曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
DFCS - FUNCTIONAL DESCRIPTION - A/P ENGAGE LOGIC TABLE-1
EFFECTIVITY
SHZ ALL 22-11-00
Page 98.55
D633A101-SHZ1 Jun 10/2003
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
22-11-00-056
General
The table shows more of the functions that the autopilot engage
interlock circuits monitor and the conditions that they cause.
These are the three conditions:
* Pre-engage - shows the functions necessary to engage the
autopilot
* Hold - shows the functions necessary to keep the autopilot
engaged
* Disengage - shows functions that disengage the autopilot.
Engage and Disengage Functions
19. If the crew wants to make a dual approach in CMD, they
must put the other A/P in CMD at a radio altitude more than 800
feet.
20. The IRS transfer switch must be in the NORMAL position to
engage the autopilot.
21. If the IRS transfer switch is in the BOTH ON 1 or BOTH ON 2
position, the autopilot will disengage and cannot be reengaged.
22. The VHF NAV transfer switch must be in a position so that
the data that the autopilot uses also shows on the CDS.
23. The flap position data from the flap transmitters must agree
with the flap position data from the SMYD.
24. The signal from the SMYD that shows a stall condition and
activates the stick shaker must not be active.
25. The selected baro corrected altitude from the ADIRU must
be valid.
26. The option pin that shows the FCC can do the dual approach,
CAT IIIA (50 ft DH), must be selected in the second up channel
FCC.
27. The VHF nav control panel for the second up channel must
be tuned to the ILS frequency.
28. The FCC that is the second up channel for a dual approach
must be on a different power bus then the first up FCC.
29. The autopilot that is the second up for the dual approach
must be in the CMD and not the CWS mode.
30. During a dual approach if one autopilot disengages, the
other autopilot also disengages.
31. The trim sensors monitor compares the neutral shift
expected value from stabilizer position and Mach trim
feedback with the actual NSS input. If the difference is more
than 0.5 elevator degrees and in dual autoland, the autopilot will
disengage.
DFCS - FUNCTIONAL DESCRIPTION - A/P ENGAGE LOGIC TABLE-2
EFFECTIVITY
SHZ ALL 22-11-00
Page 98.56
D633A101-SHZ1 Jun 10/2003
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
22-11-00-146
DFCS - FUNCTIONAL DESCRIPTION - A/P ENGAGE LOGIC TABLE-2
DFCS - FUNCTIONAL DESCRIPTION - A/P ENGAGE LOGIC TABLE-2
EFFECTIVITY
SHZ ALL 22-11-00
Page 98.57
D633A101-SHZ1 Jun 10/2003
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
22-11-00-146
THIS PAGE IS INTENTIONALLY LEFT BLANK
DFCS - FUNCTIONAL DESCRIPTION - A/P ENGAGE LOGIC TABLE-2
22-11-00
Page 98.58
D633A101-SHZ1 Oct 10/2002
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
General
The table shows the roll mode conditions that cause the
autopilot to disengage.
Disengage Conditions
1. The magnetic heading must be valid when in the CWS
heading hold or the autopilot will disengage. If the magnetic
heading fails while in the heading mode, the A/P will go to the
CWS mode first and then disengage.
2. If the radio altitude is less than 2000 feet and the A/P is not in
flare arm, it will disengage if the crew pushes a TO/GA switch.
3. If the crew pushes a TO/GA switch after touchdown (wheel
spin greater than 60 knots), both autopilots will disengage.
4. The LOC antenna must switch to the forward antenna when in
the approach mode and the crew tunes to a LOC frequency. If it
does not switch within 4.5 seconds, the autopilots will
disengage.
5. When in the dual (autoland) mode for at least 5 seconds, the
FCC monitors these:
* Autopilot actuator monitor (AAM)
* Surface position monitor (SPM)
* CPU monitor.
If a monitor shows a failure, the autopilots will disengage.
6. If the NAV transfer switch is in the BOTH ON 1 position, the B
A/P disengages. If the NAV transfer switch is in the BOTH ON 2
position, the A A/P disengages.
7. After LOC engage, if the LOC receiver is not valid or a beam
anomaly occurs, the autopilot disengages. There is a 10 second
delay to allow for interrupts.
A beam anomaly occurs if the localizer beam rate is greater
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
737NGAMM1(41)
