(b)
Put the alternate flap arm switch to ARM. 1) Make sure the STANDBY HYD LOW PRESSURE light comes on. 2) Make sure the standby hydraulic pump starts. 3) Make sure the STANDBY HYD LOW PRESSURE light is off.
(c)
Put the alternate flap control switch to DOWN.
(d)
Make sure the leading edge flaps and slats fully extend.
(e)
Put the alternate flap control switch to OFF.
(f)
Make sure the leading edge flaps and slats do not move.
S 792-043
(13)
Make sure the hydraulic fittings of the shutoff valve do not have a leak.
S 862-040
(14)
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a)
P6-2 Circuit Breaker Panel
1) ALT TE FLAP DRIVE AC
(15)
Release pressure from the hydraulic systems (Ref 27-81-00/201).
(16)
Install lockwire on the alternate flap arm switch.
(17)
Remove electrical power if it is not necessary (Ref 24-22-00/201).
S 862-041
S 432-042
S 862-039
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27-81-91
ALL ú ú 02 Page 208 ú Nov 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
LEADING EDGE AUTOSLAT SYSTEM - DESCRIPTION AND OPERATION
________________________________________________________
1. General (Fig. 1)_______
A. The leading edge autoslat system automatically extends the leading edge slats from the intermediate extend position to the full extend position to provide additional lift without changing trailing edge flap position.
B. The leading edge slats are normally at the intermediate extend position during takeoff. When the airplane reaches a predetermined angle of attack, the autoslat system extends the slats to the full extend position. The slats automatically retract to the intermediate extend position when the angle of attack is reduced.
C. The autoslat system consists of two angle of airflow sensors, two identical autoslat computers, and a dual autoslat control valve. The computers receive signals from the angle of airflow sensors, the nose gear and main gear ground sense relays, the auto speedbrake module, and the flaps greater than 10 degrees switch. The computers supply signals to the autoslat control valve, to the flight controls module to indicate faults, to the flap/slat indication module, and to the landing gear transfer relay. Each computer continuously monitors the other.
D. On airplanes with 65-52818-5 autoslat computers, there is an alpha VANE light on the face of each computer. This light is not connected and may be disregarded.
E. The Power Transfer Unit (PTU) will supply hydraulic pressure for autoslat operation if system B pressure is lost. The landing gear bypass valve will decrease the hydraulic flow for landing gear retraction during autoslat operation if either the PTU or the landing gear bypass valve is energized.
2. Angle of Airflow Sensors________________________
A. The angle of airflow (AOA) sensor for each system provides a signal which represents airplane angle of attack. The sensors are located on the outside of the fuselage below each pilot's side window. Each sensor consists of an aerodynamic vane which pivots to position three internal synchro transmitters. In flight, the vane assumes a position parallel to the airflow passing over it. Each sensor provides outputs to the stall warning system, the autoslat system, and the autopilot system.
B. A heater built into the sensor vane prevents icing. The case of the sensor is heated to prevent condensation inside. The heaters are powered through the ALPHA VANE HTR L and R circuit breakers on the P18-3 panel and are controlled by the PITOT STATIC HEAT A and B switches on the P5 overhead panel (Ref 30-31-00 D&O).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH AUTOSLAT ú
27-83-00
COMPUTER P/N 65-52818 ú CONFIG 1 ú 02 Page 1 ú Mar 15/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
3. Autoslat Computers
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本文链接地址：737-300 400 500 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 6(106)
