(i)  
Restore airplane to normal hydraulic configuration and provide elevator systems A and B hydraulic power (Ref 27-31-0).

(j)  
Measure tab positions. Check that both tabs are faired with their respective elevator within 0.03 inch.

501 
Feb 20/93  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-0 Page 525 

(5)  Test Manual Mode Operation
(a)  
Remove elevator systems A and B hydraulic power (Ref 27-31-0).

(b)  
Check that horizontal stabilizer B dimension is set at 41.57 士0.05 inches.

(c)  
Set mach trim actuator in null position (Ref 27-31-0 MP).

(d)  
Check, as follows, that control columns and control wheels are without interference. 1) Move column repeatedly fore and aft between stops and simultaneously move control wheel repeatedly left and right between stops.

2)  Hold control wheel left against stop and move column fore and aft between stops.
500 
27-31-0 Page 526  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Oct 20/84 

3) Hold control wheel right against stop and move column fore and aft between
stops.
4)  Hold column full forward and move control wheel left and right between stops.
5)  Hold column full aft and move control wheel left and right between stops.
(e)  Measure elevator and elevator tab deflections with captain's control column at extremities of travel. 1) With bubble protractor attached to captain's control column, move control
column aft until column stops are contacted and hold while measuring. Right elevator trailing edge shall deflect 14.60 +0.30/-0.85 inches up from index mark on tail cone. Tab trailing edge shall deflect 0.92 +0.10/-0.14 inch down from elevator trailing edge for airplanes with metal-fiberglass elevators and 0.89 +0.10/-0.14 inches down for airplanes with composite elevators.
NOTE:  A hand assist at the elevator surface may be required to obtain a true deflection.
2)  Check that captain's control column position is aft of vertical 7 degrees minimum (Fig. 501).
3)  With bubble protractor still attached, move captain's control column forward until stops are contacted and hold while measuring. Right elevator trailing edge shall deflect 10.55 +0.60/-0.60 inches down from index mark on tail cone. (Hand assist may be required). Tab trailing edge shall deflect 1.03 士0.10 inches up from elevator trailing edge for airplanes with metal-fiberglass elevators and 1.06 士0.10 inches up for airplanes with composite elevators.
4)  Check that captain's control column position is forward of vertical 19.8 degrees minimum.
5)  Check that total travel of captain's column determined by adding values in steps 2) and 4) above is 28.4 degrees minimum.
(6)  Test Power Mode Operation
(a)  
Set horizontal stabilizer B dimension at 41.57 士0.05 inches.

(b)  
Set mach trim actuator in null position (Ref 27-31-0 MP).

(c)  
Provide elevator systems A and B hydraulic power (Ref 27-31-0).

(d)  
Shake captain's control column lightly fore and aft to ensure that system is centered, and release.

(e)  
With bubble protractor attached to captain's control column, check that captain's column position is 6.9士0.8 degrees forward of vertical.

(f)  
With bubble protractor attached to first officer's control column, check that control column position is 6.9士0.8 degrees forward of vertical.

(g)  
While moving captain's control column slowly between forward and aft stops, check for possible interference in system. Column operation should be smooth and free of any sudden buildup or irregular column forces.

(h)  
Move captain's control column approximately 2 degrees in forward direction and release. Check that right elevator trailing edge aligns with index mark on tail cone within 0.12 inch. Then move control column about 2 degrees aft and release. Check that right elevator trailing edge aligns with index mark within 0.12 inch. In both cases, tab shall be aligned with elevator within 0.07 inch.

(i)  
Shake control column lightly fore and aft to ensure system is centered. Check that right elevator trailing edge aligns with index mark on tail cone within 0.06 inch.

(j)  
Apply masking tape on tail cone along direction of right elevator trailing edge travel.

NOTE:  Elevator travel measuring tool may be used in lieu of tape method.

(k)  
Shake captain's control column lightly fore and aft to ensure that system is centered, and release.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 2(72)