follow-up cam, you must make the cam link shorter. 2) Turn the sleeve clockwise to make the cam link shorter.
(e)
Put the flap control lever in the 5-unit detent to extend the flaps.
(f)
Put the flap control lever in the UP detent to retract the flaps.
(g)
Stop for 2 minutes, then do this task: "Hydraulic System B Depressurization" (Ref 27-51-00/201).
(h)
Make sure you can install the rig pin F-1 freely.
1) If you cannot install the rig pin freely, do the cam link adjustment again.
(i)
Tighten the checknuts and install the lockwire.
(j)
Make sure the threads are engaged in the limits.
(10)
Remove the rig pin F-1.
S 865-016
(11)
Do this task: "Hydraulic System B Pressurization" (Ref 27-51-00/201).
S 865-017
(12)
Extend and retract the flaps 5 times:
(a)
Put the flap control lever in the 40-unit detent to extend the flaps.
(b)
Put the flap control lever in the UP detent to retract the flaps.
S 095-015
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A 737-300/400/500MAINTENANCE MANUAL
S 865-018
(13)
Stop for 2 minutes, then do this task: "Hydraulic System B Depressurization" (Ref 27-51-00/201).
S 835-019
(14)
Make sure that you can easily install the rig pin F-1 in the flap control unit.
(a)
If you cannot easily install the rig pin, adjust the trailing edge cam link again.
S 415-020
(15) Install the lower pan on the flap control unit.
TASK 27-51-79-725-021
3. Functional Test - Flap Load Limiter Solenoid Valve
__________________________________________________
A. References
(1)
24-22-00/201, Manual Control
(2)
27-51-00/201, Trailing Edge Flap Systems
B.
Access
(1)
Location Zone
101, 102 Control Cabin
205 Electronic Compartment
C.
Procedure
S 865-022
(1)
Do this task: "Supply Electrical Power" (Ref 24-22-00/201).
S 865-023
(2)
Make sure these circuit breakers are closed:
(a)
P6 Panel
1) FLAP LOAD RELIEF
2) LANDING GEAR LIGHTS
(b)
P18-2 Panel
1) NO. 1 AIR DATA COMPUTER
S 865-024
(3)
Do this task: "Hydraulic System B Pressurization" (Ref 27-51-00/201).
(4)
Put the flap control lever in the 40-unit detent.
S 865-026
(5)
If the airplane is on jacks, compress the right main gear strut approximately 5 inches to the ground position.
S 865-025
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A
737-300/400/500MAINTENANCE MANUAL
S 725-027
(6) Move the flap load limiter test switch on the equipment bay light panel in the electronics compartment to the SYSTEM TEST position. (a) Make sure the flaps retract to the 30-unit position.
S 725-028
(7) Release the test switch. (a) Make sure the flaps extend to the 40-unit position.
S 725-033
(8) With the flap load limiter test switch in the test position, operate the test function of the left (number one) air data computer: (a) AIRPLANES WITH AN AIR DATA COMPUTER WITH A ROTARY TEST SELECT SWITCH AND A PRESS TO TEST SWITCH; Put the test switch to FUNCTION and push and hold the PRESS-TO-TEST switch.
(b) (c) (d) AIRPLANES WITH AN AIR DATA COMPUTER WITH A TEST/HISTORY TOGGLE SWITCH; Hold the TEST/HISTORY switch in the test position.Make sure the flaps retract to the 30-unit position and the system test light does not come on.AIRPLANES WITH A FLAP LOAD RELIEF LIGHT; Make sure the light comes on.
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