(c)
Disengage ELEV engage switch. Observe that pitch mode select switch returns to OFF and that ALT HOLD mode cannot be selected.
(d)
Engage ELEV engage switch and place pitch mode select switch in ALT HOLD position.
(e)
Pull either control column out of detent. Observe that pitch mode select switch returns to OFF when there is 15 to 23 pounds of force on the control column.
(f)
Place pitch mode select switch in ALT HOLD position.
(g)
Place NAV mode select switch out of MAN position. Observe that pitch mode select switch returns to OFF when mode select switch reaches AUTO APP position and glide slope is captured.
(h)
Return mode select switch to MAN position.
(i)
Place pitch mode select switch in ALT HOLD position.
(j)
Place air data computer selector switch to FAIL position.
(k)
Depress air data computer PUSH TO TEST switch for approximately 2 seconds. Observe that pitch mode select switch returns to OFF.
(l)
Return air data computer selector switch to normal operating position.
(m)
Disengage autopilot.
(8)
Test TURB Mode Control
(a)
Engage autopilot.
(b)
Place pitch mode select switch in TURB position.
(c)
Disengage ELEV engage switch. Observe that pitch mode select switch returns to OFF and the TURB mode cannot be selected.
22-11-0 May 15/81
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(d)
Engage ELEV engage switch. With either control wheel or control column out of detent, observe that TURB position can be selected.
(e)
Place pitch mode select switch in TURB position. Observe that VOR/LOC position can be selected.
(f)
Select an ILS frequency. Observe that mode select switch returns to MAN position and the VOR/LOC mode cannot be reselected. Observe that HDG SEL can be engaged.
(g)
Disengage autopilot.
(9)
Test Autopilot Annunciation
(a)
Rotate roll control channel self-test switch through five test positions and then to OFF. Observe that autopilot warning lights illuminate steadily for each test position.
(b)
Repeat (a) for pitch control channel.
(c)
Open 28-volt dc autopilot warning light battery bus circuit breakers and depress captain's and first officer's warning lights. Observe that neither light illuminates.
(d)
Close circuit breaker and press each light. Observe that lights flash when pressed.
(e)
Press captain's and then first officer's approach progress display indicator caps. Observe that approach progress display annunciators illuminate.
NOTE: Pressing cap on A/P (right) side causes the annunciators to illuminate green. Pressing the cap on the F/D (left) side causes the applicable annunciators to illuminate amber.
(f)
Engage autopilot and open stab trim three-phase ac circuit breaker.
(g)
Push either control column forward and release. Observe that STAB OUT OF TRIM light on center instrument panel illuminates after approximately 12 seconds.
(h)
Place LIGHTS switch on center instrument panel to DIM position. Observe that STAB OUT OF TRIM light dims.
(i)
Place LIGHTS switch to BRT position. Observe that STAB OUT OF TRIM light returns to original brightness.
(j)
Disengage autopilot, and place the LIGHTS switch, located on center instrument panel, to DIM position. Observe the autopilot warning light flashes at reduced intensity. Re-set the lights to BRT position.
(10)
Autopilot Self-Test
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Oct 20/84 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-11-0 Page 515
(a) General 1) Steps for any one channel must be performed in sequence starting with the channel disengaged and the self-test switches in OFF position. 2) Autopilot warning lights must come on steadily when any self-test switch is in
any position except OFF. 3) Do not apply rate gyro test signals for longer than 10 seconds. 4) Open radio altimeter circuit breakers (as applicable). 5) Maintain air data computer pitot and static inputs at ambient pressure.
(b) Roll Control Channel Self-Test
STEP ACTION OBSERVATION
1) Engage AIL engage switch and
select a VOR frequency
2) Deleted
3) Deleted
4) Disengage AIL engage switch
5) Place self-test switch in OFF Self-test meter reads In RED range
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本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊 AUTO FLIGHT 自動飛行 1(46)
