(b)
Ensure rigging pin A/S-13 is installed and that trim roller is seated in cam detent.
(c)
Tighten left cables AA and AB to tension specified in figure 402.
(d)
Remove rigging pin A/S-13.
(e)
Rotate captain's aileron control wheel through several complete cycles.
(f)
Check cable rigging by reinserting rigging pins A/S-1, A/S-lA and A/S-13.
(g)
Check that cable tension i s within values specified in figure 402.
(h)
Remove all rigging pins.
(i)
Install turnbuckle locking clips.
(22)
Test aileron control wheel drum. Refer to Aileron Control Wheel Drum - Adjustment/Test.
(23)
Adjust and test roll force transducer and aileron force transducer. Refer to Chapter 22, Autopilot.
(24)
Close lower nose compartment access door.
500
27-11-51 Page 412 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 01/73
506
Aug 15/73 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-51 Page 413
500
27-11-51 Page 414 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/72
AILERON CONTROL WHEEL DRUM - ADJUSTMENT/TEST
1. Aileron Control Wheel Drum Test
A. Equipment and Materials
(1)
Control Column Protractor Assembly-4MIT65B80307-1 (Preferred) or F52485-500 (Optional) which is used with the following adapters:
(a)
Control Wheel Protractor Mount-F72790
(b)
Forward Thrust Lever Protractor Adapter-F72952-2
(2)
Torque and Force Test Control Wheel Adapter-F72867-1
B. Prepare for Test
(1)
Install protractor and protractor mount on first officer's aileron control wheel.
(2)
Remove medallion and install control wheel torque and force test adapter on captain's aileron control wheel (Fig. 501).
(3)
Ensure aileron trim control wheel is in neutral (zero) position.
C. Test Aileron Control Wheel Drum
(1) Using control wheel torque and force test adapter, measure force required to manually rotate captain's aileron control wheel clockwise and counterclockwise from neutral. If adapter is not available, apply force tangentially to captain's control wheel at a 6.5-inch radius.
(a)
Measure force required to rotate control wheel clockwise until ailerons begin to move. Force required shall not exceed 192 pound-inches torque or 29.5 pounds.
(b)
Continue rotating control wheel to 20 degrees from neutral. Force required shall not exceed 220 pound-inches torque or 33.8 pounds.
(c)
Continue rotating to 40 degrees. Force required shall not exceed 256 pound-inches torque or 39.4 pounds.
(d)
Continue rotating to 75 degrees. Force required shall not exceed 310 pound-inches torque or 47.7 pounds.
(e)
Repeat steps (a) thru (d) in a counterclockwise direction.
542
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-51 Page 501
G03742
Control Wheel Torque Wrench Adapter 500
27-11-51 Figure 501 Aug 15/68
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(2)
Measure corresponding movement of captain's and first officer's aileron control wheels.
(a)
Rotate captain's aileron control wheel clockwise through full travel.
(b)
Check that first officer's and captain's aileron control wheels have rotated a minimum of 105 degrees clockwise.
(c)
Repeat procedure in counterclockwise direction from neutral.
(3)
Measure relationship of aileron control wheel movement as compared with aileron surface deflection.
(a)
Rotate captain's aileron control wheel 87 degrees minimum counterclockwise from neutral.
(b)
Check that left aileron moves up and right aileron moves down within limits specified in figure 502.
(c)
Rotate captain's aileron control wheel 87 degrees minimum clockwise from neutral.
(d)
Check that left aileron moves down and right aileron moves up within limits specified in figure 502.
D. Restore Airplane to Normal
(1)
Close lower nose compartment access door.
(2)
Remove protractor and protractor mount from aileron control wheel.
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