(e)  
Remove tab pushrod access panel at upper inboard end of elevator.

(f)  
On airplanes with a 1/2-inch diameter bushing installed in each tab mast fitting, fabricate tool using the dimensions given in detail B. Insert tool over bushing as shown, between rod end and tab mast fitting whenever tab pushrod checknuts are loosened or tightened.

(g)  
On right tab, loosen checknuts at each end of the two tab pushrods.

(h)  
Hold right elevator trailing edge in line with index on tail cone within 0.04 inch.

(i)  
Adjust right tab pushrods as follows to deflect tab trailing edge 0.22 (士0.01) inch up from elevator trailing edge. 1) Coarse Adjustment

500 
27-31-0 Page 518  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/89 

a) Remove bolts through aft rod ends. b) Turn rod ends as required (half turn at rod end equals approximately 0.1 inch at tab trailing edge). c) Reinstall bolts. 2) Fine Adjustment a) Turn tubes (turnbuckle style) as required (half turn at tube equals approximately 0.02 inch at tab trailing edge). b) To check that tab rods are not preloaded loosen nut on one bolt at rear end of tab pushrods.
c)  Check that bolt is without binding (like a rigging pin). If bolt cannot be easily rotated with finger, make some fine adjustment of one rod only until bolt is free without binding.
d)  Tighten nut on bolt at rear end of tab rod.
(j)  
Tighten four checknuts. To ensure adequate thread preload, tighten checknuts to 150-200 pound-inches.

(k)  
Provide hydraulic power as follows: 1) Provide elevator systems A and B hydraulic power. Refer to 27-31-0. 2) Position flight controls hydraulic system A switch to OFF and system B switch to

ON.

(l)  
Right tab shall be faired with elevator within 士0.03 inch. If necessary adjust tab pushrods per above procedure. Check that power off adjustment tolerance is not exceeded.

(m)  
Position flight controls hydraulic system B switch to OFF.

(n)  
On left tab loosen checknuts (four total) on the two tab pushrods.

(o)  
Hold left elevator trailing edge in line with index on tail cone within 士0.04 inch.

(p)  
Adjust left tab rods as follows to deflect tab trailing edge 0.22 士0.01 inch up from elevator trailing edge. For coarse and fine adjustment procedure, refer to step (h).

(q)  
Tighten four checknuts. To ensure adequate thread preload, tighten checknuts to 150-200 pound-inches.

(r)  
Position flight controls hydraulic system A switch to ON.

(s)  
Left tab shall be faired with elevator within士0.03 inch. If necessary, adjust tab pushrods per above procedure. Check that power off adjustment tolerance is not exceeded.

CAUTION:  DO NOT ATTEMPT TO CHANGE RIGGING BY CHANGING SHIMS IN TAB MECHANISM.

(t)  
Position flight controls hydraulic system A switch to OFF.

(u)  
Check for minimum thread engagement on all four tab pushrods. End of rod shall

CAUTION:  DO NOT ATTEMPT TO CHANGE RIGGING BY CHANGING SHIMS IN TAB MECHANISM.
500 
Feb 15/73  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-0 Page 518A 

cover at least 50% of inspection (8 places total). (6A) Adjust Elevator Tab Pushrods (Airplanes with Composite Elevators)
NOTE:  Measure tab position from bottom of trailing edge to top of straight edge as shown in Fig. 508A.
(a)  
Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).

CAUTION:  ELEVATORS AND TABS MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED. MAKE CERTAIN THAT ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF ELEVATOR AND TAB SURFACES.

(b)  
Check that horizontal stabilizer B dimension is set at 41.57 士0.05 inches and mach trim actuator is in null position per 27-31-0 MP.

(c)  
Remove lower inboard hinge cover located on lower forward inboard edge of elevator by removing 19 bolts (Fig. 508).

(d)  
Remove lower aerodynamic seal located on lower aft edge of horizontal stabilizer by removing attach bolts. It is not necessary to remove all bolts in order to access tab pushrods.

(e)  
Remove tab pushrod access panel at upper inboard end of elevator.

(f)  
Loosen checknuts (four total) on right elevator tab rods.

(g)  
Hold right elevator trailing edge in line with index on tail cone within 士0.04 inch.

NOTE:  If using TE27T-31001-15 and -17 rigging fixtures to obtain X dimension, proceed to step (i). If using C27028 or F80248-( ) rigging fixture, perform the following:
27-31-0  Oct 20/93
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 2(67)