(i)
Make sure that the in-phase voltage is not larger than 0.040v ac.
(j)
Use the phase synchronous voltmeter and repeat the same adjustment steps for the other two neutral shift transducers.
(k)
Turn the feel unit input crank clockwise approximately 5-degrees.
(l)
With the crank held at 5-degrees, measure the in-phase output of each transducer.
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(m)
Make sure that the voltage is in-phase with the input voltage.
(n)
Make sure that the difference in the voltage between two transducers is not more than 0.40v ac.
(o)
Turn the feel unit input crank counterclockwise approximately 2-degrees.
(p)
With the crank held at 2-degrees, measure the in-phase output of each transducer.
(q)
Make sure that the voltage is in-phase with the input voltage.
(r)
Make sure that the difference in the voltage between two transducers is not more than 0.40v ac.
(s)
Put a lockwire on the control rod.
(t)
Disconnect the voltmeter and cable from the transducer connector.
S 825-055
(6) Neutral Shift Transducer Adjustment (PROCEDURE 5):
CAUTION: USE PROCEDURE 5 (WHICH USES MCDP GROUND TEST 66)
_______ ONLY IF AT LEAST ONE OF THE THREE TRANSDUCERS IS CORRECTLY ADJUSTED WITH PROCEDURE 1, 2, 3, OR 4. MCDP GROUND TEST 66 COMPARES TRANSDUCER OUTPUTS. IF AT LEAST ONE TRANSDUCER IS NOT ADJUSTED WITH PROCEDURE 1, 2, 3, OR 4, INCORRECT ADJUSTMENTS CAN OCCUR.
(a) Do MCDP Ground Test 66 - XDCR OUTPUTS
(AMM 22-00-02/201, Autoflight BITE).
S 845-056
(7)
Do these steps to put the airplane back to its usual condition:
(a)
Connect the electrical connector to the transducer.
(b)
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the P11 panel: 1) 11E17, FLT CONT COMPUTER POWER LEFT 2) 11E20, FLIGHT CONT CMPTR PWR CENTER 3) 11E35, FLT CONT CMPTR PWR RIGHT
(c)
Make sure that the rod ends are correctly engaged on the threads.
NOTE: The rod end can be seen through the inspection hole.
____
(d)
Remove the pressure from the right and center hydraulic systems (AMM 29-11-00/201).
(e)
Remove the pressure from the auxiliary pitot systems No. 1 and No. 2 (AMM 34-11-00/201).
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MAINTENANCE MANUAL
Autopilot Servo Rod Adjustment
S 825-265
(1)
Do the adjustment for the autopilot servo rod (AMM 22-12-01/401).Feel Computer Control Rod Adjustment (Fig. 508)
S 865-057
(1)
Make sure that Dimension B on the stabilizer ballscrew actuator is
15.89 | 0.01 inches (403.6 | 0.3 mm) (Fig. 502).
S 715-002
(2)
Do the steps that follow to adjust the control rod for the feel computer:
(a)
Make sure that rig pin E/ST11 can be freely put in the computer arm.
(b)
If rig pin E/ST11 cannot be freely put in, adjust the length of the control rod until the rig pin can be easily installed.
(c)
Make sure that the rod end is can be seen through the
inspection hole.
(d)
Connect the control rod to the computer arm.
(e)
Tighten the attachment fasteners.
(f)
Remove rig pin E/ST11.PCA Centering Springs Adjustment (Fig. 509)
S 865-058
(1)
Make sure that the power from the left, right, and center hydraulic systems is removed (AMM 29-11-00/201).
S 495-217
(2) 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：757 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 3(23)
