(5)
Continue start procedure per paragraph A. steps (7) through (13).
(6)
Retard thrust lever to IDLE on engine used for cross-start after engine started attains idle rpm or, if desired, retard thrust lever to IDLE anytime after engine being started attains starter cutout speed (35% to 40% N2).
10. New Engine Operating Procedure
A. Check thrust reverser operation (Ref 78-32-01 A/T).
WARNING: DO NOT OPERATE ENGINE IN REVERSE THRUST MODE WITH ENGINE SIDE COWLS INSTALLED AND OPEN. DAMAGE TO ENGINE OR INJURY TO PERSONNEL MAY OCCUR.
B. Operate New Engine
(1)
Operate engine at idle rpm for 5 minutes or until rpm stabilizes.
(2)
Adjust engine oil pressure. See paragraph 11.
(3)
With engine at idle; check engine bleed ducts and all joints for leaks or other defects. Diffused leakage is permitted at a joint; however, jet blasts are not allowable. There shall be no evidence of defective ball joints or connections.
(4)
Purge air from engine fuel control by accelerating engine four or five times between idle and 90% N2 rpm or until fuel flow indication and throttle response is normal and return thrust lever to idle.
(5)
Slowly accelerate engine and record N1 speed at which anti-surge bleed valves close. Bleed closing is indicated by a sudden increase in EPR.
(6)
Slowly decelerate engine from a stabilized point just above bleed valve closing and record N1 speed at which anti-surge bleed valves open. Bleed valve opening is indicated by a sudden decrease in EPR.
NOTE: Engine prior to P&WA SB 5425 bleed configuration will indicate EPR increment of approximately 0.05 at constant power lever position during anti-surge bleed actuation. Engine incorporating P&WA SB 5425 bleed configuration will indicate smaller EPR shift of approximately 0.02.
(7)
Check bleed valve opening and closing per Anti-Surge Bleed Chart (Fig. 207).
(8)
Increase power to 85% N2 rpm. Position engine inlet anti-ice switch to ON and observe EPR decrease. EPR should decrease approximately 0.05 units. After 15 to 20 seconds, position inlet anti-ice switch to OFF.
(9)
With power still at 85% N2, check fuel system as follows:
(a)
Operate engine from its own tank for 25 to 30 seconds, with both fuel pumps OFF, cross-feed valve closed, center tank fuel pumps OFF. (Fuel warning light on glare shield annunciator panel will come on.)
(b)
Monitor engine fuel flow at center panel. A deterioration in fuel flow is cause for suspecting a partially clogged fuel line and should be investigated.
(c)
Turn on fuel pumps. For additional fuel system checks, refer to Chapter 28, Fuel.
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Oct 20/84 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 71-09-100 Page 225
Note: If you must use the fuel boost pumps in the center tank, you must have a maintenance person or observer in the flight compartment to continuously monitor the LOW PRESSURE lights. Turn the applicable fuel boost pump to the OFF position if the LOW PRESSURE light for the center tank stays on.
(10)
Retard thrust lever to idle position. Check that antisurge bleed valves open as scheduled in Fig. 207.
(11)
Check fuel deicing system operation as follows:
(a)
Move fuel heat switch on forward overhead panel to ON position.
(b)
Observe a drop in engine N2 rpm as the valves open.
(c)
After approximately 60 seconds, the valve should automatically close. Observe that N2 rpm returns to its original value. For additional fuel deicing system checks, refer to Chapter 73, Engine Fuel Heating (Deicing) System.
(12)
Observe the generator drive oil temperature gage on the forward overhead panel for a small rise in temperature.
(13)
Turn on the generator of the applicable engine and position the AC meter switch to this generator. Observe that the generator is producing 115 volts and 400 cps.
(14)
Turn off and on the applicable System A hydraulic pump switch and observe that System A depressurizes and repressurizes on the hydraulic system pressure gage on the First Officer's panel.
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