S 416-017

 (5)  
Close the access panel 315A (AMM 06-09-05/201).

 S 866-018

 (6)  
Remove electrical power if it is not necessary (AMM 24-22-00/201).

 TASK 22-12-01-206-019
 3. EAS Mechanical Linkage Full Inspection (Fig. 601)
______________________________________
 A. General
_______
 (1)  This procedure is for a full inspection of the worn areas. To do this check, you have to remove the EAS mechanical linkage. Usually you use this procedure when you do the overhaul of the EAS mechanical linkage.
 B. Standard Tools and Equipment
 (1)  Micrometer
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 22-12-01
 ALL  ú ú 01 Page 604 ú Jun 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

INDEX NO.  PART NAME  DIM.  DESIGN LIMITS  WEAR LIMITS  REPLACE WORN PART  REPAIR WORN PART  REPAIR INSTR 
DIAMETER  DIM. WEAR MITTED PER- DIA MAX CLEAR-ANCE
MIN  MAX 
1  BOLT  OD  0.2485  0.2495  0.2480  0.0030  X 
OUTPUT CRANK  ID  0.2495  0.2500  0.2515  2 
2  BOLT  OD  0.2485  0.2495  0.2480  0.0030  X 
BEARING  ID  0.2497  0.2500  0.2515  3 
3  BOLT  OD  0.2485  0.2495  0.2480  0.0030  X 
BEARING  ID  0.2497  0.2500  0.2515  3 
4  BOLT  OD  0.2485  0.2495  0.2480  0.0030  X 
INPUT ARM ELEVATOR SERVO  ID  0.2495  0.2505  0.2515  4 

REFER TO VENDOR MANUAL FOR REPAIR INFORMATION.
REPLACE THE BEARING WHEN THE INTERNAL BEARING CLEARANCE IS LARGER THAN THE MAXIMUM VALUE OF 0.0004.
REFER TO OVERHAUL MANUAL FOR REPAIR INFORMATION.

EAS Mechanical Linkage Wear Limits
Figure 601 (Sheet 2)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 22-12-01
 ALL  ú ú 01 Page 605 ú Jun 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
B88642
A
747-400 MAINTENANCE MANUAL
 (2)  Vernier Caliper
 C. Procedure
 S 026-001
 (1)
Remove the parts that are necessary for a full inspection.

 S 226-002

 (2)  
Examine the parts:

 (a)  
Use a micrometer or a Vernier Caliper to measure the parts.

 (b)  
Compare the dimensions you measured with the permitted dimensions that are shown in Fig. 601.

 (c)  
Repair or replace the parts that are out of the tolerance.

 S 426-003
 (3)  Install the parts.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 22-12-01
 ALL  ú ú 01 Page 606 ú Jun 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 ELEVATOR AUTOPILOT SERVO ELECTROHYDRAULIC SERVOVALVE
____________________________________________________ AND SOLENOID VALVE - MAINTENANCE PRACTICES
__________________________________________
 1.  General_______
 A.  This procedure contains three tasks. The first task is for the removal of the Electrohydraulic Servovalve (EHSV) and the Solenoid Valve. The second task is for the installation of the EHSV and the solenoid valve. The third task is for the operational test of the EHSV and the solenoid valve.
 B.  This procedure applies to the Electrohydraulic Servovalve (EHSV) and the Solenoid Valve. The valves are on the left, center, and right of the EAS. Each EAS has one EHSV and two Solenoid Valves. The three EASs are on the aft side of the stabilizer hinge bulkhead. You can get access to the EASs through the 315A access door in the tail cone.
 TASK 22-12-02-002-051
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機(jī)維護(hù)手冊(cè) 空調(diào) AUTO FLIGHT(98)