(n)  
Event 14 - If the radio altimeter valid discrete is lost when both GS and LOC are engaged (prior to monitors active) the A/P is disengaged. A 2-second delay allows for short interrupts.

 (o)  
Event 15 - If both channels are engaged with monitors active both radio altimeters must fail before the disengage signal is generated.

 (p)  
Event 16 - During the APPROACH mode, if a LCL or FGN bus transfer has been made and the FGN is placed in CMD the LCL cannot be engaged.

 E. A/P Red Warning Lights Operation (Fig. 18)
 (1)  
The A/P red WARN light warns the crew when the A/P is disengaged by flashing red. The red warn light is illuminated steady red when BITE is performed or for a computer warn signal. The A/P warning lights are connected in parallel.

 (2)  
The A/P warning lights flash red and an aural warning (horn) is issued if either A/P engage switch changes from CMD or CWS to the OFF. A flashing A/P warning may be reset by pressing and releasing either A/P warning light assembly or either disengage switch.

 (3)  
The A/P warning light illuminates steady red for one of the
 following:

 (a)  BITE in progress.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú

 22-11-01
 ú ú 10 Page 56 ú Jul 15/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú

 22-11-01
 ú ú 04 Page 57 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 (b)  
Yaw damper armed for BITE.

 (c)  
When on a dual approach with both pitch channels engaged, descended below 800 feet and prior to 100 ft, and if the STAB OUT TRIM light is illuminated. If the A/P red light is on when descending below 100 ft, the light remains on unless the STAB TRIM WARN light is extinguished.

 (d)  
A/P warn from the master flight control computer. These warning are initiated: 1) When on the ground and the power up test fails. 2) When an A/P GO AROUND is made and the radio altitude is

 greater than 400 and ALT ACQUIRE is INHIBITED. This inhibit is due to the elevator position exceeding the single channel authority.
 F. A/P - A/T Amber Warning Lights Operation (Fig. 19)
 (1)  
The A/P and A/T warning lights flash amber to alert the crew.

 (a)  
The A/P warning light flashes to indicate CWS reversion. The following, A/P Warning Lights, section applies only if the CWS WARNING option is selected.

 (b)  
The A/T warning light flashes to indicate that the A/T is not holding the target speed. The following , A/T Amber Warning lights, section applies only if the A/S WARNING option is selected.

 (2)  
A/P Warning Lights

 (a)  The CWS warning causes the A/P warning lights on both FMA's to flash amber, if the A/P is engaged in CMD, a CMD mode is selected and CWS is used to override the CMD mode. The warning is initiated by single shots and the logic is latched until reset by pressing the warning lights. The CWS warning signal is sent to the mode control panel on the 429 bus. The mode control bus selects the proper channel, decodes the signal and provides grounds for both amber warning lights on the flight mode annunciators.

 (3)  
A/T Amber Warning Lights

 (a)  An automatic test of the A/T flashing amber function is performed if the A/T is engaged in MCP SPD or FMC SPD, TAS is valid, more than 150 sec after liftoff and flaps are not up. The A FCC circuit is tested, the logic TEST COMPLETE goes to the FGN FCC and the B FCC circuit is tested. The autotest causes the A/T amber light to flash for two seconds, go off for two seconds and then flash again for two seconds.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú

 22-11-01
 ú ú 06 Page 58 ú Nov 12/01
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 自動飛行 AUTOFLIGHT 1(101)