501  Turbine Section Water Wash Probe Installation 
May 15/79  Figure 703 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  71-00 Page 707 

(7)  
Make certain there is no N2 rotation. Engage starter and allow engine to reach full starter rpm. Do not exceed starter duty cycle.

(8)  
Inject water into combustion section of engine through probes, at 40- to 45-psi pressure, for 30 seconds.

(9)  
Turn water off and release starter.

(10)
Allow engine to drain for approximately 5 minutes.

(11)
Repeat steps (7) thru (10) two more times.

(12)
Remove probes and reinstall igniter plugs, packing holders, and igniter plug leads (Ref 74-21-21).

(13)
Check fuel control PB sense line water trap for moisture.

(14)
If engine is to remain inoperative for a period of 4 hours or more after washing, start engine and run at idle for 5 minutes.

NOTE:  Under very cold and windy weather conditions, even if water/alcohol mixture is used, there is a high probability of ice formation in the engine in less than 4 hours if an engine run-up is not made following wash to purge/evaporate residual water.

(15)
Shut down engine and recheck fuel control PB sense line water trap for condensation.

501 
71-00 Page 708  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/84 

F.  Clean Engine - Detergent Wash Procedure (Optional)
CAUTION:  THE DETERGENT IS HIGHLY CORROSIVE TO ACOUSTICAL LININGS AND ALUMINUM STRUCTURAL SURFACES. ANY DETERGENT SPLASHED SURFACE MUST BE RINSED WITH WATER IMMEDIATELY TO PREVENT CORROSION DAMAGE.
NOTE:  For the detergent wash method, the engine must be prepared for internal gas path cleaning by blocking or disconnecting ports and bleed lines to prevent detergent wash solution from entering certain compartments.
(1)  
Conduct engine performance check, if desired.

(2)  
Shut down engine and allow at least 30 minutes to elapse before spraying compressor.

(3)  
During the cooling period, the following preparation tasks can be accomplished: 

(a)  
Open side cowl panel.

NOTE:  If Zok 27 detergent is used, the nose cowl and nose dome do not have to be removed because Zok 27 is non-corrosive.

(b)  
Remove engine nose cowl (AMM 71-11-31) and nose dome (AMM 71-11-51).

(c)  
Disconnect Pt2, Ps3, and Ps4 lines to pressure ratio bleed control at engine.

(d)  
Disconnect Pt2 and Pt7 lines to engine pressure ratio transmitter at low point on engine.

(e)  
Disconnect PB sense line to fuel control unit at engine.

(f)  
If installed, disconnect CSD pressurization line at 6th-stage bleed duct.

(g)  
Disconnect thrust reverser and hydraulic reservoir pressurization line at engine.

(h)  
Disconnect and cap generator cooling inlet (aft) supply duct.

(i)  
Disconnect engine ignition leads and deactivate circuit breaker.

NOTE:  It is not necessary to cap off fittings at disconnected lines providing these fittings have been offset to prevent water entering the line or valve.

(j)  
Check for proper silicone oil level in the fuel control burner pressure (Pb) bellows (Ref. P&WA 73-21-1, Removal/Installation).

(4)  
Prepare 20 gallons of detergent solution composed of 20 percent detergent (4 gallons) and 80 percent water of drinking purity.

(5)  
Check that start lever is in CUTOFF position.

(6)  
Check that all anti-ice and fuel heater valves are in CLOSED position, except engine bleed valve.

(7)  
Provide a handheld hose and nozzle, or attach water wash rig (P&WA 33382) to inlet guide vanes and connect supply hose (Fig. 701). If engine is to be cleaned during freezing temperature conditions, add sufficient alcohol to the wash water to ensure no ice forms that could cause damage to the engine. See Fig. 702 for recommended minimum water-alcohol mixtures. However, a mixture of up to 50% alcohol may be used.

501 
May 01/03  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  71-00 Page 709 

WARNING:  IF HOSE IS HANDHELD, OPERATOR MUST STAY AT LEAST 3 FEET FROM ENGINE INLET AT APPROXIMATELY WAIST-HIGH LEVEL OR BELOW.
CAUTION:  SPRAYING WATER INTO GAS PATH BEFORE ENGINE HAS COOLED CAN RESULT IN DAMAGE TO ENGINE PARTS DUE TO THERMAL SHOCK.
(8)  
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護(hù)手冊 動力裝置 POWER PLANT(21)