(b)
Pull the first officer's control column forward with the force gage until the control column starts to move.
(c)
Make sure the breakout force is 32.0-36.0 pounds (143-160 newtons).
(d)
Let the control columns go to the neutral position.
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S 825-011
(3) If the control columns do not have the above breakout forces, do the steps that follow to correct the breakout forces:
NOTE: These steps adjust the spring eyebolts.
____
(a) Adjust the locknut.
NOTE: One-half of a turn of the the locknut changes the
____ control column breakout force approximately 0.45 pound (2 newtons).
(b)
Make sure the difference in spring lengths is less than 0.04 inch.
(c)
Use the double twist method to put a lockwire on the locknuts.
F.
Put the Airplane Back to Its Usual Condition
S 085-012
(1)
Remove the force gage.
S 095-013
(2)
Remove the adapter equipment (if installed) for the control wheel.
S 435-014
(3)
Do the steps that follow to connect the aft end of the first officer's control rod to the elevator forward quadrant:
(a)
Install the bolt that holds the control rod to the crank and make sure the conditions that follow are correct: 1) You can install the bolt freely and easily. 2) You installed the bolt with the bolt head up.
(b)
Lift the crank to its initial position and tighten the bolts on the shaft of the elevator forward quadrant.
(c)
Do the adjustment for the elevator cables, if it is necessary (Ref 27-31-00).
S 415-015
(4)
Close the access door for the forward equipment bay, 113AL
(Ref 06-41-00).
S 865-016
(5)
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the P11 panel:
(a)
11H17, FLT CONT SHUTOFF TAIL LEFT
(b)
11H18, FLT CONT SHUTOFF TAIL CTR
(c)
11H28, FLT CONT SHUTOFF TAIL RIGHT
S 865-017
(6) Put the R, L and C FLT CONTROL SHUTOFF switches on the P61 panel to the ON position.
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(7) Remove electrical power if it is not necessary (Ref 24-22-00).
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STALL WARNING SYSTEM - DESCRIPTION AND OPERATION
________________________________________________
1. General (Fig. 1)_______
A. The stall warning system provides warning and protection from impending stalls, indication and guidance in windshear conditions, and detection and display of system faults.
B. In impending stall conditions, the system performs the following
functions:
(1)
Shakes both of the control columns to alert the flight crew.
C.
In windshear conditions, the system performs the following functions:
(1)
Signals data to the Ground Proximity Warning Computer (GPWC) to provide the flight crew with visual and aural warnings (Ref 34-46-00).
(2)
Controls the maximum pitch limit value which is signaled to the Electronic Flight Instrument System (EFIS). The maximum pitch limit value is displayed on the Electronic Attitude Director Indicator (EADI) to guide the flight crew (Ref 34-22-00).
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