6) Fail the VOR/LOC superflag. Observe approach progress display indicator remains illuminated green. Disengage AIL engage switch.
(b) Test VOR Displacement Gain 1) Engage AIL engage switch, ground roll TP-9 (erection cutoff) and place mode
select switch in VOR/LOC position. 2) Ground roll TP-11, roll TP-13 and roll TP-5 (gain programmer output). 3) Set course selector to airplane heading (0 degrees of wheel displacement). 4) Apply 1/2-dot of fly-right VOR deviation signal. 5) Remove ground from roll TP-5. Observe that control wheel turns clockwise. 6) Tilt vertical gyro to center control wheel. Observe that required gyro tilt is not
less than 12 degrees and not more than 22 degrees of right roll. 7) Remove ground from roll TP9. Turn the control wheel out of detent. Observe the
mode selector switch returns to MAN. 8) Disengage AIL engage switch. 9) Remove grounds, reduce VOR deviation signal to zero, and level vertical gyro.
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(14) Test ILS Mode
(a) Test Heading Hold and Lateral Beam Sensor (150 mv) 1) Engage AIL engage switch, apply an ILS voltage using the radio simulator, and
fail the NAV superflag.
2) Apply 2-dots or more fly-right deviation signal.
3) Place mode select switch in VOR/LOC position. Observe that VOR/LOC
approach progress display indicators illuminate amber (LOC ARM).
4) Ground roll TP-11 and engage HDG SEL switch. Observe that control wheel responds to heading selector inputs.
5) Set heading selector to airplane heading (center the control wheel) and ground roll TP-13.
6) Decrease deviation input to 1/2-dot fly-right. Observe that approach progress display VOR/LOC indicator remains amber.
7) Restore the NAV superflag. Observe the approach progress display changes to VOR/LOC engaged (green), HDG SEL switch returns to center position and the control wheel rotates clockwise. Observe that not less than 4 degrees and not more than 12 degrees of left course selector command are required to center the control wheel.
8) Disengage AIL engage switch, remove grounds, remove ILS voltage and remove radio signal.
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(b) Test Gain Programmer 1) Engage autopilot, set ILS deviation to zero, and ground roll TP-10, roll TP-11, and roll TP-13. 2) Using radio altimeter test set, adjust radio altimeter altitude to 2000 feet, apply ILS voltage, and place NAV mode select switch to AUTO/APP position. 3) Adjust LOC deviation for 1/2-dot fly-right. Center the control wheel with the vertical gyro. 4) Decrease radio altimeter to 500 feet. Observe that the control wheel rotates
counterclockwise. 5) Disengage autopilot. 6) Repeat steps 1) thru 3) and open radio altimeter No. 1 circuit breaker. Observe
that the control wheel rotates counterclockwise. 7) Disengage autopilot, remove grounds and remove ILS voltage. Close circuit breaker and adjust simulated altitude to 2000 feet.
(15) Test Pitch Control Wheel Steering
NOTE: Protractors are not required for pitch channel tests. They should be removed from the control wheel and column.
Check and adjust, if necessary, null voltage of captain's and first officer's pitch transducers before conducting pitch control wheel steering tests (Ref 22-11-91).
Set stabilizer to 16 units.
(a) Test CWS Detent 1) Engage ELEV engage switch. 2) Slowly push captain's control column until column starts to move. Observe
that 3.8 to 7.5 pounds of force are required. Record force value.
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3) Repeat 2) by pulling on control column. Observe that the difference in required
force is less than 2 pounds.
4) Repeat 2) and 3) for flight officer's column.
5) Disengage autopilot.
6) and 7) Deleted
(b) Test CWS Gain and Camout 1) Slowly push control column until column starts to move. Record required force. 2) Repeat 1) for pull on control column. 3) Engage ELEV engage switch and ground pitch TP-6. Cycle column back and 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737 AMM 飛機維護手冊 AUTO FLIGHT 自動飛行 1(49)
