(b)  
Check that time for flaps to extend is 35 (+ 5) seconds.

NOTE:  Operating time should be measured from start of flap motion in up position until downstop on number 4 bal1 screw nut is 1.50 (+ 0.20) inches from downstop on the jackscrew.

(c)  
Position flap control lever in FLAP UP detent.

(d)  
Check that time for flaps to retract is 35 (+ 5) seconds.

(4)  Test trailing edge alternate flap drive operation.
(a)  
On circuit breaker panel (P6-2):
1) Check that TE ALT FLAP DRIVE MOTOR circuit breaker is closed.
2) Check that FLAP VALVES circuit breaker is closed.

(b)  
Position alternate flap switch at ARM.

NOTE:  Actuation of alternate flap switch to ARM energizes standby hydraulic pump motor.

(c)  
Move flap control lever to FLAP DOWN detent.

NOTE:  Flap control lever is moved to FLAP down position as a standard procedure to minimize load on flap hydraulic motor when hydraulic system A is pressurized.

(d)  
Actuate alternate flap drive switch to DOWN position. Hold switch in this position until trailing edge flap motion stops.

CAUTION:  LEADING EDGE CONTROL SURFACES WILL EXTEND. ENSURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR.
NOTE:  Extension of trailing edge flaps is controlled by limit switches.
(e)  
At number 4 jackscrew, check that clearance between downstop on ball screw nut and downstop lug on jackscrew is between 2 and 3 turns.

(f)  
Actuate alternate flap drive switch to UP position. Hold switch in this position until trailing edge flap motor stops.

NOTE:  Retraction of trailing edge flaps is controlled by limit switches.

(g)  
At number 4 jackscrew, check that clearance between upstop on ball screw nut and upstop on jackscrew yoke is between 0.40 and 0.71 inches.

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27-51-201 Page 510  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/73 

(5)  
Check flap control lever operating force.

(a)  Check that tangential force required to move flap control lever between detents does not exceed 2.5 pounds, excluding cable cushion. Measure force at end of lever.

(6)  
Test operation of leading edge flaps and slats (Ref 27-81-0, Leading Edge Flaps and Slats

- Adjustment/Test).

(7)  
Test operation of flap takeoff warning switch (Ref 31-26-23, Flap Takeoff Warning Switch).

(8)  
Test operation of flap landing warning switch (Ref 31-26-12, Flap Landing Warning Switch).

(9)  
Test operation of Mach trim switch (Ref 22-21-31, Mach Trim Flap Switch).

(10)
Test operation of flaps 10-degree switch (Ref 27-88-21, Flaps 10-Degree Switch).

(11)
Restore airplane to normal configuration.

(a)  
Remove system A hydraulic power (Ref 27-51-0).

(b)  
Remove electrical power if n longer required.

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Feb 15/78  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-201 Page 511 

TRAILING EDGE FLAP CONTROL VALVE -REMOVAL/INSTALLATION
1. General
A.  The trailing edge flap control valve is mounted on the flap control unit aft of the leading edge flap and slat control valve. This procedure provides instructions for replacement of the trailing edge flap control valve. The valve has a solenoid valve attached. The procedure in par. 2 provides instructions for replacement of the control valve and solenoid valve as a unit. The procedure in par. 3 provides instructions for replacement of the solenoid valve only.
2.  Removal/Installation Trailing Edge Flap Control Valve
A.  Equipment and Materials
(1)  
Hydraulic Fluid -BMS 3-11 (Ref 20-30-21)

(2)  
Skydrol Assembly Lube - MCS352 (Ref 20-30-21)

(3)  
Rigging Pin - F-l, 0.311 +0.000/-0.002 inch diameter, 2.35 +0.06 inches long (MS20392-4)

NOTE: Rigging pin is a part of kit F70207-61 or -84.

(4)  
Grease - MIL-G-23827 (Ref 20-30-21)

(5)  
Sealant - BMS 5-79, Type B (Ref 20-30-11)

B.  Prepare Trailing Edge Flap Control Valve for Removal
(1)  
Pressurize hydraulic system A (Ref 27-51-0 MP).

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

(3)  
Depressurize hydraulic system A and depressurize hydraulic reservoirs (Ref 27-51-0 MP).

(4)  
Remove lower pan from flap control unit (Fig. 401).

(5)  
Install rigging pin F-1 through follower arm and valve cam.

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Feb 20/88  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-212 Page 401 
　
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