11) Engage ELEV engage switch and ground pitch TP-6. Cycle column back and forth 15 or 20 times leaving it in a vertical position. Using spring scale, maintain force on control column to prevent it from moving.
12) Apply nose up tilt to vertical gyro until force on spring scale levels out. Disengage ELEV engage switch, level the vertical gyro, and remove ground. Observe that force required in step 1) plus the force in this step is greater than 20 pounds and less than 26 pounds.
13) Repeat 11) and 12) for nosedown vertical gyro tilt. Observe that required force plus the force in 2) is greater than 19 pounds and less than 27 pounds.
14) Disengage autopilot, remove ground, and level vertical gyro.
(c) Test Pitch Synchronization Prior to Engage 1) Ground pitch TP-6 and tilt the vertical gyro 5 degrees in nosedown direction. 2) Wait 15 seconds, then attempt to engage the ELEV engage switch. Observe that the ELEV engage switch does not engage. 3) Remove the ground from pitch TP-6. 4) Wait 10 seconds, then attempt to engage the ELEV engage switch. Observe
that the ELEV engage switch does engage. 5) Disengage the ELEV engage switch, remove ground, and level the vertical gyro.
583
Nov 15/79 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-11-0 Page 525
(15A) Deleted.
(16) Test Attitude Hold
(a) Test Q Control and Turbulence 1) Engage ELEV engage switch, ground pitch TP-6, and observe control column in neutral position. 2) Apply 2 degrees noseup tilt to vertical gyro. Observe that control column moves forward. Record displacement. 3) Increase airspeed to 350 KIAS. Observe that control column moves aft to
approximately 60 to 80 percent of its displacement in 2).
4) Decrease airspeed to 120 KIAS. Observe that control column moves forward.
5) Place pitch mode select switch in TURB position. Observe that control column
moves aft to approximately 40 to 70 percent of its displacement in 2) within 4 seconds. 6) Disengage autopilot, remove ground and level vertical gyro.
(b)
Test Altitude Hold Versine 1) Engage autopilot and observe control column in neutral position, and verify vertical gyro is level. 2) Engage HDG SEL switch. Set heading selector for a 45-degree increase in heading. Observe that control column moves aft. 3) Slowly increase airspeed to 350 KIAS. Observe that control column moves forward.
4) Disengage autopilot, level vertical gyro, decrease airspeed to 120 KIAS and return heading selector to zero.
(c)
Test Derived Rate (Pitch computers without rate gyro test switch)
1) Ground pitch TP-12, engage ELEV engage switch, and tilt vertical gyro approximately 5 degrees nose up. Observe that control column moves forward then returns to neutral.
2) Return vertical gyro to level. Observe that control column moves aft then returns to neutral. 3) Disengage ELEV engage switch and remove ground.
5C8 22-11-0 Jun 20/85
Page 526
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(d) Test Altitude Displacement Gain and Limit
1) Engage ELEV engage switch and ground pitch TP-6.
NOTE: Observe control column in neutral before each sequence.
2) Set altitude at 500 feet above ambient.
3) Place pitch mode select switch in ALT HOLD position and increase altitude to 580 feet. Observe that control column moves forward, and that 2.5 to 4.2 degrees of nosedown gyro tilt centers control column.
4) Decrease altitude to 420 feet. Observe that control column moves aft, and that 2.5 to 4.2 degrees noseup gyro tilt centers control column.
5) Disengage autopilot, level vertical gyro, and remove ground.
(17) Test Approach Mode
(a) Test Glide Slope Annunciator 1) Engage autopilot ground pitch TP-6, place radio simulator switch to ILS position. 2) Apply one-dot fly-up glide slope deviation signal. 3) Fail the glide slope superflag and place NAV mode select switch in AUTO/APP
position. Observe that approach progress display GLIDE SLOPE annunciator illuminates amber (G/S ARM). 4) Decrease deviation signal to zero. Observe that approach progress display GLIDE SLOPE annunciator remains illuminated amber (G/S ARM). 5) Restore the glide slope superflag. Observe that approach progress display GLIDE SLOPE annunciator illuminates green (G/S ENG).
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 AUTO FLIGHT 自动飞行 1(50)
