TROUBLE  PROBABLE CAUSE  ISOLATION PROCEDURE  REMEDY 
One light does not illuminate on press to test or in any switch position Neither light illuminates on press to test or in valve transit One light does not agree with switch position  Defective lamp Defective lamp base Defective wiring Defective valve control circuit  Check continuity of lamp. IF -No Continuity -Continuity OK - Check for defective lamp base Check for continuity with lamp installed between base terminals 1 and 2, and 1 and 3 with light cover normal and between terminals 1 and 4 with light cover depressed. IF -No Continuity Continuity OK Remove receptacle D462 from P5-11 module and check for dc power at pin 18. IF -No Power Power OK - Check for continuity between pin 29 and ground. IF -No Continuity Continuity OK Check if valve position agrees with switch position. IF - Replace lamp Replace lamp base Replace P5-11 module Repair wiring between circuit breaker and receptacle Repair wiring between receptacle and ground Replace P5-11 module 

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WING THERMAL ANTI-ICING SYSTEM - ADJUSTMENT/TEST
EFFECTIVITY
Airplanes without Wing TAI System Ground Operation Capability
1.  Wing Thermal Anti-Icing System Test
A.  General
(1)  Testing of the wing TAI system is separated into three parts; an electrical control and indicating system test, a duct pressure and leakage test, and a ground operational test.
(a)  
The electrical control test is effective in establishing correct functioning of the electrical control components, circuit continuity, and valve motor operation.

(b)  
The duct leakage test is effective in establishing that all joints are properly made and that allowable leakage is distributed throughout the system. Leakage should not be present in any localized area to an extent capable of creating operating pressure or temperature hazards.

(c)  
The ground test is effective as a system confidence check. The test is accomplished with either the engines or the APU running. All functions are performed in the control cabin and requires no access to ducts or system components.

B.  Electrical Control and Indicating System Test
(1)  Equipment and Materials
(a)  Temp-Cal Probe Heater BH3884-40 (attachment to Jet-Cal engine analyzer) or H294 Temp-Cal Thermal Switch Tester or H394 Temp Cal Tester with adapter cable BH405 BH24944 Heater Probe Kit (basic P/N)
NOTE:  This kit is necessary to use the testers listed above. There are different dash number kits for specific airplane model and tester combinations. Please consult with supplier.
Howell Instruments 3479 West Vickery Blvd. Fort Worth, Texas 76107
(2)  Prepare to Test Control and Indicating System
(a)  
Connect external power and energize 115v ac transfer buses No. 1 and 2, and  28v dc T/R bus No. 1.

(b)  
Check that the following circuit breakers on the P18-3 anti-ice and rain circuit breaker panel are closed. 1) ENG 1 & WING VALVE (C146) 2) ENG 2 & WING VALVE (C147) 3) ENG 2 (C148) 4) ENG 1 & WING CONTROL (C149)

(c)  
On pilot's overhead panel (P5), press to test wing anti-ice left and right valve open lights for operation.

NOTE: Each light will come on when pressed and go off when released.
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(3)  
Test Valve Control Circuit

(a)  
Open ENG 1 & WING VALVE (right wing valve) circuit breaker.

(b)  
Position the wing TAI control switch to ON or hold in GRD-TEST or TEST position as applicable and check that left valve open light glows brightly for 1 to 3 seconds and then continues to glow dim as long as switch is held or ON, and left wing anti-ice valve opens.

NOTE:  Right valve open light will glow brightly as long as control switch is held or ON as applicable.

(c)  
Position wing TAI control switch to OFF and check that left valve open light glows brightly for 1 to 3 seconds and then goes off and left wing anti-ice valve closes.

NOTE: Right valve open light will go off when control switch is released.
　
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