531  Leading Edge Flap and Slat Control System Component Location 
May 15/71  Figure 1 (Sheet 2)  27-81-0 
Page 3 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Leading Edge Flap and Slat Control System Component Location  500 
27-81-0  Figure 1 (Sheet 3)  Nov 15/68 
Page 4 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500  Leading Edge Flap and Slat Control System Component Location 
Nov 15/68  Figure 1 (Sheet 4)  27-81-0 
Page 5 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

E.  A standby hydraulic system is provided to extend the leading edge flaps and slats in the event hydraulic system A fails. The system is controlled by the alternate trailing edge flap switches on the overhead panel. Actuating the switches automatically pressurizes the standby hydraulic system. Pressurized fluid from the standby system is directed to the flap and slat actuators by a motor operated shutoff  valve in the standby system modular package. Fluid flow to the actuators is regulated by a flow limiting valve and a hydraulic fuse. The leading edge flap and slat control valve is bypassed during use of standby hydraulic power.
2.  Leading Edge Flaps
A.  Two Krueger type leading edge flaps are installed on each wing. The flaps are numbered 1 through 4 as shown on figure 1. Each flap is a machined aluminum casting containing integral ribs and stiffeners. Flaps 1 and 4 each have four gooseneck hinges and flaps 2 and 3 each have five gooseneck hinges which attach to fittings in the leading edge of the wing. A centrally located fitting is also provided on each flap for connecting the flap to a hydraulic actuator. A hinged fairing is installed on the trailing edge of flaps 1 and 4, and two fairings are installed on the trailing edge of flaps 2 and 3. Two linkages rotate the hinged fairing as the leading edge flap 1 or 4 extends. Three linkages rotate the two hinged fairings as the leading edge flap 2 or 3 extends. Each linkage consists of two pushrods and a differential bar attached to a bracket on the flap casting. One pushrod extends from the fairing to the differential bar and the other pushrod connects the bar to the fixed leading edge of the wing. When the leading edge flap retracts, the linkage folds the fairing inward against the flap. When the leading edge flap extends, the fairing also extends, allowing air to flow smoothly over the surface of the flap.
531 
27-81-0 Page 6  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 15/71 

3.  Leading Edge Slats
A.  Three leading edge slats are installed on each wing outboard of the engine. The slats are numbered 1 thru 6 as shown on Fig. 1. The slats consist of ribs attached to a beam, inner and outer clad aluminum skins, and a honeycomb trailing edge. A void between the inner and outer skins provides a path for thermal anti-icing. Anti-icing ducts installed in the slat leading edge connects with hot air supply lines through a telescoping tube. A three-position hydraulic actuator is attached at the center of all leading edge slats (1 thru 6). Each slat has two main tracks and two auxiliary tracks which ride on rollers in the wing leading edge. A third auxiliary track is installed at the outboard end of slats No. 1 and 6. Structural stops are provided in both the extended and retracted slat positions. The downstops are attached to the slat tracks and contact with track guides in the extended position. The upstops consist of three adjustable plates which contact with the slat beam when the slats are retracted. All slats (1 thru 6) are stabilized at the intermediate position by a torsion rod and support arm assembly attached to the front spar between the auxiliary slat tracks. In the fully extended position, the No. 1 and 6 slats do not extend as far as the other 4 slats.
3A.  Leading Edge Slat Aerodynamic Seal
A.  Wing leading edge aerodynamic seals are installed at cutouts in the wing fixed leading edge skin. The cutouts provide for attachment, actuation, and heating of leading edge slats. Seal curtains are located at slat main track and thermal anti-icing duct cutouts and seal doors are located at slat actuator and auxiliary track cutouts. When the leading edge slats extend, each seal rotates or slides downward sealing cutout and preventing airflow into fixed leading edge.
4.  Leading Edge Flap and Slat Control Valve
A.  A three-position control valve regulates operation of the leading edge flaps and slats (Fig. 1). The control valve is mounted on the trailing edge flap follow-up mechanism located in the right wheel well (Fig. 1.) The valve consists of a sliding piston enclosed in a valve housing. Drilled passages are provided in the valve housing for a pressure port, a return port, and two cylinder ports. A pushrod connects the control valve to the trailing edge flap follow-up mechanism. With the trailing edge flaps retracted, the control valve slide blocks flow of pressurized fluid to the leading edge flap and slat actuator extend ports. When the trailing edge flaps extend to the 0-to 1-unit position, pressurized fluid is ported through one of the cylinder ports to extend the leading edge flaps and to extend the leading edge slats to the intermediate position. When the trailing edge flaps reach the 10-unit position, pressurized fluid is ported through both control valve cylinder ports to fully extend all leading edge slats.
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(147)