(2)  
Airplane Control Surfaces Protractor - F52485-500, F70044-500 or 4MIT65B80307-1 as applicable

(3)  
Protractor Adapter (Thrust Lever) - F72952-2

(4)  
Hydraulic test bench capable of delivering 20 gpm at 3000 psi

(5)  
One air pressure source with regulated outlet, pressure of which can be accurately set at pressures between 8 and 80 psig and flow of 15 lbs per minute at 4.5 psig. All pressures are to be monitored by pressure gages with an accuracy of + 1.0%. Shutoff valves must be provided on source side of all gages.

C.  Prepare to Test Landing Gear Warning System
(1)  
Jack airplane until all tires clear ground (Ref Chapter 7, Jacking Airplane).

(2)  
Provide electrical power.

(3)  
Check that external hydraulic pressure supply is connected but do not pressurize hydraulic system A (Ref 29-11-0 MP).

(4)  
On airplanes with inflatable-type wheel well seal, pressurize pneumatic manifold.

(5)  
Check that LANDING GEAR LIGHTS; LEVER LATCH AND PRESS WARN; LANDING GEAR TEST; AURAL WARNING; ENGINES - EPR WARNING; ENG 1 EPR & L.G. WARNING; ENG 2 EPR & L.G. WARNING circuit breakers on the P6 panel are closed.

501 
Feb 20/91  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  31-26-0 Page 503 

G42634
Thrust Lever Position Measurement  501 
31-26-0Page 504   Figure 501 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/89 

(6)  
Check that press-to-test and all indicator light circuit breakers on circuit breaker panel P6 are closed.

(7)  
With thrust levers fully retarded, place protractor with adapter in position on thrust levers and set protractor to 0 degrees (Fig. 501).

(8)  
Advance both thrust levers approximately 20 degrees from idle.

(9)  
Place landing gear control lever in DN position.

(10)
Install gear ground lockpins in all landing gear and check that shock struts are fully extended.

Feb 20/91 31-26-0 Page 504A/504B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

(11)
Increase hydraulic system A pressure to 3000 psi (Ref 29-11-0).

(12)
Extend trailing edge flaps to the 1-unit position (Ref Chapter 27, Trailing Edge Flap System).

D.  Test Landing Gear Warning System
(1)  Test Throttle Versus Landing Gear Warning
(a)  
Remove the ground lockpin from the nose landing gear.

(b)  
Place landing gear control lever UP and retract nose landing gear to locked position.

(c)  
Place landing gear control lever to OFF. Check that the red gear light goes off and the warning horn remains silent. 

(d)  
Retard No. 1 throttle toward idle. Check that a continuous warning horn sounds and the red gear light illuminates before throttle lever reaches 5.0 degrees from idle stop.

(e)  
Place throttle lever on idle stop. Check that horn continues sounding and red gear light remains illuminated.

(f)  
Retract flaps to full UP position. Make sure that the horn stops.

(g)  
Fully extend flaps. Make sure that a continuous warning horn sounds at all flap settings.

(h)  
Retract the flaps to the 1 unit position. Check that the horn continues to sound and the red gear light remains on.

(i)  
Advance throttle lever No. 1. Check that the horn stops and the red gear light goes off before the lever reaches 13.5 degrees from the idle stop.

(j)  
Retard the throttle lever to idle. Check that the continuous horn sounds and the red gear light illuminates.

(k)  
Press the horn cutout switch on the aisle stand. Check that the horn stops and the red gear light remains illuminated.

(l)  
Advance throttle lever No. 1 greater than 13.5 degrees from the idle stop and return to idle stop position. Check that a continuous warning horn sounds and the red gear light goes off then back on.

(m)
Repeat steps (d) and (e), then steps (i) and (j) using throttle lever No. 2 in lieu of No.

1.

(n)  
Extend the nose gear. Check that the red gear light goes off and the horn stops.

(o)  
Advance throttle lever No. 2 greater than 13.5 degrees from the idle stop. Check that the horn remains silent.

(p)  
Repeat steps (a) thru (e), (i) thru (j), (n) and (o) using left main gear in lieu of nose gear.

(q)  
Repeat steps (a) thru (e), (i) thru (j), (n) and (o) using right main gear in lieu of nose gear.
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 通訊描述和操作(60)