737-300 400 500 AMM 飞机维护手册 自动飞行 AUTOFLIGHT 2(13)

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BOLT  OD  0.2485  0.2495  0.2481 
 X 
 
 
2  LEVER  ID 0.2495  0.2505  0.0000  0.0020 
 0.2535  3 0.0040  X  1  0.0000  0.0011 
BOLT  OD  0.2485  0.2495  0.2481 
 X 
 
 
3 BEARING  ID  0.2497  0.2500  0.0002  0.0015 
 0.2530  3 0.0035  X 
BOLT  OD  0.2485  0.2495  0.2481 
 X 
 
 
4 LEVER  ID  0.2495  0.2505  0.0000  0.0020 
 0.2535  3 0.0040  X  1  0.0000  0.0011 
BOLT  OD  0.2485  0.2495  0.2481 
 X 
 
 
5 BEARING  ID  0.2497  0.2500  0.0002  0.0015 
 0.2530  3 0.0035  X 
BOLT  OD  0.2485  0.2495  0.2481 
 X 
 
 
6 LEVER  ID  0.2495  0.2505  0.0000  0.0020 
 0.2535  3 0.0040  X  1  0.0000  0.0011 
BOLT  OD  0.2485  0.2495  0.2481 
 X 
 
 
7 BEARING  ID  0.2497  0.2500  0.0002  0.0015 
 0.2530  3 0.0035  X 
BOLT  OD  0.2485  0.2495  0.2481 
 X 
 
 
8 LEVER  ID  0.250  0.251  0.0005  0.0025 
 0.255  3 0.005  X  2  0.0000  0.0011 
BOLT  OD  0.2485  0.2495  0.2481 
 X 
 
 

OBTAIN BUSHING. BORE HOLE (0.3756 INCH DIAMETER MAXIMUM) TO ATTAIN 0.0002 TO 0.0011 INCH INTERFERENCE FIT. REAM BUSHING TO 0.2495/0.2500 INCH DIAMETER.
OBTAIN BUSHING. BORE HOLE (0.3756 INCH DIAMETER MAXIMUM) TO ATTAIN 0.0002 TO 0.0011 INCH INTERFERENCE FIT. REAM BUSHING 0.250/0.251 INCH DIAMETER.
THE TOTAL DIAMETRICAL CLEARANCE OF LOCATIONS (1 + 2 + 3 + 4 + 5 + 6 + 7 + 8) MUST NOT EXCEED 0.0225 INCH.
ALL DIMENSIONS ARE IN INCHES
A737-300/400/500MAINTENANCE MANUAL
A/P Elevator Actuator Linkage Wear Limits
Figure 601 (Sheet 3)

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 22-11-26
ALL  úú 01 Page 604 ú Nov 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 SPOILER POSITION SENSOR - REMOVAL/INSTALLATION
______________________________________________
 1.  General_______
 A.  This procedure contains two tasks. The first is the removal of the spoiler position sensor. The second is the installation of the spoiler position sensor.
 B.  The spoiler position sensors are installed on spoilers No. 2 and 7. You will extend the spoilers to access the sensor, but they must be lowered to do the adjustment.
 TASK 22-11-27-024-001
 2.  Spoiler Position Sensor Removal_______________________________
 A.  References
 (1)  
12-31-01/201, General Zone Diagram

 (2)  
24-22-00/201, Electrical Power Control

 (3)  
27-61-00/201, Spoiler Control System

 B.  Access
 (1)  Location Zone
 102 Control Cabin
 307 Left Wing Spoiler
 407 Right Wing Spoiler

 C.  Equipment
 (1)  
Flight Spoiler Ground Lock F80017-33 (Preferred) or F80017-23 (Alternate) (Use with Chamfered Flight Spoiler Clevis)

 (2)  
Flight Spoiler Ground Lock C27047-16 (Use with Rounded Flight Spoiler Clevis)

 D.  Prepare for the Removal
 S 864-002
 (1)  Supply electrical power (Ref 24-22-00/201).
 S 864-003
 WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL
_______ SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SLATS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
 (2)  
Supply system A and B hydraulic power (Ref 27-61-00/201).

 S 864-004

 (3)  
Put the FLT CONTROL A switch, on the forward overhead panel (P5), to the ON position.
　
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