+ 0.05 psi (334 ± 3 knots).
CAUTION:  DO NOT EXCEED 6 PSI (474 KNOTS) TO THE PITOTS AT ANY TIME DURING THIS TEST. OVERPRESSURE MAY DAMAGE FEEL COMPUTER.
(u)
Check that system B on the autopilot control panel is selected.

(v)
Repeat steps (h) thru (n) above.

(w)
Check that total displacement of steps (j) and (l) is 2.43 + 0.39 inches.

(x)
Turn off hydraulic system A flight controls switch.

(y)
Repeat steps (h) thru (n) above.
(aa) Check that total displacement of steps (j) and (l) is 3.07 + 0.49 inches.
(ab) Reduce 2.8 psi (334 knots) pitot pressure to zero.

545 
27-31-131 Page 412  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/92 

S.  Restore Airplane to Normal
(1)  
Ensure that all tools used during testing are removed.

(2)  
Remove all masking tape.

(3)  
Remove seals from drain holes in each vertical fin pitot tube.

CAUTION: MAKE SURE SEALS ARE REMOVED FROM PITOT TUBES.

(4)  
Remove pressure gage lines from systems A and B drain lines located below feel computer.

(5)  
Install drain plugs on system A and B drain lines located below feel computer.

(6)  
Remove regulated air pressure lines from both vertical fin pitot tubes.

(7)  
Open the vertical gyro circuit breaker and wait 10 minutes before remounting gyro.

(8)  
Close all circuit breakers opened during testing.

(9)  
Install access panels.

(10)
Restore airplane to normal hydraulic configuration (Ref 27-31-0).

(11)
Service hydraulic reservoirs, if required (Ref Chapter 12 Hydraulic Servicing).

(12)
Remove electrical power if no longer required.

545 
Aug 15/78  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-131 Page 413 

ELEVATOR FEEL COMPUTER - INSPECTION/CHECK
1.  General
A.  This data consists of illustrations and wear limits charts. There will be no procedure given in this section for gaining access to, or removing and replacing the components after inspection for wear. Refer to Component Removal/Installation for this information.
2.  Elevator Feel Computer Wear Limits

G10232 G10245G10254
500  Elevator Feel Computer Wear Limits 
Aug 15/68  Figure 601 (Sheet 1)  27-31-131 
Page 601 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Elevator Feel Computer Wear Limits  500 
27-31-131  Figure 601 (Sheet 2)  May 15/68 
Page 602 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500  Elevator Feel Computer Wear Limits 
Aug 15/68  Figure 601 (Sheet 3)  27-31-131 
Page 603 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

INDEX NO.  PART NAME  DIM  DESIGN LIMITS  WEAR LIMTS  REPLACE WORN PART  REPAIR WORN PART  REPAIR INSTR. 
DIAMETER  MAX WEAR DIM.  MAX DIAM CLEAR-ANCE
MIN  MAX 
1  ARM  ID  0.2495  0.2505  0.2535  0.0040  X  1 
BOLT  OD  0.2485  0.2495  0.2481  X 
2  BEARING  ID  0.2497  0.2500  0.2530  0.0035  X 
BOLT  OD  0.2485  0.2495  0.2481  X 
3  BEARING  ID  0.2495  0.2500  0.2530  0.0035  X 
BOLT  OD  0.2485  0.2495  0.2481  X 
4  BUSHING  ID  0.2495  0.2505  0.2525  0.003530  X 
BOLT  OD  0.2485  0.2495  0.2481  X 
5  ARM  ID  0.3762  0.3767  0.3785  0.0040  X  2 
BUSHING  OD  0.3754  0.3761  0.3745  X 
6  ARM  ID  0.2495  0.2505  0.2535  0.0040  X 
BOLT  OD  0.2485  0.2495  0.2481  x 
7  BEARING  ID  0.1895  0.1900  0.1945  0.0050  X 
BOLT  OD  0.1870  0.1895  0.1866  X 
8  CRANK  ID  0.1895  0.1905  0.1950  0.0055  X 
BOLT  OD  0.1870  0.1895  0.1866  X 
9  ARM  ID  0.1895  0.1900  0.1945  0.0050  X  3 
　
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 飛行操縱 FLIGHT CONTROLS 2(116)