(2)  
On circuit breaker panel (P18-3) close the following circuit breakers.

(a)  
Engine 1 -ENG 1 AND WING ANTI-ICE VALVE and ENG 1 AND WING ANTI-ICE CONTROL.

(b)  
Engine 2 -ENG 2 AND WING ANTI-ICE VALVE and ENG 2 AND WING ANTI-ICE CONTROL.

(3)  
Gain access to valves by opening left and right engine cowl panels (Ref Chapter 71). Left and right anti-ice valves are respectively located at 11 o'clock and 1 o'clock. Nose cowl anti-ice valve is located at 4 o'clock.

B.  Test Engine and Nose Cowl Anti-Icing System
(1)  
Place ENG ANTI-ICE switch on pilot's overhead panel (P5-11) to ON position. All valves should open as indicated by the position indication on each valve. Engine 1 COWL VALVE OPEN, R VALVE OPEN and L VALVE OPEN indicator lights should illuminate bright during valve transit. Indicator lights should change to a dim condition when the valves reach the full open position.

(2)  
Visually check nose cowl anti-icing regulator (Thermostatic valve) failure indicating pin to verify that the valve is fully open. Scribed marks on the failure indicating pin are visible beyond the open position stop to give indication of regulator failure.

(3)  
With the regulator valve between 60 and 100oF the inboard scribe mark shall be within 0.040" to flush with end of open position stop screw, when a force of 1 to 2 lbs. is applied to the end of the pin. Regulator failure is indicated if the pin will not move, or if the inboard scribe mark moves inwards beyond the end of the open position stop screw.

(4)  
Place ENG ANTI-ICE switch to the OFF position. All valves should close as indicated by the position indication on each valve. Engine valve position indicator lights should illuminate bright during valve transit then go out and remain out as long as the valves are closed.

(5)  
If required, repeat steps (1) thru (4) for other engine.

C.  Restore Airplane to Normal Configuration
(1)  
Close engine cowl panels.

(2)  
Determine if electrical power is needed, if not, disconnect electrical power.

500 
Oct 20/85  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  75-11-0 Page 501 

ANTI-ICING AIR SYSTEM -INSPECTION/CHECK

1.  Periodic Inspection
A.  General
(1)  
These check procedures are a normal function of operating organizations. They consist of required checks and minor adjustments necessary on the JT8D engine air systems. The nature and conditions of engine operation determine the time interval between required checks.

(2)  
Engine compartment cleanliness is important because the extensive mass air flow tends to draw foreign objects into the engine. Thoroughly clean the entire engine compartment with a vacuum cleaner after completion of any work. Keep the compartment free of dirt, oil, and grease, and remove any small unused parts, such as nuts, washers, and pieces of lockwire. Immediately cover all apertures resulting from the disconnection of tubing or parts.

(3)  
Carefully check the air systems without dismantling to ensure that all connections are tight and free from leaks and that lines, tubing, and controls are secure.

500 
May 15/78  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  75-11-0 Page 601 

ENGINE ANTI-ICING SHUTOFF VALVE - REMOVAL/INSTALLATION
1. General
A.  There are two engine anti-icing shutoff valves on each engine. The valves are located at the 11 o'clock and 1 o'clock positions on the front fan case. Replacement procedure is the same for both valves.
2.  Remove Engine Anti-Icing Shutoff Valve (Engines before PWA SB 5872)
A.  Open applicable ENGINE AND WING ANTI-ICE VALVE and ENGINE AND WING ANTI-ICE CONTROL circuit breakers on P-18 circuit breaker panel.
B.  Disconnect electrical connector from valve (Fig. 401).
C.  Establish clip and bracket locations to facilitate installation.
D.  Remove three nuts and washers that secure anti-icing tube to engine.
E.  Remove nuts and bolts securing anti-icing valve support to front compressor case bracket per one of the following methods:
(1)  Remove bolts from front flange of anti-icing valve, remove support.
(a)  
Prior to P&WA SB 5666. Remove bolts, locknuts and washers.

NOTE:  Assembly prior to P&WA SB 3218 have key washers under boltheads. Straighten tabs of key washers and discard after bolts are removed.

(b)  
Incorporating P&WA SB 5666. Remove bolts, locknuts and washers. Remove bushing, using drift at each side of valve support.
　
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