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STALL WARNING SYSTEM - DESCRIPTION AND OPERATION
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General
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A. Two independent stall warning systems alert the pilots of an approaching stall condition. The warning is accomplished by vibrating the pilots' control columns. This warning is also used if airspeed falls too low. Each stall warning system and includes an angle of airflow sensor, a flap position transmitter, a stall management computer, a self-test switch, and a control column shaker.
B. The angle of airflow sensor senses the airplane angle of attack and the flap position transmitter senses the position of the trailing edge flaps. The stall management computer receives these signals and signals from other flight systems. At predetermined combinations of flap position and airplane angle of attack, the computer outputs a stall warning signal to activate the control column shaker. The point at which the stall warning signal occurs is also influenced by engine speed, airspeed, and flap asymmetry.
C. The stall management computers activate the autoslat control valve to extend the LE slats from the intermediate extend position to the full extend position (Ref 27-83-00).
D. The stall warning computers provide information to the Electronic Flight
Instrument System (EFIS) for the pitch limit display function.Angle of Airflow Sensor
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A. The Angle of Airflow Sensor can also be identified as the Stall Warning Sensor or as the Sensor for the Sensor Instl - Stall Warning.
B. 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. The sensor consists of an aerodynamic vane which pivots to position three internal synchro transmitters. In flight, the vane takes a position parallel to the airflow passing over it. The sensor provides separate outputs to the stall management computer and to the autopilot.
C. 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).
Flap Position Transmitter
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A. The flap position transmitter for each system provides a signal which represents trailing edge flap position. The transmitters are located on the wing rear spars between the two outboard flap tracks. Each transmitter provides separate outputs to the stall warning system, the autopilot system, and the pilots' trailing edge flaps position indicator.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STALL MANAGEMENT ú
27-32-00
COMPUTER P/N 65-52822 ú CONFIG 2 ú 04 Page 1 ú Mar 15/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
FLAP POSITION
TRANSMITTER
SEE A
STALL WARNING TEST MODULE
SEE D
ANGLE OF MAIN EQUIPMENT AIRFLOW CENTER SENSOR
SEE C TRANSMITTER
CONTROL SEE B
COLUMNS
SEE E
FWD INBD WING REAR SPAR
A
STALL MANAGEMENT COMPUTER
SEE F
FWD
B
FWD
____LEFT ANGLE OF AIRFLOW
NOTE: SENSOR AND FLAP POSITION TRANSMITTER SHOWN. RIGHT
C
SENSOR AND TRANSMITTER
SIMILAR.
Stall Warning System Component Location
Figure 1 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STALL MANAGEMENT ú
27-32-00
COMPUTER P/N 65-52822 ú CONFIG 2
ú 01 Page 2
ú Mar 15/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
NO. 1 NO. 2 STALL WARNING TEST BITE INSTRUCTIONS
D SMC MAINTENANCE CONTROL PANEL
COLUMN CONTROL CAPTAIN'S CONTROL COLUMN SHAKER CONTROL COLUMN FIRST OFFICER'S YES MENU NO ON/ OFF
COLUMN CONTROL SHAKER BOEING SERIAL NO. PART NO. 65-52822 STALL MANAGEMENT COMPUTER
E F
Figure 1 (Sheet 2) Stall Warning System Component Location
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