(a)
Pressurize the hydraulic systems A and B (AMM 27-11-00/201).
(b)
Make sure that the FLT CONTROL A and B switches are ON.
(c)
Make sure the aileron trim switches are at the zero trim position.
(d)
Make sure the trim roller is against the cam detent.
(e)
Move the control wheel in the backlash band to put the aileron control wheels in the center.
NOTE: The center of the backlash band is the neutral position
____
of the control wheels.
(f) Make sure you can easily install or remove the rig pins A/S-1, A/S-1A, A/S-3, A/S-4 and A/S-15.
CONTROL WHEEL
TORQUE AND FORCE TEST ADAPTER (F72867)
Control Wheel Torque and Force Test Adapter
Figure 508
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737-300/400/500MAINTENANCE MANUAL
(g)
Make sure the ailerons align with the index marks on the wing structure (Fig. 506).
(h)
Make sure the distances between the lug of the top bus drum and stop bolts on the bottom drum are as specified (Fig. 505).
(i)
Make sure the index mark on the control wheel hub aligns with zero on the control column marker.
(j)
Operate the control wheel through a minimum of two cycles.
(k)
Make sure the aileron spring cartridge is not compressed.
(l)
Make sure the aileron spring cartridge can move freely.
F.
Put the Airplane Back to its Usual Condition
S 865-012
(1)
Release the pressure from hydraulic systems A and B
(Ref 27-11-00/201).
S 865-013
(2)
Remove electrical power is it is not necessary (AMM 24-22-00/201).
S 415-014
(3)
Close the access door.
TASK 27-11-00-735-002
3. System Test - Aileron and Aileron Trim Control System_____________________________________________________
A. Special Tools and Equipment
(1)
4MIT65B80307-1 - Control Surface Protractor
(2)
F72790 - Protractor Mount - Aileron Control Wheel
(3)
F80222-1 - Aileron Tab Alignment Protractor
(4)
F72867-1 - Adapter - Control Wheel Torque and Force Test
B.
Standard Tools and Equipment
(1)
Spring Scale - Capacity 0 to 150 pounds
(2)
Voltmeter - General Purpose VTVM (2 Necessary)
C.
References
(1)
AMM 22-11-25/501, Autopilot Aileron Actuator
(2)
AMM 27-11-00/201, Aileron and Aileron Trim Control System
(3)
AMM 27-51-00/501, Trailing Edge Flap System
D.
Access
(1)
Location Zone 101 Control Cabin, LH 102 Control Cabin, RH 306 Wing Trailing Edge Aileron and Control Tab, LH 406 Wing Trailing Edge Aileron and Control Tab, RH
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E. Prepare the Aileron and Aileron Trim Control System for Test
S 495-043
(1)
Install the control surface protractor and the protractor mount on the first officer's aileron control wheel.
S 865-021
(2)
Make sure the aileron trim system is at the center.
S 865-075
(3)
Make sure the outboard flaps are correctly adjusted, or must be extended 1 to 5 degrees to prevent possible deflection of point "A" (AMM 27-11-00, Fig. 506) on the wing structure (Ref. AMM 27-51-00/501 Trailing Edge Flap System).
S 865-019
(4)
Release the pressure from hydraulic systems A and B (AMM
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