(1)
27-31-17/201, Elevator Pitot-Static System
(2)
30-31-00/501, Pitot-Static Tubes, Temperature Probe and Alpha Vane Anti-Icing System
C.
Access
(1)
Location Zone
706 Vertical Stabilizer
(2)
Access Panels
9525 Access Door Between Fin
D.
Procedure
S 424-005
(1)
Install the pitot tube:
(a)
Make sure there is good electrical ground.
(b)
Make sure you clean the area inside the vertical fin contacted by the mounting bolts.
(c)
Set the pitot tube, gaskets and wedge on the vertical fin.
(d)
Apply a bead of adhesive RTV 174 around the tube tongue.
NOTE: You can use the adhesive in the gasket between the pitot
____ tube and the wedge. Do not use adhesive in the gasket between the wedge and the vertical fin.
(e)
Tighten the bolts.
(f)
Remove the unwanted adhesive.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-31-94
ALL ú ú 03 Page 402 ú Mar 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
(g) Remove the protective cap and attach the pitot air connector to the pitot tube.
CAUTION:_______ YOU MUST PUSH THE ELECTRICAL CONECTOR STRAIGHT ON WHEN YOU CONNECT THE ELECTRICAL CONNECTOR TO THE PITOT HEATER PINS. THIS IS TO PREVENT THE SOCKET ENLARGEMENT.
(h) (i) Connect the electrical connector D692 or D694.Remove the DO-NOT-MOVE tags and set the PITOT STATIC switches to ON.
(2) S 414-004Install the access panel 9525.
(3) S 714-008Do this task: "System Test - Elevator Pitot Static System" (Ref 27-31-17/201).
(4) S 714-006Do this task: "Pitot-Static, Temperature Probe and Alpha Vane Anti-Ice System Test" (Ref 30-31-00/501).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-31-94
ALL ú ú 01 Page 403 ú Mar 15/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
1.
2.
3.
A
737-300/400/500MAINTENANCE MANUAL
STALL WARNING SYSTEM - DESCRIPTION AND OPERATION
________________________________________________
General (Fig. 1)
_______
A. Two 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 operates independently and includes an angle of airflow sensor, a flap position transmitter, a digital stall warning computer, a self-test switch, and a control column shaker.
B. The angle of airflow (AOA) sensor detects the airplane angle of attack and the flap position transmitter senses the position of the trailing edge flaps. These signals are passed to the stall warning computer along with information about airplane flight status. 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 warning occurs is also influenced by engine speed, airspeed, and any asymmetry between leading edge and trailing edge flaps.
Angle of Airflow Sensor
_______________________
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. 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.
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 D&O).
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(22)
