(10)
Position flap control lever to FLAP UP detent.

(11)
After 2 minutes, remove system A hydraulic power (Ref 27-51-0).

(12)
Check that rigging pin F-1 fits freely in flap control unit. If not, repeat steps (2) through (11).

(13)
Install lower pan on flap control unit.

NOTE: No additional testing of control valve is required.
2.  Flap Load Limiter Solenoid Valve Test
A.  Test Flap Load Limiter Solenoid Valve
(1)  
Connect electrical power to the airplane.

(2)  
Close the flap load limiter circuit breaker on the P6 panel.

(3)  
Provide system A hydraulic power (Ref 27-51-0).

522 
Nov 15/79  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-212 Page 505 

(4)  Position flap control lever to the 40-unit detent. 
NOTE:  If airplane is on jacks, compress right-hand main gear strut approximately 5 inches to the ground position. 
(5) (6) (7) (8) (9)  Actuate the flap load limiter test switch on the equipment bay light panel in the electronics compartment to the SYSTEM TEST position, and check that the flaps retract to the approximate 30-unit position. Release test switch and check that flaps extend to the 40-unit position. Position flap control lever to the FLAPS UP detent to retract flaps. Remove system A hydraulic power (Ref 27-51-0). Disconnect electrical power. 

522 
27-51-212 Page 506  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Nov 01/74 

TRAILING EDGE FLAP CONTROL VALVE -APPROVED REPAIRS
1. General
A.  If a trailing edge flap control valve is found to indicate excessive internal leakage, the following procedure may be implemented with the valve installed on the airplane, to reduce the leakage by approximately half.
2.  Equipment and Materials
A. Rigging Pin - F-1, 0.311 +0.000/-0.002 inch diameter, 1.65 +0.06 inches long (MS20392-4)
NOTE:  Rigging pin is a part of kit F70207-61 or -84.
3.  Trailing Edge Flap Control Valve Internal Leakage Repair
A.  Provide system A hydraulic power (Ref 27-51-0 MP).
B.  Position flap control lever to 40-UNIT detent to extend trailing edge flaps.
C.  Remove system A hydraulic power (Ref 27-51-0 MP).
D.  Position flap control lever to FLAPS UP detent.
E.  Rotate sleeve 90 degrees (Fig. 801).
NOTE:  This action repositions the eroded metering edges of the flap valve slide with respect to the rectangular slots in the sleeve.
F.  Position flap control lever to 40-UNIT detent.
G.  Provide system A hydraulic power (Ref 27-51-0 MP).
H.  Position flap control lever to FLAPS UP detent to retract trailing edge flaps.
I.  Test trailing edge flap control valve.
(1)  
Position flap control lever to 40-UNIT detent and then to FLAP UP detent. Pause at  40-UNIT and FLAP UP detent to allow flap drive unit to respond. Repeat for five cycles.

(2)  
Position flap control lever to FLAP UP detent.

(3)  
After waiting 2 minutes, depressurize system A hydraulic power (Ref 27-51-0 MP).

(4)  
Remove lower pan from flap control unit.

(5)  
Check that rigging pin F-1 fits freely in flap control unit. If not, adjust trailing edge flap control valve (Ref 27-51-212 A/T).

(6)  
Install lower pan on flap control unit.

587 
Feb 20/88  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-212 Page 801 

G25466
Trailing Edge Flap Control Valve Repair  507 
27-51-212  Figure 801  Nov 15/78 
Page 802 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

FLAP POWER UNIT - ADJUSTMENT/TEST
1.  Flap Power Unit Test
A.  Prepare Flap Power Unit for Test
(1)  
Connect electrical power to airplane.

(2)  
Pressurize hydraulic system A (Ref 27-51-0, Maintenance Practices).

(3)  
Remove inboard flap track fairings (Ref 27-51-141).

(4)  
Check that the following circuit breakers on panel P6 are closed.

(a)  
TE AL FLAP DRIVE MOTOR

(b) 
 FLAP VALVES

(c)  
TE Flap Position INDICATION

B.  Test Flap Power Unit
(1)  
Position flap control lever in 1-unit detent, allow flaps to respond, then return flap control lever to FLAP UP detent.

(2)  
Check that both flap position indicator pointers point into the black UP area on the indicator dial. Also check that pointer tips are within 0.040 inch of each other.
　
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 3(63)