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TROUBLE PROBABLE CAUSE ISOLATION PROCEDURE REMEDY
The test indicator does not spin Shaker does not shake P5-18 stall warning module Defective synchro on airflow sensor Defective synchro in flap position transmitter Open circuit in airplane wiring P5-18 stall warning module Defective shaker motorOpen circuit in airplane wiring Check continuity between pins 4, 5, and 6 of D365. Check continuity between pins 7, 8, and 9 of D365 Check continuity between pins 4, 5, and 6 of D229. Check continuity between pins 7, 8, and 9 of D229 Check continuity between the following: Pin 16 (D213) to pin 5 (D365) Pin 17 (D213) to pin 6 (D365) Pin 18 (D213) to pin 4 (D365) Pin 8 (D365) to pin 4 (D229) Pin 7 (D365) to pin 5 (D229) Pin 9 (D365) to pin 6 (D229) Pin 7 (D229) to pin 24 (D213) Pin 8 (D229) to pin 22 (D213) Check continuity between pin 5 (D213) and pin A (D281), pin B (D281) and airplane ground Replace module Replace airflow sensor if necessaryReplace the transmitter if necessary Repair wiring Replace module Replace shaker Establish continuity
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C. Airplane Condition: Airplane on ground, No. 1 engine running, switch (S1) in NORMAL position.
TROUBLE PROBABLE CAUSE ISOLATION PROCEDURE REMEDY
OFF indicator does not go off See like trouble in par. B No ground at pin 12 (D213) while engines are on Check for continuity between pin 12 (D213) and pin C (D422) M119 engine No. 1 cutout switch. Check for ground at pin A (D422) See par. B Establish continuity. Replace the cutout switch if necessary
D. Airplane Condition: Airplane in air, switch (S1) in normal position. NOTE: Perform trouble shooting on the ground.
TROUBLE PROBABLE CAUSE ISOLATION PROCEDURE REMEDY
Shaker shakes during normal flight or at incorrect airplane speed Refer to probable cause for trouble “OFF indicator does not turn on when the master test switch (P2-1) is in TEST position” in par. B. TROUBLE chart Angle of airflow sensor may be out of alignment or bent Flap position transmitter out of alignment See par. B Check and assure correct installation Check and assure proper installation
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
STALL WARNING SYSTEM - ADJUSTMENT/TEST
1. Stall Warning System Test
A. Equipment and Materials
(1)
Portable Calibrator - F72786-101 or -1 [for CONRAC sensor vane, part number 10-60878-( )]
NOTE F72786-101 replaces F72786-1 for future procurement.
(2)
Adapter Kit Assembly - F72786-183 [for Rosemount sensor vane, part number 10-62047-( )] -183 adapter used in conjunction with -101 calibrator makes a -181 calibrator which can be used on Conrac and Rosemount sensor vanes.
B. Prepare Stall Warning System for Test
(1)
Apply external electrical power to airplane.
(2)
Ensure that circuit breakers on P6 and P18 circuit breaker panels are closed and position LIGHTS switch on P2 circuit breaker panel to DIM.
C. Test Stall Warning System
(1) Perform confidence test.
(a)
Check that OFF light on stall warning module is illuminated.
(b)
If MASTER CAUTION lights are illuminated, press and release either light to reset master caution circuit. MASTER CAUTION lights shall extinguish.
(c)
Deleted
(d)
Hold stall warning module switch in TEST position. Check that the following occurs: 1) Stall warning module OFF light extinguishes. 2) MASTER CAUTION and OVHD annunciator lights shall be disregarded. 3) Test indicator on stall warning module shall spin at a minimum of two
revolutions per second.
4) Control column shaker operates.
(e)
Release switch and allow switch to return to NORMAL position. Check that the following occurs: 1) Stall warning module OFF light illuminates.
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