(4)
When the ENG ANTI-ICE switch is moved to OFF, the blue COWL VALVE OPEN light comes on bright to indicate valve in transit, then goes off to indicate valve closed.
(5)
When a pressure of 65 |3 psi is sensed by the TAI pressure switch, the switch is activated causing the amber COWL ANTI-ICE warning light to come on.
(6)
When a temperature of 825 |20°F is sensed by the TAI overheat switch, the switch is activated causing the amber COWL ANTI-ICE warning light to come on.
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A 737-300/400/500MAINTENANCE MANUAL
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A
737-300/400/500MAINTENANCE MANUAL
(7) If the engine is not running and the ENG ANTI-ICE switch is set to ON, the COWL VALVE OPEN light will come on bright and will stay on. Under these conditions, if the pneumatic system is pressurized, the COWL VALVE OPEN light may become dim momentarily.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
INLET COWL ANTI-ICING SYSTEM - TROUBLE SHOOTING
_______________________________________________
1. General_______
A. The Inlet Cowl Anti-Icing System uses engine hot bleed air from the 5th and 9th-stages of the high pressure compressor (HPC) to maintain ice-free inlet cowl surfaces during flight and ground operations.
B. The system consists of ducting, a dual purpose pressure regulating and shutoff valve, an anti-icing distribution spray ring located in the lip of the inlet cowl, and an exhaust port located at the 6 o'clock position on the inlet cowl.
C. Each engine anti-icing system operates independently. Each anti-ice valve is pneumatically operated, and is controlled electrically by a switch on the pilot's overhead panel P5-11. The associated valve position indicator lights and warning lights are located adjacent to the switches.
D. The inlet cowl anti-ice system is dependent upon the operation of the engine bleed air distribution system, since the cowl anti-ice valve is pneumatically operated. An improperly operating engine bleed air distribution system could cause the inlet cowl anti-ice system to operate improperly. If the engine bleed air distribution system is suspected to be causing cowl anti-ice system faults, trouble shoot per MM 36-11-05/101.
E. All trouble shooting procedures are based on the following assumptions:
(1)
Double failures do not exist.
(2)
The faulty system was fully operational prior to the fault indication with all equipment properly installed.
(3)
All relevant circuit breakers were checked.
(4)
All applicable airplane/engine operating procedures were accomplished.
(5)
The airplane is on the ground, it has been shut down in accordance with normal operating procedures and all power is off.
(6)
Fault was accurately described.
(7)
Generally, electrical wiring is satisfactory and power is available.
F. If the corrective action in the procedure does not correct the problem, check wiring using the wiring diagram. Prior to trouble shooting, check master Dim and Test circuits to ensure panel lights are operable.
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