(q) Install tab pushrod access panels and stabilizer access panels. (6B) Adjust the elevator tab pushrods after the flight test.
NOTE:  Do this adjustment only when the number of turns of the stabilizer trim control wheel exceeds the limits during the MM 27-11-0 flight test. A flight test is only required following certain maintenance actions on the ailerons. A flight test is not required following any maintenance action involving the elevator or elevator tab mechanisms.
(a)  
Compare the number of turns of the stabilizer trim control wheel from the flight test data with the limits in Fig. 508B.

(b)  
Make sure that the B dimension is at 41.57 士0.01 inches.

(c)  
Set the mach trim actuator at the NULL position.

(d)  
Remove the elevator systems A and B hydraulic power.

(e)  
Align the right elevator with the index mark in 士0.04 inch or less.

NOTE: Keep the elevators at this point while you adjust the tab pushrods.

(f)  
Remove the access panel 9105 or 9205.

(g)  
Remove the access panel for the tab pushrods.

(h)  
Set the tab rigging fixture below and along the elevator rib at the second tab hinge.

NOTE:  Use the same method (single or four point method) that you used to adjust the tab pushrods before the flight test. The fixture must only touch the elevator at the spacers. The permitted difference in thickness of the spacers is 0.005 inch.
500 
Aug 01/94  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-0 Page 518E 

Elevator Tab Pushrod Adjustment  500 
27-31-0  Figure 508  May 01/03 
Page 518F 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(i)  Adjust the tab pushrods until they agree with the tab adjustment determined in  Fig. 508B (士0.01 inch). 1) Coarse adjustment of the elevator tab trailing edge.
a)  One half turn of the 3/8 inch rod end moves the tab trailing edge by 0.089 inch. b) One half turn of the 7/16 inch rod end moves the tab trailing edge by 0.10 inch. 2) Fine adjustment of the elevator tab trailing edge. a) One half turn of the rod barrel moves the tab trailing edge by approximately
0.017 inch.
(j)  
Make sure that the right elevator trailing edge aligns with the index mark in 士0.04 inch.

(k)  
Calculate the final tab position “a” after the flight test:

TABLE 2 - ELEVATOR TAB POSITION AFTER FLIGHT TEST
Airplane  Initial Tab  Tab  Final Tab  Spacer  Permitted 
Tempera- Dimension  Adjustment  Dimension  Thickness  Tab Position 
ture  Before Flight Test TABLE 1 and Fig. 508A  After Flight Test Fig. 508B  “Xf” After Flight Test (Xf=Xi+Delta X)  “t”  “a” After Flight Test (a=Xf-t) 
F  C  Xi+/-0.01  Delta X  Xf+/-0.01  “t”  “a” inch 
120  49  Metal-Fiberglass  Composite 
0.120-0.360  0.083-0.323 
110  43  0.120-0.360  0.090-0.330 
100  38  0.120-0.360  0.098-0.338 
90  32  0.120-0.360  0.105-0.345 
80  27  0.120-0.360  0.113-0.353 
70  21  0.120-0.360  0.120-0.360 
60  16  0.120-0.360  0.127-0.367 
50  10  0.120-0.360  0.135-0.375 
40  4  0.120-0.360  0.142-0.382 
30  -1  0.120-0.360  0.150-0.390 
20  -7  0.120-0.360  0.157-0.397 
10  -12  0.120-0.360  0.164-0.404 
0  -18  0.120-0.360  0.172-0.412 
-10  -23  0.120-0.360  0.179-0.419 
-20  -29  0.120-0.360  0.186-0.426 
-30  -34  0.120-0.360  0.193-0.433 
-40  -40  0.120-0.360  0.200-0.440 
-50  -46  0.120-0.360  0.208-0.448 
-60  -51  0.120-0.360  0.215-0.454 

500 
May 01/01  27-31-0 
Page 518G 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

EXAMPLE:  The initial tab dimension “Xi” is 0.74 inch at 70 degrees F, the spacer thickness “t” is 0.50 inch, the stabilizer trim control wheel turns required during the flight test was 4 turns airplane nose up. A tab adjustment of -0.075-inch tab trailing edge down is determined from Fig. 508B. The final tab dimension “Xf” is 0.74-0.075=0.665 inch. The tab position “a” is 0.665-0.500=0.165 inch, which is within the after flight test limits of TABLE 2.
　
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