(u)
Press the G/A switch, check that A/P annunciation changes from FLARE to TO/GA. Observe control column moves aft and flight directors indicate 12 degrees nose-up.
(v)
Position antiskid test box master switch to ON. Press G/A switch. Verify that A/P and F/D remain in G/A mode.
(w)
Disengage autopilot. Position antiskid test box master switch to OFF. Open autopilot stabilizer trim ac circuit breaker.
(x)
Repeat step (s).
(y)
Decrease radio altimeter altitude to 30 feet. Position antiskid test box master switch to ON. Press G/A switch. Check that autopilot disengages.
505
22-11-01 Page 516 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/88
505
Jun 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-11-01 Page 517
(z) Repeat steps (s) and (y) with antiskid test box selected to inboard wheel of right gear. Position antiskid test box master switch to OFF.
(aa) Repeat step (s) to obtain FLARE arm.
(ab) Adjust simulated barometric altitude to 200 feet then decrease radio altitude to 200
feet.
505
22-11-01 Page 518 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/88
(ac) Press G/A switch. Verify that A/P FMA annunciation changes from FLARE to TO/GA.
Observe control column moves aft and flight directors indicate fly-up. (ad) Press V/S and HDG pushbuttons. Verify that A/P and F/D remain in TO/GA. (ae) Increase radio altitude to 500 feet. Press HDG SEL pushbutton. Verify that HDG SEL
pushbutton illuminates, HDG SEL is annunciated on FMAs and control wheel
responds to HDG SEL inputs. (af) Disengage autopilot. (ag) Repeat step(s). (ah) Set baro altitude to 200 feet then decrease radio altitude to 200 feet. Press GA
switch with radio altitude at 200 feet then increase baro altitude to 2000 feet at 2000 feet per minute. (ai) Increase radio altitude to 500 feet. Verify that A/P red warning lights illuminate and
ALT ACQ on FMAs does not come on at approximately 1700 feet. (aj) Set the MCP altitude to 2200 feet. Verify that A/P red warning lights extinguish. (ak) Increase simulated barometric altitude toward 2200 feet at 1000 feet per minute rate.
Verify that when altitude approaches 2200 feet A/P ENGAGE B switch drops to OFF
and A/P and F/D ALT HOLD is annunciated on FMAs. (al) Disengage autopilot. Select both F/Ds to OFF. (am) Set radio altitude to 0 feet. Set IAS to below 60 knots. Wait 3 minutes. Place both F/D
switches to ON press TOGA switch. Verify that HDG SEL and TOGA is annunciated
on FMAs. (an) Place both F/D switches to OFF. (ao) Position antiskid test box master switch to OFF and disconnect from antiskid unit.
Close AUTO SPEED BRAKE circuit breaker and restore spoiler/speed brake system to normal.
(18)
Test Approach Mode Generator Failure Interlock
(a)
Set Radio Altimeter and baro altitude to 1800 feet. Set flaps at 5 units and Alpha vanes at zero (level with waterline).
(b)
Start APU (Ref 49-11-0, M/P). Close both No. 1 and 2 Bus Tie Breakers (Overhead Panel, APU Left and APU Right).
(c)
Engage channel A autopilot. Select ILS test frequency and apply one dot Fly-Up glide slope signal. Select APP mode. Set LOC radio signal to zero deviation. Engage channel B Autopilot.
(d)
Simulate No. 1 generator failure by opening No. 1 Bus Tie Breaker. Check that both A/P ENGAGE paddles drop to off. Verify that it is possible to re-engage one A/P channel. Select APP mode. Verify that remaining channel is locked off.
(e)
Close No. 1 Bus Tie Breaker, select APP mode and engage Autopilot in dual-channel operation. Simulate No. 2 generator failure by opening No. 2 Bus Tie Breaker. Verify that results are the same as observed in step (d).
(f)
Disengage Autopilot. Open No. 1 and 2 Bus Tie Breakers and shut off APU. Restore airplane to normal ground power.
(19)
Test A/P Altitude Select, Altitude Hold and Altitude Alert.
(a)
Place trailing edge flaps up. Place A/P ENGAGE A switch to CMD.
(b)
Select 20,000 feet with ALTITUDE SEL control.
(c)
Apply 18,000 feet of altitude using pitot static source.
(d)
Increase altitude from 18,000 feet toward 20,000 feet using static pressure source at 1500 ft/min. Observe at approximately 19,100 feet, altitude alert lights illuminate and aural warning sounds for 1 second. Observe at approximately 19,600 ft, mode annunciators indicate ALT ACQ. Observe at approximately 19,700 feet, altitude alert lights extinguish.
(e)
Increase altitude to selected altitude. Observe that ALT ACQ retracts and ALT HOLD annunciations appear.
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(105)
