27-31-00
ALL ú ú 02 Page 540 ú Mar 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
2) Make sure the inspection hole of the rod end bearing can not be seen. a) If the thread engagement is not correct, you must do
the course adjustment.
(r)
Do the measurement of X at the second hinge to make sure the the tab adjustment is correct.
(s)
Install the access panels for the tab rods.
(t)
AIRPLANES WITH THE ALUMINUM TAB PUSHRODS;
Install the access panels for the stabilizer.
S 825-110
(10)
Adjust the elevator tab pushrods after the Elevator Power Off Flight Test.
(a)
Compare the number of turns of the stabilizer trim control wheel from the flight test data with the limits in Fig. 510.
NOTE: Do this adjustment only when the number of turns of the
____ stabilizer trim control wheel is more than the limits shown on Fig. 510.
(b)
Make sure that the B dimension is at 41.57 |0.05 inches (3 units of trim).
(c)
Do the task to Remove the Pressure from the Elevator Hydraulic System A and B (AMM 27-31-00/201).
(d)
If aluminum tab pushrods are installed, remove the access panel 9105 or 9205.
(e)
Remove the 9313L or the 9413R access panel for the tab pushrods.
(f)
Push the elevator trailing edge full up.
(g)
While you move the elevator trailing edge down, align the left and right elevator with the index mark in |0.04 inch or less.
NOTE: Keep the elevators at this position while you adjust
____ the tab pushrods. If the elevator position is changed, you must put the elevator trailing edge at the full up position and do this step again before you continue.
(h) Set the tab rigging fixture below and along the elevator rib at the second inboard tab hinge.
NOTE: The fixture must only touch the elevator at the spacers.
____ The permitted difference in thickness of the spacers is
0.005 inch.
1) Measure the tab position (this will be "Xm"). 2) Write down the Xm value.
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27-31-00
ALL ú ú 02 Page 541 ú Nov 12/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
0.10
0.08
0.06
0.04
0.02
0.00
-0.02
-0.04
-0.06
-0.08
-0.1
ELEVATOR TAB ADJUSTMENT(INCH)
(TRAILING EDGE DOWN) (TRAILING EDGE UP)
-10-8-6-4-2 0 2 4 6 8 101214
AIRPLANE NOSE DOWN TRIM
AIRPLANE NOSE UP TRIM
(AIRPLANE PITCHED NOSE
(AIRPLANE PITCHED NOSE DOWN
UP DURING FLIGHT TEST)
DURING FLIGHT TEST)
USE OF GRAPH
STABILIZER TRIM WHEEL TURNS
1. IT IS NOT NECESSARY TO ADJUST THE ELEVATOR TAB UNLESS THE NUMBER OF STABILIZER TRIM WHEEL TURNS DURING THE FLIGHT TEST IS MORE THAN THE LIMITS THAT FOLLOW:
A. AIRPLANES WITH ALUMINUM TAB RODS, THE LIMITS ARE +1.0 TURN NOSE UP TRIM AND
-1.0 TURN NOSE DOWN TRIM.
B. AIRPLANES WITH TITANIUM TAB RODS, THE LIMITS ARE +2.0 TURNS NOSE UP TRIM AND
-2.0 TURNS NOSE DOWN TRIM.
2.
IF THE LIMITS IN STEP 1 ARE EXCEEDED, FIND THE POINT ALONG THE HORIZONTAL AXIS WHICH AGREES WITH THE NUMBER OF TURNS AND DIRECTION NECESSARY DURING THE FLIGHT TEST.
3.
FROM THIS POINT ON THE HORIZONTAL AXIS, MAKE A VERTICAL LINE TO THE DATA CURVE.
4.
DRAW A HORIZONTAL LINE FROM THE POINT ON THE DATA CURVE IN STEP 3 TO THE VERTICAL AXIS.
5.
THIS POINT ON THE VERTICAL AXIS IS THE ADJUSTMENT NECESSARY FOR EACH ELEVATOR TAB AT THE ELEVATOR TRAILING EDGE.
____ A. THE TAB IS MOVED UP OR DOWN FROM ITS CURRENT POSITION.
NOTE:
B. THE LEFT ELEVATOR TAB POSITION MUST BE THE SAME AS THE RIGHT ELEVATOR TAB POSITION IN |0.02 INCH.
C. THE ELEVATOR TAB POSITION MUST BE IN THE LIMITS SHOWN IN TABLE 505.
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