(2)
Position FLT CONTROLS A and B switches on forward overhead panel to ON.
(3)
Close all flight control circuit breakers on P 6 circuit breaker panel.
(4)
Pressurize hydraulic reservoirs as required. Refer to 29-09-300.
500
27-11-0 Page 204 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
AILERON AND AILERON TRIM CONTROL SYSTEM - ADJUSTMENT/TEST
1. Aileron and Aileron Trim Control System Adjustment
A. General
(1)
When installing new cables, the initial cable tension should be double the applicable values shown in Fig. 501. After the system has been cycled 20 times, the cable tension must be readjusted to correct values.
(2)
Some airplanes have on the aileron control wheels a foil marker calibrated in degrees of control wheel rotation. These foil markers are for flight crew use. Do not use these foil markers when adjusting or testing the aileron control system.
NOTE: Control wheel neutral position for maintenance purposes is determined by rotating the control wheel left and right in decreasing amounts until the neutral position can be determined by feel.
(3)
The aileron trim control system must be properly adjusted prior to checking or adjusting the aileron control system.
(4)
The aileron and aileron trim control systems are properly adjusted when the following results are obtained: (Refer to Fig. 501 for rigging pin locations and cable tension requirements.)
WARNING: ALL FLIGHT CONTROL SYSTEMS ARE FULLY POWERED. CHECK TO ENSURE THAT PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF ALL CONTROL SURFACES BEFORE TURNING HYDRAULIC POWER ON.
(a) Aileron Trim Cables ATA and ATB
1) With the aileron trim control knob indicator in the zero trim position (Fig. 502), rigging pin A/S-13 shall fit without binding in aileron trim gearbox. Cable tension shall be within limits shown in Fig. 501. If discrepancies exist, adjust the cable turnbuckles in forward cargo compartment as described in par. C.(1).
506
Nov 01/75 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-0 Page 501
G03249
Aileron System Rigging Pin Location 500
27-11-0 Figure 501 (Sheet 1) May 15/81
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Aileron System Rigging Pin Location
Apr 01/97 Figure 501 (Sheet 2) 27-11-0
Page 503
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G03257 G03268 G03276G03278
Aileron Trim Control Unit 500
27-11-0 Page 504 Figure 502 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/68
506 Aileron Trim Control Unit
May 01/76 Figure 502 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-0 Page 505
Aileron Control Wheel Adjustment 500
27-11-0 Figure 503 (Sheet 1) Aug 15/68
Page 506
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Aileron Control Wheel Adjustment
Aug 15/69 Figure 503 (Sheet 1) 27-11-0
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(b)
Aileron Control Bus Cables ACBA and ACBB
1) With rigging pin A/S-1A installed and straightedge bearing on the captain's and first officer's control wheel upper ends (Fig. 503), one end of first officer's control wheel may be out of alignment a maximum of 0.20 inch. Cable tension on cables ACBA and ACBB must conform with values shown in Fig. 501. If discrepancies occur, adjust the cables in the lower nose compartment as described in par. C.(2).
(c)
Aileron Control Cables AA and AB
1) With rigging pins A/S-1, A/S-1A, and A/S-13 installed, the roller of the aileron trim mechanism should be seated on the cam, and rigging pins A/S-3 shall fit without binding. Cable tension on cables AA, AB (left), AA, AB (right) must conform to values shown in Fig. 501. If discrepancies occur, adjust the cables in the lower nose compartment as described in par. C.(3).
(d)
Aileron Power Control Unit Valve Rods
1) With aileron trim control wheel in neutral, captain's and first officer's aileron control wheels in neutral, and hydraulic power ON, rigging pin A/S-4 shall fit without binding. If discrepancies exist, adjust power control unit valve rods as described in par. C.(5). 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(57)
