(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 - Unpublished Work - See title page for details. 27-31-0 Page 518E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 - Unpublished Work - See title page for details.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.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(69)
