(f)
Increase altitude to 21,000 feet. At approximately 20,300 ft above selected altitude check that control column moves forward, altitude alert light flashes (2 second) and the aural warn sounds (1.5 second).
(g)
At approximately 20,900 feet, verify that altitude alert lights extinguish. Decrease the altitude toward 20,000 ft. At approximately 20,900 feet verify that altitude alert lights begin to flash and aural warning sounds for 1 second. Check that altitude alert lights extinguish at approximately 20,300 feet.
(h)
Stabilize altitude at 20,000 feet. Place trailing edge flaps to 30 units. Reduce altitude toward 19,000 feet at 1500 ft/min. Check that no altitude alert warnings occur.
(i)
Disengage autopilot. Reduce altitude to ambient.
(j)
Repeat (a) thru (i) using A/P ENGAGE B switch.
(20)
Test A/P Pitch Control Wheel Steering
(a)
Remove protractors and adapters from control wheels and manually set stabilizer to 16 units.
(b)
Place A/P ENGAGE A switch to CMD. Observe CWS PITCH and CWS ROLL is annunciated on FMAs.
(c)
Place A/P ENGAGE A switch to CWS. Observe CWS PITCH and CWS ROLL annunciation remains and control columns are vertical.
(d)
With spring scale attached to control column, slowly push captain's column until column begins to drive. Observe required force is between 4.5 and 8.5 pounds. Check that voltage at J6-63 is between -1.0 and -2.0 volts dc on AFCS computer A.
(e)
Repeat step (d) pulling on column except check that voltage at J6-63 is between +1.0 and +2.0 volts dc.
(f)
Repeat steps (d) and (e) using first officer's control column.
(g)
Place A/P ENGAGE A switch to CMD and press ALT HOLD button. Observe the ALT HOLD button illuminates and ALT HOLD is annunciated on FMAs. Observe CWS PITCH annunciation goes off.
(h)
Push on captain's control column. Observe force required to move column out of detent is between 18 and 24 pounds. Observe ALT HOLD button and ALT HOLD annunciation go off and CWS PITCH as annunciated.
(i)
Press ALT HOLD button and repeat step (h) except pull on control column.
(j)
Press ALT HOLD button and repeat steps (h) thru (i) using first officer's control column.
(k)
Disengage autopilot.
(l)
Repeat steps (b) thru (k) using A/P ENGAGE B switch and AFCS computer B.
(21)
Test Pitch CWS Tracking
(a)
Apply a pitot pressure of 4 psi to the elevator feel computer (Pitot heads located on vertical fin).
(b)
Remove connector D385 from F/O's pitch force transducer.
(c)
Using a spring scale, push captain's column with a force of 20 pounds. Check AFCS A computer pin in J6-63 for -3.5 +2.0 VDC.
(d)
Repeat (c) with a pull. Check that voltage is opposite polarity and within 3.0 v of (c).
(e)
Reconnect D385 to F/O's transducer.
(f)
Remove connector D383 from captain's pitch force transducer.
(g)
Repeat (c) and (d) with F/O's column.
(h)
Reconnect D383 to captain's transducer.
(i)
Remove connector D1675 from F/O's pitch force transducer.
(j)
Repeat (c) and (d) by measuring voltage at J6-63 of AFCS B computer.
(k)
Reconnect D1675 to F/O's transducer.
(l)
Remove connector D1673 from captain's pitch force transducer.
(m)
Repeat (j) with F/O's column.
(n)
Reconnect D1673 to captain's transducer.
(o)
Verify that readings between (j) and steps (c)/(d) with respect to push and pull are within 0.5 v. Verify that the readings between (m) and (g) with respect to push and pull are within 0.5 v.
(22)
Test A/P Roll Control Wheel Steering
(a)
Place A/P ENGAGE A switch to CWS.
(b)
Using 10-pound limit torque wrench attached to hub of control wheel, slowly apply clockwise force until wheel begins to drive. Observe force required is between 8 and 16 inch-pounds. Check that voltage at J7-63 is between -1.0 and -2.0 VDC on AFCS computer A.
(c)
Repeat step (b) rotating control wheel to left and check that voltage is between +1.0 and +2.0 volts dc.
(d)
Place A/P ENGAGE switch to CMD and press HDG SEL button. Observe HDG SEL button illuminates and HDG SEL Is annunciated on FMAs. Observe CWS ROLL annunciation goes off.
(e)
Rotate captain's control wheel to the left. Observe force required to rotate control wheel out of detent is between 60 and 100 inch-pounds. Observe HDG SEL button and HDG SEL annunciation go off and CWS ROLL is annunciated. Release control wheel.
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本文链接地址：737 AMM 飞机维护手册 AUTO FLIGHT 自动飞行 1(106)
