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Autoslats
If the FLAP/SLAT handle is set in the 0° to 13° flap takeoff range, airspeed 240 KIAS or less, and either of the two stall warning computers detect that an approach-to-stall, the slats will extend automatically from the mid-sealed to extended position. When the approach-to-stall condition ceases to exist, the slats will retract automatically to the mid-sealed position. The slat DISAGREE and AUTO lights will illuminate upon autoslat extension.  The autoslat system automatically undergoes a self test whenever takeoff flaps/slats are selected. When the flap handle is moved from 0° RET to the takeoff range, the slats will extend from the retracted position through the mid-sealed position. While the slats are at the extended position, the slat DISAGREE and AUTO lights will be on. If the AUTO SLAT FAIL light also illuminates, an invalid test is indicated. The AUTO SLAT FAIL light can be reset and the test reaccomplished by cycling the FLAP / SLAT handle to 0° RET and back to flap takeoff range.
Post Stall Pusher System
Whenever a stall condition is detected by both stall detection systems and slats are fully extended, the control columns will be abruptly moved forward, the STICK PUSHER PUSH TO INHIBIT glareshield annunciator lights will illuminate, and the autopilot, if engaged, will disconnect.  The post stall pusher system will keep forward pressure on the control columns until either the stick shaker system is shut off, the G-force is reduced to between +0.65G to +0.50G, or the post stall pusher system is turned off by pushing either of the STICK PUSHER PUSH TO INHIBIT glareshield annunciator lights.  In addition, the stick pusher may be manually overridden by pulling aft on the control column. However, if stall persists and aft pressure is released, the stick pusher will again force the column forward. The STALL INDICATION FAILURE light will illuminate any time the post stall pusher system is shut off via pushing either glareshield annunciator lights or by reduction in G forces. The PUSH TO INHIBIT glareshield annunciator lights will go off whenever the system is automatically disengaged or whenever either glareshield annunciator light is pushed.
On some aircraft, after the PUSH TO INHIBIT light has been pressed, the pusher remains inhibited. On these aircraft, the STALL INDICATION FAILURE light remains on until the pusher is reset by maintenance.
On some aircraft, after the PUSH TO INHIBIT light has been pressed, the pusher will reset after the stall condition is removed. On these aircraft, the STALL INDICATION FAILURE light goes out when the pusher is automatically reset.

Continental
Rev. 12/01/00 #29 Flight Manual
Stall Protection System Self-Test
A switch on the overhead panel provides the capability of testing each detection system individually. The stall warning test may be performed at any flap/slat configuration on the ground or inflight.  Switch position 1 or 2 tests the ability of each computer to actuate both stick shakers, both stall recognition speakers, and annunciator lights.  Any failure in angle-of-attack, flap or slat inputs or faults within a single computer will inhibit all stall warning outputs on the affected side and turn on the STALL INDICATION FAILURE light. Stabilizer input faults will not inhibit the stall warning outputs but will turn on the STALL INDICATION FAILURE light to illuminate and inhibit only the recognition speakers. On the ground, stall warning system comparators are armed and most system failures will be detected and indicated by the STALL INDICATION FAILURE light prior to takeoff. If one of the detection systems malfunctions in flight, causing the STALL lights and/or stall recognition speakers to come on at full intensity, the STALL lights can be dimmed by placing the STALL TEST switch to either SYS 1 or SYS 2. The STALL TEST switch is normally at OFF at all times except during stall indication test or isolating malfunctioning system.
FLIGHT CONTROLS

FLIGHT CONTROLS - CONTROLS AND INDICATORS LATERAL
CONTROL AND TRIM

 

MD-80
Continental
Rev. 12/01/00 #29 Flight Manual

FLIGHT CONTROLS - CONTROLS AND INDICATORS LONGITUDINAL
CONTROL AND TRIM

FLIGHT CONTROLS - CONTROLS AND INDICATORS DIRECTIONAL
CONTROL AND TRIM

 

MD-80
Continental
Rev. 12/01/00 #29 Flight Manual

FLIGHT CONTROLS - CONTROLS AND INDICATORS SPOILER /
SPEEDBRAKE SYSTEM

FLIGHT CONTROLS - CONTROLS AND INDICATORS FLAP / SLAT
SYSTEM

MD-80 Rev. 12/01/00  #29 Continental Flight Manual

FLIGHT CONTROLS - CONTROLS AND INDICATORS MACH TRIM AND
STALL WARNING

FLIGHT CONTROLS - MAJOR COMPONENT LOCATION
MD-80
Continental
Rev. 12/01/00 #29 Flight Manual

FLIGHT CONTROLS - FUNCTIONAL SCHEMATIC STALL PROTECTION
SYSTEM

FLIGHT CONTROLS - FUNCTIONAL SCHEMATIC FLIGHT HYDRAULICS
　
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