(h)  Adjust right tab rods as follows to obtain X dimension using rigging fixture C27028 or F80248-( ) (Fig. 508A): 1) Locate and hold fixture below and along elevator rib at second tab hinge.
NOTE:  Fixture should only contact elevator at spacers. Spacer thickness should be within 0.005 inch of each other.
2)  Measure X dimension perpendicular to fixture at tab trailing edge as shown in Fig. 508A.
3)  Calculate X dimension (power off) per Table 1.
TABLE 1
Condition  Airplane Temperature 。F 。C  Tab Position "a" 士0.01 Required  Spacer Thickness "t"  X Dimension X = a + t 士0.01 
Power off  120  49  0.203 
110  43  0.210 
100  38  0.218 
90  32  0.225 
80  27  0.233 
70  21  0.240 
60  16  0.247 
50  10  0.255 
40  4  0.262 
30  -1  0.270 
20  -7  0.277 
10  -12  0.284 
0  -18  0.291 
 -10  -23  0.298 
 -20  -29  0.306 
 -30  -34  0.312 
 -40  -40  0.320 
 -50  -46  0.327 
 -60  -51  0.335 

Initial Elevator Tab Position
NOTE:  Elevator tab moves 0.0073 inch for each 10。F temperature change.
EXAMPLE:  Tab position "a" is 0.24 inch at 70。F, spacer thickness "t" is 0.50 inch, then required X dimension is 0.74士0.01 inch.
NOTE:  Elevator tab adjustment should be accomplished according to temperature noted or interpolated from Table 1.  To ensure that proper adjustment is obtained allow a minimum of 1 hour at constant ambient temperature 士5。F for airplane temperature to stabilize.
Oct 20/93 27-31-0 Page 518C
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

NOTE:  The following is an optional method for measuring the elevator trailing edge position at four places. When using this method, the resulting number may differ slightly from the single point method. Only one method should be used for consistency; the single point method in step (h) or the four point method in step (i).
(i)  
Measure the X dimension as described in step (h)1), except at four places (two inboard and two outboard locations) using rigging fixtures TE27T-31001-15 and -17.

(j)  
Obtain the average of the four X dimensions recorded in steps (h)1) and (i). Subtract this average value from the required nominal X dimension. Record the difference and determine whether the value was positive or negative.

(k)  
Readjust the tab rigged position obtained in step (h)1) by adding the value obtained in step (j) to the actual X dimension recorded in step (h)1). This will be the final tab rigged X dimension. Note that a positive value in step (h)1), and a negative value in step (j) will result in a lower X dimension. 1) Coarse adjustment:

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) Install bolts. 2) Fine adjustment: a) Turn tubes (turnbuckle style) as required (full turn at tube equals approximately 0.035 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 bolt is without binding. 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.
(l)  
Tighten four checknuts (right elevator). To ensure adequate thread preload, tighten checknuts 150 to 220 pound-inches.

(m)
Adjust left tab rods as follows to obtain X dimension. 1) Position tab-rigging fixture below and along elevator rib at second tab hinge.

500 
27-31-0 Page 518D  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/90 

NOTE:  Fixture edge should only contact elevator at spacers. Spacer thickness should be within 0.005 inch of each other.
2)  Measure X dimension perpendicular to fixture at tab trailing edge as shown in Fig. 508A.
(n)  
Check that left and right tab positions are within 士0.02 inch of each other.

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

(p)  
Check for minimum thread engagement on all four-tab pushrods. End of rod shall cover at least 50% of inspection hole (8 places).
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊 飛行操縱 FLIGHT CONTROLS 2(68)