(2)
Open all flight control circuit breakers on P6 circuit breaker panel.
(3)
Position No. 1 and No. 2 system B HYD PUMPS switches on forward overhead panel to OFF.
(4)
Position GRD INTERCONNECT switch on forward overhead panel to CLOSE.
(5)
To dissipate remaining hydraulic power, cycle captain's control wheel.
(6)
If any hydraulic connections are to be disturbed, depressurize hydraulic system A and system B reservoirs. Refer to 29-09-300, Hydraulic Reservoir Pressurization System -Maintenance Practices.
(7)
Install hydraulic module. See figure 201.
(a)
Disconnect electrical connector from spoiler shutoff valve at system A flight controls hydraulic module in left wheel well.
(b)
Disconnect electrical connector from spoiler shutoff valve system B flight controls hydraulic module in right wheel well.
(c)
Manually place override lever at both spoiler shutoff valves in position 2.
(d)
Install lock on each spoiler shutoff valve and insert attaching lockpins.
C. Restore Airplane to Normal
NOTE: Perform the following steps after completing speed brake system maintenance.
(1)
Remove locks from system s A and B flight controls hydraulic module shutoff valves and reconnect electrical connectors.
(2)
Position spoiler 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.
543
27-62-0 Page 204 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
SPEED BRAKE CONTROL SYSTEM - ADJUSTMENT/TEST
1. General
A. The speed brake control system provides a speed brake signal to the spoiler mixer and controls hydraulic system A pressure to the ground spoiler actuators. (See Spoiler Control System, 27-61-0.)
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.
B. Both the spoiler and speed brake systems must be in adjustment prior to testing either system.
C. The following conditions must be met before adjusting or testing the speed brake control system.
(1)
Aileron control system must be properly adjusted. Refer to 27-11-0, Aileron and Aileron Trim Control System - Adjustment/Test.
(2)
Wing trailing edge flaps must be properly adjusted. Refer to 27-51-0, Trailing Edge Flaps System - Adjustment/Test.
D. Throughout the speed brake control system maintenance practices, it is assumed that the weight of the airplane is supported by the landing gear. In this configuration the ground spoiler interlock valve is open, allowing the ground spoiler actuators to operate the ground spoilers. Unless specifically noted otherwise, the weight of the airplane on the landing gear may be simulated by opening the ground spoiler interlock valve as follows:
(1)
Detach the ground spoiler interlock valve cable from the right landing gear torsion link. Refer to 27-62-51 Ground Spoiler Interlock Valve Cable - Removal/Installation.
(2)
Manually move the valve lever to dimension B in figure 505.
(3)
After completion of test, return airplane to normal configuration as follows:
(a)
Attach the ground spoiler interlock valve cable to the right landing gear torsion link.
(b)
Adjust and test ground spoiler interlock valve cable. Refer to 27-62-51, Ground Spoiler Interlock Valve Cable - Adjustment/Test.
500
Aug 15/69 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-62-0 Page 501
G39052
Speed Brake Control System-Rigging Pin Location and Cable Tension 500
27-62-0Page 502 Figure 501 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 15/81
2. Speed Brake Control System Adjustment
A. General
(1) The speed brake control system will be properly adjusted when the individual components are adjusted to meet the following conditions. See figure 501 for rigging pin locations and cable tension requirements.
(a) Speed Brake Control Lever
1) With the speed brake control lever in the DOWN detent-rigging pin SB-1 fits freely. If not, this condition may be met by adjusting the lower control rod at the speed brake forward drum per paragraph 2.C.(1).
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 3(119)
