(3) Excessive Forces Right Discrepancy Correction
(a)
Forces are recorded by pilots at approximately 30 degrees clockwise and 30 degrees counterclockwise control wheel position.
(b)
Obtain force ratio by dividing clockwise force by counterclockwise force.
(c)
Forces are corrected by changing tab rod lengths to raise or lower aileron tab relative to aileron.
(d)
After force ratio is determined select correct amount of tab rod change from Fig. 503.
NOTE: For either tab, both rods must be changed in sets.
(e)
With aileron indexes aligned, measure the tab trailing edge mismatch with the lower aileron surface by using a straightedge or aileron tab alignment protractor positioned at the rod attach points and record this dimension.
NOTE: After aileron tab control rod length adjustments are completed, the aileron tab training edge must be within -0.01 to +0.15 inch of the aileron lower surface on airplanes with nonadjustable aileron tab control rods, or within +.05 to +0.09 inch of aileron lower surface on airplanes with adjustable aileron tab control rods. These dimensions are applicable at the midpoint of the aileron tab. To complete the adjustment within the required dimensions, it may be necessary to divide the total required control rod adjustment between the left and the right wings (Ref 27-11-0 A/T).
(f)
Either shorten right tab rod set or lengthen left tab rod set or a combination of both to obtain the required amount of tab rod change from Fig. 503. Shorten or lengthen aileron tab rods per steps (2) (b) 1) or (2) (b) 2).
(g)
With aileron indexes aligned, measure and record the tab trailing edge mismatch with the lower aileron surface by using a straightedge or aileron tab alignment protractor positioned at the rod attach points.
NOTE: Verify that the tab trailing edge moves in the direction required. For correcting excessive forces right the trailing edge should move downward on the right aileron or upward on the left aileron or a combination of the two.
(4) After tab rods are adjusted and with aileron indexes aligned in the rigged position, at the midspan of the tab, measure its trailing edge with respect to lower surface of aileron. The tab shall be within -0.01 to +0.15 inch of aileron tabs with nonadjustable control rods, or +0.05 to +0.09 on aileron tabs with adjustable control rods.
500
27-09-400 Page 518 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/92
7. Speed Brake Rolloff Discrepancy Correction
A. If a speed brake discrepancy is reported, the spoiler pickups and speed brake symmetry should be checked. Refer to Adjust Spoiler Actuator Input Lever, 27-61-0, in Spoiler Control System -A/T.
8. Rudder Trim Discrepancy Correction
A. If a rudder trim discrepancy is reported the input to the main rudder power control unit should be checked. Refer to Adjust Input to Rudder Power Control Unit, in 27-21-0, Rudder and Rudder Trim Control System - A/T.
Jun 20/90 27-09-400 Page 518A/518B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
B. If slight rudder trim input is consistently required (.2 to .3 units) and system has been checked and found correctly rigged, recenter rudder trim as follows:
(1)
Set rudder trim knob at position required for straight flight (within .2 to .3 unit range).
(2)
Turn on hydraulic systems A and B.
WARNING: ACTIVATION OF HYDRAULIC SYSTEMS MAY ALSO ENERGIZE OTHER SYSTEMS THAN RUDDER. TO AVOID INJURY TO PERSONNEL, OR DAMAGE TO EQUIPMENT, ISOLATE OR TAG SYSTEMS AS REQUIRED. ENSURE ALL CONTROL SURFACES ARE CLEAR OF OBSTRUCTIONS BEFORE APPLYING POWER.
(3)
Loosen two tail cone index plate bolts.
(4)
Reposition index plate so that both sides of rudder trailing edge are within width of tab on index plate.
(5)
Tighten index plate bolts.
(6)
Set rudder trim knob to zero.
(7)
Adjust main and standby power control units input to align rudder with new index position (Ref Adjust Input to Rudder Power Control Unit and Adjust Input to Standby Rudder Actuator, 27-21-0, Adjustment/Test.
9. Rudder Standby Power Discrepancy Correction
A. If a rudder standby power discrepancy is reported, check input to rudder standby power control unit (Ref Adjust Input to Standby Rudder Actuator, 27-21-0, Adjustment/Test.
10. Elevator Power Off Discrepancy Correction
A. If an elevator power off discrepancy is reported, check elevator tab rigging (Ref Adjust Elevator Tab Pushrods, 27-31-0, Adjustment/Test.
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 1(38)
