracket, adjust the thrust rod (Fig. 505 Detail A). 1) Loosen the thrust rod jam-nut. 2) Adjust the rod end until the rig pin is freely installed into the control rig pin

bracket.
3) Tighten the jam-nut.

(h)  
Secure the thrust rod to the right thrust crank using bolt, washer and nut. Torque nut 30 to 40 pound-inches and install cotter pin.

(i)  
Install the thrust push-pull cable at the left thrust crank with bolt: For push-pull cable installations using locknut, install washer and locknut and torque nut 50 to 70 pound-inches (Fig. 504). For push-pull cable installations using castellated nut, install washer and castellated nut, torque castellated nut 30 to 40 pound-inches and install cotter pin (Fig. 504). For push-pull cable installations with bolt retainer, insert bolt retainer around crank for and under bolthead, install washer and locknut. Torque nut 50 to 70 pound-inches and bend retainer tab over bolthead (Fig. 504).

(j)  
Remove the rig pins.

(k)  
Remove the thrust control rig pin bracket.

5C8 76-11-0 May 01/99
Page 510
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

B.  Reverse Thrust Detent Adjustment
NOTE:  The following procedures are only required if thrust lever or detent parts are replaced or procedures are used to check for system malfunction.
(1)  Prepare reverse thrust control system for detent adjustment.
(a)  
Deleted.

(b)  
Override the thrust reverse follow-up system: 1) Disconnect reverse thrust follow-up push-pull cable from crank arm at thrust reverse (Fig. 506).

2)  Rotate engine control drum and shaft assembly thrust reverser interlock cam in the direction which allows movement of reverse thrust lever by pulling push-pull cable until end of normal travel.
3) Open reverse thrust isolation valve circuit breakers C276 and C277. 4) Install reverse thrust isolation valve ground lock assembly F80109-3.
575 
May 15/80  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  76-11-0 Page 511 

F59456 G42818
Cross-Shaft to Fuel Control Linkage  501 
76-11-0  Figure 505 (Sheet 1)  Feb 01/96 
　
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